FCOM M2K 065 FLIGHT CREW OPERATING MANUAL HC CRU 2K
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
The content of this document is the property of Airbus. It is supplied in confidence and commercial
security on its contents must be maintained. It must not be used for any purpose other than that for
which it is supplied, nor may information contained in it be disclosed to unauthorized persons. It must
not be reproduced in whole or in part without permission in writing from the owners of the copyright.
© AIRBUS 2005. All rights reserved.
REFERENCE: GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
ISSUE DATE: 17 OCT 17
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TRANSMITTAL LETTER
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Issue date: 17 OCT 17
This is the FLIGHT CREW OPERATING MANUAL major event publication at issue date 17 OCT
17 for the A318/A319/A320/A321 and replacing last issue dated 05 SEP 17
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
TRL P 1/2
17 OCT 17
TRANSMITTAL LETTER
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
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FCOM
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FILING INSTRUCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Please incorporate this major event revision as follow:
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Subsection Title
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LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
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LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETIN
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FCOM
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FLIGHT CREW
OPERATING MANUAL
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FLIGHT CREW
OPERATING MANUAL
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Subsection Title
Rev. Date
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
17 OCT 17
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
17 OCT 17
General Information
05 SEP 17
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
17 OCT 17
Overview
24 JAN 17
Description
24 JAN 17
Ground Handling
19 JUN 17
Ground Clearance Diagram
24 JAN 17
Landing Geometry
19 JUN 17
Visual Ground Geometry
19 JUN 17
General
24 JAN 17
Main Components
22 MAR 17
Temperature and Flow Regulation
22 MAR 17
System Operation under Failure Condition
24 JAN 17
Controls and Indicators
22 MAR 17
General
24 JAN 17
Main Components
24 JAN 17
System Operation
24 JAN 17
Controls and Indicators
24 JAN 17
General
24 JAN 17
Avionics Ventilation
24 JAN 17
Battery Ventilation
24 JAN 17
Lavatory and Galley Ventilation
24 JAN 17
Controls and Indicators
24 JAN 17
General
24 JAN 17
System Operation
24 JAN 17
Controls and Indicators
22 MAR 17
ECAM Cond Page
24 JAN 17
Description
24 JAN 17
System Interface Diagram
24 JAN 17
FMGS Modes of Operation
24 JAN 17
Management of the Displays
24 JAN 17
MCDU
24 JAN 17
FCU
05 SEP 17
Thrust Levers
24 JAN 17
Primary Flight Display
24 JAN 17
Navigation Display
24 JAN 17
General
22 MAR 17
Characteristic Speeds
22 MAR 17
Limit Speeds
22 MAR 17
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PRELIMINARY PAGES
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FLIGHT CREW
OPERATING MANUAL
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Subsection Title
Rev. Date
Protection Speeds
22 MAR 17
Other Speeds
22 MAR 17
General
24 JAN 17
General
24 JAN 17
Position Computation
24 JAN 17
Evaluation of Position Accuracy
22 MAR 17
Radio Navigation Tuning
05 SEP 17
Alignment of Inertial Reference System
24 JAN 17
Navigation Database
24 JAN 17
General
24 JAN 17
General
12 APR 17
FMS2 HONEYWELL
24 JAN 17
General
24 JAN 17
FMS2 Honeywell
24 JAN 17
Optimization
24 JAN 17
Cost Index
24 JAN 17
Predictions
24 JAN 17
FMS2 Honeywell
05 SEP 17
FMS2 Honeywell
24 JAN 17
MCDU - Data Format List
24 JAN 17
Effect of Baro Reference Setting
24 JAN 17
Clear Key (Clearing Function)
24 JAN 17
How to Execute a Diversion
24 JAN 17
Engine Out
05 SEP 17
Secondary Flight Plan
24 JAN 17
Pilots/Stored Route Function
24 JAN 17
Report Page
24 JAN 17
Closest Airports
24 JAN 17
Time Marker
24 JAN 17
Step ALTS
12 APR 17
Required Time of Arrival (RTA)
24 JAN 17
Equitime Point
24 JAN 17
MCDU Back Up Navigation
24 JAN 17
Descent Profile Optimization (if installed)
24 JAN 17
AOC Functions
24 JAN 17
Print Functions
24 JAN 17
FMGC Reset
12 APR 17
"CHECK GW" or "CHECK WEIGHT" Message
22 MAR 17
FMS2 HONEYWELL Temporary Abnormal Behaviors
22 MAR 17
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LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
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FLIGHT CREW
OPERATING MANUAL
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DSC-23-10-40
DSC-23-10-50
DSC-23-20-10
Subsection Title
Rev. Date
All FMS Temporary Abnormal Behaviors
22 MAR 17
General
24 JAN 17
Flight Director
24 JAN 17
Autopilot (AP)
24 JAN 17
Speed/Mach Control
24 JAN 17
AP/FD Modes General
24 JAN 17
AP/FD Lateral Modes
24 JAN 17
Principles
24 JAN 17
Climb Mode
24 JAN 17
Open Climb Mode
24 JAN 17
Descent Mode
24 JAN 17
Open Descent Mode
24 JAN 17
Altitude Acquire Mode
12 APR 17
Altitude Hold Mode
24 JAN 17
Vertical Speed Mode - Flight Path Angle Mode (V/S - FPA)
05 SEP 17
Expedite
24 JAN 17
Mode Reversions
22 MAR 17
General
24 JAN 17
Takeoff
24 JAN 17
General
24 JAN 17
Precision Approach
24 JAN 17
Non Precision Approach
05 SEP 17
Go Around (GA)
24 JAN 17
Autothrust
22 MAR 17
Flight Mode Annunciator (FMA)
24 JAN 17
Temporary Abnormal Behaviors
05 SEP 17
General
24 JAN 17
Yaw Functions
24 JAN 17
Flight Envelope Function
22 MAR 17
Windshear Detection Function
24 JAN 17
Controls and Indicators
24 JAN 17
Auto Flight - AOC Functions
24 JAN 17
Auto Flight - Print Interface
24 JAN 17
Introduction
22 MAR 17
Radio Tuning
22 MAR 17
Intercommunication Systems
22 MAR 17
Cockpit Voice Recorder
22 MAR 17
Controls
22 MAR 17
Flight Crew Interphone System
22 MAR 17
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LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
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FLIGHT CREW
OPERATING MANUAL
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DSC-24-10-10
DSC-24-10-20
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DSC-26-10
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DSC-27-20-10-30
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DSC-27-20-20
Subsection Title
Cabin Interphone System
Service Interphone System
Passenger Address
Radio Communication
Emergency Evacuation
Emergency Locator Transmitter
Memo Display
General
Generation of Electrical Power
General
Normal Configuration
Abnormal Configurations
Distribution Table
Controls and Indicators
General
Cockpit Plan
Seats
Main Instrument Panels
Pedestal
Overhead Panel
C/B Panels
Foot Warmer (If Installed)
Emergency Equipment
General
System Description
Controls and Indicators
System Description
Controls and Indicators
System Description
System Description
Controls and Indicators
General
Architecture
General
Pitch Control
Lateral Control
Sideslip Target
Aircraft Trimming
Reconfiguration Control Laws
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Rev. Date
05 SEP 17
05 SEP 17
05 SEP 17
05 SEP 17
19 JUN 17
22 MAR 17
05 SEP 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
05 SEP 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
24 JAN 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
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17 OCT 17
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LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
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DSC-28-10-70
DSC-28-10-80
DSC-28-20
DSC-29-10-10
DSC-29-10-20
DSC-29-10-30
DSC-29-20
DSC-30-10-10
DSC-30-20-10
DSC-30-20-20
DSC-30-30-10
DSC-30-30-20
DSC-30-40-10
DSC-30-40-20
DSC-30-50-10
DSC-30-50-20
DSC-30-60-10
DSC-30-60-20
DSC-30-70-10
DSC-31-05-10
DSC-31-05-20
DSC-31-05-30
DSC-31-05-40
DSC-31-05-50
DSC-31-05-60
DSC-31-10
DSC-31-15
DSC-31-20
DSC-31-25-10
DSC-31-25-20
DSC-31-27
Subsection Title
Controls and Indicators
Description
Controls and Indicators
General
Tanks
Engine Feed
APU Feed
Fuel Recirculation System
Refueling and Defueling
Fuel Quantity Indication and Level Sensing
Controls and Indicators
General
Generation
Distribution
Controls and Indicators
Description
Description
Controls And Indicators
Description
Controls and Indicators
Description
Controls and Indicators
Description
Controls and Indicators
Description
Controls and Indicators
Description
Introduction
Cockpit Arrangement
Architecture
Controls and Switching
Reconfiguring the DMC
Reconfiguring DUs
ECAM Description
Indications on E/WD
Indications on SD
General
Example
OEB Reminder
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Rev. Date
22 MAR 17
24 JAN 17
24 JAN 17
24 JAN 17
22 MAR 17
22 MAR 17
24 JAN 17
22 MAR 17
22 MAR 17
24 JAN 17
22 MAR 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
19 JUN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
05 SEP 17
24 JAN 17
24 JAN 17
24 JAN 17
12 APR 17
22 MAR 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
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17 OCT 17
PRELIMINARY PAGES
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
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Localization
DSC-31-30
DSC-31-40
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DSC-31-60-30
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DSC-33-30-10
DSC-33-30-20
DSC-33-40-10
DSC-34-NAV-10-10
DSC-34-NAV-10-20
DSC-34-NAV-15-10
DSC-34-NAV-20
DSC-34-NAV-30-10
DSC-34-NAV-30-20
DSC-34-NAV-30-30
DSC-34-NAV-40-10
DSC-34-SURV-10-10
DSC-34-SURV-10-20
DSC-34-SURV-30-10
DSC-34-SURV-30-20
DSC-34-SURV-30-30
DSC-34-SURV-40-10
Subsection Title
Rev. Date
ECAM Controls
05 SEP 17
Indications on PFD
22 MAR 17
Indications on ND
22 MAR 17
EFIS Controls
24 JAN 17
General
24 JAN 17
Controls and Indicators
22 MAR 17
Flight Data Recording System
24 JAN 17
Controls and Indicators
24 JAN 17
Aircraft Integrated Data System
24 JAN 17
Description
24 JAN 17
Landing Gear System/Interface
24 JAN 17
Interactions between Landing Gear and Aircraft Systems
24 JAN 17
Controls and Indicators
24 JAN 17
Description
24 JAN 17
Controls and Indicators
05 SEP 17
Description
22 MAR 17
Controls and Indicators
24 JAN 17
General
24 JAN 17
Description
24 JAN 17
Controls and Indicators
24 JAN 17
General
24 JAN 17
Controls and Indicators
24 JAN 17
Description
05 SEP 17
Controls and Indicators
24 JAN 17
Controls and Indicators
24 JAN 17
Description
24 JAN 17
Controls and Indicators
22 MAR 17
Description
24 JAN 17
Standby Instruments
24 JAN 17
Tuning
24 JAN 17
Navaids
24 JAN 17
Controls and Indicators
24 JAN 17
Description
24 JAN 17
Description
22 MAR 17
Controls and Indicators
22 MAR 17
Description
22 MAR 17
Predictive Windshear System
22 MAR 17
Controls and Indicators
22 MAR 17
Description
22 MAR 17
Continued on the following page
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PLP-LESS P 6/14
17 OCT 17
PRELIMINARY PAGES
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
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Localization
DSC-34-SURV-40-20
DSC-34-SURV-40-35
DSC-34-SURV-40-40
DSC-34-SURV-60-10
DSC-34-SURV-60-20
DSC-35-10
DSC-35-20-10
DSC-35-20-20
DSC-35-30-10
DSC-35-30-20
DSC-35-40-10
DSC-36-10-10
DSC-36-10-20
DSC-36-10-30
DSC-36-10-40
DSC-36-10-50
DSC-36-10-60
DSC-36-20
DSC-38-10
DSC-45-10
DSC-45-20
DSC-45-25
DSC-45-30
DSC-46-10-10
DSC-46-10-20-10
DSC-46-10-40-30
DSC-46-10-40-40
DSC-46-10-40-60
DSC-46-10-50
DSC-46-20-20
DSC-46-30
DSC-46-40-10
DSC-46-40-20
DSC-46-40-30
DSC-49-10-10
DSC-49-10-20
DSC-49-20
DSC-52-10-10
DSC-52-10-20
Subsection Title
GPWS Basics Modes
Predictive GPWS Functions
Controls and Indicators
Description
Controls and Indicators
General
Description
Controls and Indicators
Description
Controls and Indicators
Description
General
Engine Bleed System
APU Bleed Air Supply
Crossbleed
Leak Detection
Operation Following Failures
Controls and Indicators
Description
Description
System Operation
Data Loading
Printer
General System Description
General
MCDU Datalink Pages
MCDU Scratchpad Messages
ECAM
How To
Applications
Electronic QRH (eQRH)
General
In Seat Power Supply System
Controls and Indicators
General
Main Components
Controls and Indicators
General
Passenger Doors
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Rev. Date
05 SEP 17
22 MAR 17
19 JUN 17
22 MAR 17
22 MAR 17
24 JAN 17
24 JAN 17
22 MAR 17
24 JAN 17
24 JAN 17
24 JAN 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
24 JAN 17
22 MAR 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
05 SEP 17
22 MAR 17
24 JAN 17
24 JAN 17
19 JUN 17
22 MAR 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
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17 OCT 17
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LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
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FLIGHT CREW
OPERATING MANUAL
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Localization
DSC-52-10-30
DSC-52-10-40
DSC-52-10-50
DSC-52-10-60
DSC-52-10-80
DSC-52-20
DSC-52-40-10
DSC-52-40-20
DSC-52-40-30
DSC-52-50
DSC-56-10
DSC-56-20
DSC-56-30
DSC-56-40
DSC-70-05
DSC-70-10
DSC-70-20
DSC-70-30-10
DSC-70-30-20
DSC-70-30-30
DSC-70-30-40
DSC-70-40
DSC-70-50
DSC-70-60
DSC-70-70
DSC-70-80-10
DSC-70-80-20
DSC-70-80-30
DSC-70-80-40
DSC-70-90-10
DSC-70-90-20
DSC-70-90-30
DSC-70-90-40
DSC-70-90-50
PRO-PLP-LETDU
PRO-ABN-ABN-00
PRO-ABN-ABN-ADV
PRO-ABN-ABN-MEM
PRO-ABN-ABN-QRH
Subsection Title
Rev. Date
Emergency Exits
22 MAR 17
Cargo Doors
22 MAR 17
Avionics Compartment Access Door
24 JAN 17
Cockpit Door
22 MAR 17
Escape Slides/Rafts
24 JAN 17
Controls and Indicators
24 JAN 17
Description
22 MAR 17
Cockpit Door Locking System (CDLS)
22 MAR 17
Cockpit Door Surveillance System (CDSS)
22 MAR 17
How to
22 MAR 17
General
22 MAR 17
Fixed Windows
22 MAR 17
Sliding Windows
22 MAR 17
Description
22 MAR 17
Overview
24 JAN 17
System Description
22 MAR 17
FADEC
22 MAR 17
General
22 MAR 17
Thrust Levers
22 MAR 17
Thrust Rating Limit
24 JAN 17
Thrust Control
22 MAR 17
Fuel System (CFM56)
22 MAR 17
Oil System
24 JAN 17
Airbleed System (CFM56)
22 MAR 17
Thrust Reverser System
22 MAR 17
General
22 MAR 17
Architecture
24 JAN 17
Ignition System
22 MAR 17
Engine Starting System
22 MAR 17
Overhead Panel
24 JAN 17
Pedestal
22 MAR 17
Maintenance Panel
24 JAN 17
Engine Display
05 SEP 17
Memo Display
24 JAN 17
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
05 SEP 17
INTRODUCTION
05 SEP 17
[ADV] ECAM ADVISORY
05 SEP 17
[MEM] MEMORY ITEMS
19 JUN 17
[QRH] PROCEDURES
22 MAR 17
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PLP-LESS P 8/14
17 OCT 17
PRELIMINARY PAGES
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
Localization
PRO-ABN-ABN-RESET
PRO-ABN-A-ICE
PRO-ABN-AIR
PRO-ABN-APU
PRO-ABN-APUF
PRO-ABN-AUTO_FLT
PRO-ABN-AVNCS
PRO-ABN-BLEED
PRO-ABN-BRAKES
PRO-ABN-NWS
PRO-ABN-CAB_PR
PRO-ABN-C_B
PRO-ABN-COM
PRO-ABN-COND
PRO-ABN-CONFIG
PRO-ABN-DATALINK
PRO-ABN-DOOR
PRO-ABN-EIS
PRO-ABN-ELEC
PRO-ABN-ENG
PRO-ABN-F_CTL
PRO-ABN-FUEL
PRO-ABN-FWS
PRO-ABN-HYD
PRO-ABN-LG
PRO-ABN-MISC
PRO-ABN-NAV
PRO-ABN-OVERSPEED
PRO-ABN-RECORDER
PRO-ABN-SMOKE
PRO-ABN-SURV
PRO-ABN-VENT
PRO-ABN-WHEEL
PRO-ABN-W_A_ICE
PRO-ABN-90
PRO-NOR-SOP-01
PRO-NOR-SOP-02
PRO-NOR-SOP-03
PRO-NOR-SOP-04
Subsection Title
[RESET] SYSTEM RESET
A-ICE
AIR
APU
APU FIRE
AUTO FLT
AVIONICS SMOKE
BLEED
BRAKES
BRAKES-N/WS
CAB PR
C/B
COM
COND
CONFIG
DATALINK
DOOR
EIS
ELEC
ENG
F/CTL
FUEL
FWS
HYD
L/G
MISC
NAV
OVERSPEED
RECORDER
SMOKE
SURV
VENT
WHEEL
WING A.ICE
Detailed Cabin / Cockpit Evacuation Procedure
General Information
Flight Preparation
Safety Exterior Inspection
Preliminary Cockpit Preparation
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Rev. Date
05 SEP 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
19 JUN 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
12 APR 17
22 MAR 17
22 MAR 17
22 MAR 17
05 SEP 17
05 SEP 17
19 JUN 17
22 MAR 17
22 MAR 17
05 SEP 17
05 SEP 17
19 JUN 17
19 JUN 17
19 JUN 17
22 MAR 17
05 SEP 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
05 SEP 17
19 JUN 17
22 MAR 17
24 JAN 17
05 SEP 17
Continued on the following page
PLP-LESS P 9/14
17 OCT 17
PRELIMINARY PAGES
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
Localization
PRO-NOR-SOP-05
PRO-NOR-SOP-06
PRO-NOR-SOP-07
PRO-NOR-SOP-08
PRO-NOR-SOP-09
PRO-NOR-SOP-10
PRO-NOR-SOP-11
PRO-NOR-SOP-12
PRO-NOR-SOP-13
PRO-NOR-SOP-14
PRO-NOR-SOP-15
PRO-NOR-SOP-16
PRO-NOR-SOP-17
PRO-NOR-SOP-18-A
PRO-NOR-SOP-18-B
PRO-NOR-SOP-18-C
PRO-NOR-SOP-19
PRO-NOR-SOP-20
PRO-NOR-SOP-21
PRO-NOR-SOP-22
PRO-NOR-SOP-23
PRO-NOR-SOP-90
PRO-NOR-SUP-SUP
PRO-NOR-SUP-ADVWXR
PRO-NOR-SUP-COM
PRO-NOR-SUP-ENG
PRO-NOR-SUP-FUEL
PRO-NOR-SUP-LG-LG_DN
PRO-NOR-SUP-LG-LG
PRO-NOR-SUP-MISC-D
PRO-NOR-SUP-MISC-A
PRO-NOR-SUP-MISC-C
PRO-NOR-SUP-NAV
PRO-NOR-SRP-01-05
PRO-NOR-SRP-01-10
PRO-NOR-SRP-01-15
PRO-NOR-SRP-01-20
PRO-NOR-SRP-01-30
PRO-NOR-SRP-01-40
Subsection Title
Exterior Walkaround
Cockpit Preparation
Before Pushback or Start
Engine Start
After Start
Taxi
Before Takeoff
Takeoff
After Takeoff
Climb
Cruise
Descent Preparation
Descent
Approach General
Aircraft Configuration Management
Aircraft Guidance Management
Landing
Go-Around
After Landing
Parking
Securing the Aircraft
Standard Callouts
Supplementary Procedures Menu
Adverse Weather
Communication
Engines
Fuel
Flight with Landing Gear Down
Operation with Nosewheel Steering Offset
Pushback with Power Push Unit
Hight Altitude Airport Operations
Operations at QNH Above 1050 hPa
Navigation
Introduction
Cockpit Preparation
Before Pushback or Start
Taxi
Takeoff
Climb
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Rev. Date
05 SEP 17
12 APR 17
19 JUN 17
05 SEP 17
22 MAR 17
05 SEP 17
22 MAR 17
19 JUN 17
22 MAR 17
22 MAR 17
22 MAR 17
19 JUN 17
05 SEP 17
22 MAR 17
22 MAR 17
05 SEP 17
05 SEP 17
24 JAN 17
05 SEP 17
05 SEP 17
19 JUN 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
19 JUN 17
05 SEP 17
05 SEP 17
05 SEP 17
22 MAR 17
22 MAR 17
22 MAR 17
22 MAR 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
24 JAN 17
Continued on the following page
PLP-LESS P 10/14
17 OCT 17
PRELIMINARY PAGES
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
R
Continued from the previous page
Localization
PRO-NOR-SRP-01-50
PRO-NOR-SRP-01-60
PRO-NOR-SRP-01-70
PRO-NOR-SRP-01-80
PRO-SPO-20
PRO-SPO-40-10
PRO-SPO-40-20
PRO-SPO-40-30
PRO-SPO-40-40
PRO-SPO-40-50
PRO-SPO-40-60
PRO-SPO-45
PRO-SPO-50
PRO-SPO-51
PRO-SPO-60
PRO-SPO-85
LIM-PLP-LETDU
LIM-INT
LIM-AG-F_CTL
LIM-AG-OPS
LIM-AG-SPD
LIM-AG-WGHT
LIM-AIR
LIM-AFS-10
LIM-AFS-20
LIM-APU
LIM-COM
LIM-ENG
LIM-F_CTL
LIM-FUEL
LIM-ICE_RAIN
LIM-LG
LIM-NAV
LIM-OXY
LIM-SURV
OEB-PLP-LETDU
OEB-PLP-LEOEB
PER-PLP-LETDU
PER-LOD-GEN
Subsection Title
Rev. Date
Cruise
22 MAR 17
Descent
24 JAN 17
Approach
22 MAR 17
Go-Around
24 JAN 17
Flight Without Cabin Pressurization
22 MAR 17
General
24 JAN 17
Operational Limitations
22 MAR 17
Dispatch Consideration
24 JAN 17
Diversion During Extended Range Operations
22 MAR 17
Procedures
05 SEP 17
Performance
22 MAR 17
Engine Intermix Operations
19 JUN 17
Reduced Vertical Separation Minimum - RVSM
22 MAR 17
Required Navigation Performance (RNP)
05 SEP 17
Operations on Narrow Runways
22 MAR 17
ILS PRM Approach
22 MAR 17
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
22 MAR 17
Introduction
05 SEP 17
Flight Maneuvering Load Acceleration Limits
22 MAR 17
Operational Parameters
05 SEP 17
Speeds
22 MAR 17
Weights
22 MAR 17
Air Bleed/Cond/Press/Vent
22 MAR 17
General
05 SEP 17
Automatic Approach, Landing and Rollout
22 MAR 17
Auxiliary Power Unit
05 SEP 17
Communication
19 JUN 17
Engines
22 MAR 17
Flight Controls
22 MAR 17
Fuel
22 MAR 17
Ice and Rain Protection
22 MAR 17
Landing Gear
19 JUN 17
Navigation
22 MAR 17
Oxygen
22 MAR 17
Surveillance
22 MAR 17
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
17 OCT 17
LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETIN
17 OCT 17
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
17 OCT 17
GENERAL
24 JAN 17
Continued on the following page
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FCOM
PLP-LESS P 11/14
17 OCT 17
PRELIMINARY PAGES
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
Localization
PER-LOD-CGO
PER-LOD-FUL
PER-LOD-WBA-LTS
PER-LOD-WBA-FIT-10
PER-OPD-GEN
PER-OPD-CON-AEO
PER-OPD-CON-OEI
PER-THR-GEN
PER-THR-MTO
PER-THR-MGA
PER-THR-FLX
PER-THR-MCT
PER-THR-MCL
PER-THR-MCR
PER-TOF-THR-FLX-10
PER-TOF-THR-FLX-20
PER-TOF-THR-FLX-30
PER-TOF-THR-FLX-40
PER-TOF-TOC-05
PER-TOF-TOC-10-10
PER-TOF-TOC-10-20
PER-TOF-TOC-10-30
PER-TOF-TOC-12-10
PER-TOF-TOC-12-30
PER-TOF-TOC-12-40
PER-TOF-TOC-12-50
PER-TOF-TOC-14-10
PER-TOF-TOC-14-20
PER-TOF-TOC-14-25
PER-TOF-TOC-14-30
PER-TOF-TOC-16-10
PER-TOF-TOC-16-20
PER-TOF-TOC-16-30
PER-TOF-TOC-18-10
PER-TOF-TOC-18-20
PER-TOF-TOC-18-30
PER-TOF-TOC-18-40
Subsection Title
Rev. Date
CARGO LOADING
22 MAR 17
FUEL
22 MAR 17
LOAD AND TRIM SHEET
24 JAN 17
FUEL INDEX TABLE
22 MAR 17
GENERAL
24 JAN 17
ALL ENGINES OPERATIVE
24 JAN 17
ONE ENGINE INOPERATIVE
24 JAN 17
GENERAL
24 JAN 17
MAXIMUM TAKEOFF
24 JAN 17
MAXIMUM GO AROUND
24 JAN 17
FLEXIBLE TAKEOFF
24 JAN 17
MAXIMUM CONTINUOUS
24 JAN 17
MAXIMUM CLIMB
24 JAN 17
MAXIMUM CRUISE
24 JAN 17
DEFINITION OF FLEXIBLE TAKEOFF
24 JAN 17
USE OF FLEXIBLE TAKEOFF
24 JAN 17
REQUIREMENTS
24 JAN 17
RECOMMENDATION
24 JAN 17
INTRODUCTION
24 JAN 17
TAKEOFF PERFORMANCE
24 JAN 17
TAKEOFF CHART DESCRIPTION
24 JAN 17
ADDITIONAL INFORMATION
24 JAN 17
DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND
24 JAN 17
SPEEDS
EXTRAPOLATION
24 JAN 17
MAXIMUM STRUCTURAL TAKEOFF WEIGHT
24 JAN 17
SUMMARY
24 JAN 17
DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE
24 JAN 17
AND SPEEDS
FLEXIBLE TAKEOFF NOT POSSIBLE
24 JAN 17
FLEXIBLE TAKEOFF POSSIBLE BUT NOT USED
24 JAN 17
SUMMARY
24 JAN 17
TAKEOFF PERFORMANCE
24 JAN 17
TAKEOFF CHART DESCRIPTION
24 JAN 17
ADDITIONAL INFORMATION
24 JAN 17
DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND
24 JAN 17
SPEEDS
EXTRAPOLATION
24 JAN 17
MAXIMUM STRUCTURAL TAKEOFF WEIGHT
24 JAN 17
SUMMARY
24 JAN 17
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PLP-LESS P 12/14
17 OCT 17
PRELIMINARY PAGES
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
Localization
PER-TOF-TOC-20-10
PER-TOF-TOC-20-20
PER-TOF-TOC-20-30
PER-TOF-TOD-24
PER-TOF-TOD-25-10
PER-TOF-TOD-25-20
PER-TOF-CTA-10
PER-TOF-CTA-20
PER-TOF-CTA-30
PER-TOF-CTA-40-10
PER-TOF-CTA-40-20
PER-TOF-CTA-40-30
PER-TOF-CTA-40-40
PER-FPL-GEN-MFR
PER-FPL-GEN-FPL
PER-FPL-FLP-QFP-10
PER-FPL-FLP-QFP-20
PER-FPL-FLP-QFP-30
PER-FPL-FLP-QFP-40
PER-FPL-FLP-QFP-50
PER-FPL-FLP-ALN-20
PER-CLB-GEN
PER-CLB-CLT
PER-CRZ-ALT-10
PER-CRZ-ALT-20
PER-CRZ-CRT-10
PER-CRZ-CRT-20
PER-CRZ-CRT-30
PER-CRZ-ICQ-10
PER-CRZ-ICQ-20
PER-HLD-GEN
PER-HLD-HLD
PER-DES-GEN
PER-DES-STD
PER-DES-EMG
PER-GOA-GEN
PER-GOA-ACG-NOR
Subsection Title
Rev. Date
DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE
24 JAN 17
AND SPEEDS
FLEXIBLE TAKEOFF NOT POSSIBLE
24 JAN 17
SUMMARY
24 JAN 17
QNH/BLEEDS CORRECTION
24 JAN 17
SPEEDS LIMITED BY VMCG/VMCA
24 JAN 17
V2 LIMITED BY VMU/VMCA
24 JAN 17
GENERAL
24 JAN 17
DEFINITIONS
24 JAN 17
OPERATIONAL CONDITIONS
24 JAN 17
TAKEOFF PERFORMANCE
24 JAN 17
TAKEOFF FROM A WET RUNWAY
24 JAN 17
TAKEOFF FROM A CONTAMINATED RUNWAY
22 MAR 17
EXAMPLE
24 JAN 17
MINIMUM RECOMMENDED FUEL REQUIREMENTS
24 JAN 17
FLIGHT PLAN
24 JAN 17
INTRODUCTION
24 JAN 17
CORRECTION FOR DEVIATION FROM REFERENCE LANDING
24 JAN 17
WEIGHT
EXAMPLE
05 SEP 17
FLIGHT PLANNING AT A GIVEN MACH NUMBER
24 JAN 17
FLIGHT PLANNING AT LONG RANGE SPEED
24 JAN 17
ALL ENGINES OPERATIVE
24 JAN 17
GENERAL
24 JAN 17
CLIMB TABLES
24 JAN 17
OPTIMUM AND MAXIMUM ALTITUDES
22 MAR 17
WIND ALTITUDE TRADE FOR CONSTANT SPECIFIC RANGE
24 JAN 17
GENERAL
24 JAN 17
CRUISE AT M.78
24 JAN 17
CRUISE AT LONG RANGE
24 JAN 17
GENERAL
22 MAR 17
EXAMPLE
22 MAR 17
GENERAL
24 JAN 17
HOLDING TABLES
24 JAN 17
GENERAL
24 JAN 17
STANDARD
24 JAN 17
EMERGENCY
22 MAR 17
GENERAL
22 MAR 17
NORMAL
24 JAN 17
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PLP-LESS P 13/14
17 OCT 17
PRELIMINARY PAGES
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
Localization
PER-GOA-ACG-CAT
PER-LDG-GEN
PER-LDG-CTA-10
PER-LDG-CTA-20
PER-LDG-DIS-MAT
PER-LDG-DIS-RLD
PER-LDG-DIS-RLA
PER-OEI-GEN
PER-OEI-ALT-10
PER-OEI-CRT-10
PER-OEI-CRT-20
PER-OEI-ICQ-10
PER-OEI-ICQ-20
PER-OEI-HLD
PER-OEI-DES-10
PER-OEI-DES-15
PER-OEI-DES-20
PER-OEI-DES-30
Subsection Title
CAT II
GENERAL
GENERAL
DEFINITIONS
Runway Condition Assessment Matrix for Landing
REQUIRED LANDING DISTANCES / MANUAL LANDING
REQUIRED LANDING DISTANCES
GENERAL
CEILINGS
STANDARD AND OBSTACLE STRATEGIES
FIXED SPEED STRATEGIES
STANDARD STRATEGIES
FIXED SPEED STRATEGIES
HOLDING
STANDARD STRATEGY
OBSTACLE STRATEGY
FIXED SPEED STRATEGIES
DESCENT TO LANDING
Rev. Date
24 JAN 17
19 JUN 17
24 JAN 17
05 SEP 17
22 MAR 17
24 JAN 17
24 JAN 17
22 MAR 17
22 MAR 17
24 JAN 17
24 JAN 17
22 MAR 17
22 MAR 17
24 JAN 17
24 JAN 17
22 MAR 17
24 JAN 17
24 JAN 17
(1) Evolution code : N=New, R=Revised, E=Effectivity, M=Moved
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PLP-LESS P 14/14
17 OCT 17
PRELIMINARY PAGES
AIRCRAFT ALLOCATION TABLE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
This table gives, for each delivered aircraft, the cross reference between:
-
The Manufacturing Serial Number (MSN).
The Fleet Serial Number (FSN) of the aircraft as known by AIRBUS S.A.S.
The registration number of the aircraft as known by AIRBUS S.A.S.
The aircraft model.
(1)
M
MSN
FSN
3408
Registration Number
Model
HC-CRU
320-214
(1) Evolution code : N=New, R=Revised
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PLP-AAT P 1/2
24 JAN 17
PRELIMINARY PAGES
AIRCRAFT ALLOCATION TABLE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PLP-AAT P 2/2
24 JAN 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
MODIFICATION
J0006
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
J0012
FUEL SYSTEM - ADDITIONAL TREATMENT OF
CENTRE TANK STRUCTURE AND INSTALLATION OF
CENTRE TANK SYSTEM
20 AUG 10
Applicable to: ALL
J0022
NAVIGATION LIGHTS SYSTEM - INSTALLATION OF A
SECOND NAVIGATION LIGHT SYSTEM
20 AUG 10
Applicable to: ALL
J0071
INSTALLATION OF A FUEL QUANTITY SELECTOR IN
THE FLIGHT COMPARTMENT
20 AUG 10
WING STRUCTURE-INTRODUCTION OF A WING TIP
INCORPORATING A TIP FENCE FOR 72T MTOW A/C
20 AUG 10
FUEL SYSTEM-TO IMPROVE LOW LEVEL WARNING
20 AUG 10
Applicable to: ALL
J1255
WING-TO DELETE L/E VENTILATION SYSTEM
(PICCOLO TUBE)
20 AUG 10
Applicable to: ALL
J1334
FUEL - TANK LEVEL SENSING - CHANGE TO LOW
PRESSURE WARNING
20 AUG 10
Applicable to: ALL
J1617
LANDING GEAR-MLG-LGCIU-INTRODUCTION OF
A NEW STANDARD FOR IMPROVED PROXIMITY
SENSOR FAULT MONITORING FUNCTION
20 AUG 10
Applicable to: ALL
J2190
FLIGHT CONTROLS - GENERAL - DELETE LAF
FEATURE FROM A320 DEFINITION (PRODUCTION
SOLUTION)
20 AUG 10
Applicable to: ALL
J2257
FUEL - MAIN FUEL PUMPS SYSTEMS - CENTRE
TANK PUMPS AUTO FEED FAULT.ADAPT PUMP
CONTROL LATCH FOR FLIGHT DECK REFUEL
CABABILITY
20 AUG 10
Applicable to: ALL
J2360
FUEL - MANUAL MAGNETIC INDICATORS - ATTITUDE
MONITOR DELETION
20 AUG 10
FUEL - QUANTITY INDICATION - INTRODUCE FUEL
LEAK DETECTION ASSOCIATED WITH FQIC - 13 - 9
Applicable to: ALL
J0664
Applicable to: ALL
J0689
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 1/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
J2361
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
J2527
FUEL - QUANTITY INDICATION - REMOVAL OF FUEL
LEAK DETECTION FUNCTION ASSOCIATED WITH
THE FQIC 13 - 9
20 AUG 10
Applicable to: ALL
J2662
FUEL - QUANTITY INDICATING - INTRODUCE NEW
STANDARD OF FUEL QTY INDICATING COMPUTER
13-10
15 FEB 13
Applicable to: ALL
J2816
FUEL - QUANTITY INDICATING - INTRODUCE NEW
STANDARD OF FQIC (P/N SIC5059 14-20)
07 APR 11
Applicable to: ALL
K0024
WING - FIXED PARTITION - INTRODUCED A
STANDARD OF BOX WITHOUT DRY BAY
20 AUG 10
Applicable to: ALL
K0026
INSTALLATION OF ADDITIONAL CARGO DOOR
(BULK DOOR)
20 AUG 10
Applicable to: ALL
K0035
LIGHTS - LOGOLIGHTS - INSTALLATION OF
LOGOLIGHTS SYSTEM
20 AUG 10
Applicable to: ALL
K0036
FIRE PROTECTION - FWD LOWER HOLD INSTALLATION OF SMOKE DETECTION SYSTEM
20 AUG 10
Applicable to: ALL
K0037
FIRE PROTECTION - AFT LOWER HOLD INSTALLATION OF SMOKE DETECTION SYSTEM
20 AUG 10
FIRE PROTECTION - FWD AND AFT LOWER
HOLD INSTALLATION OF A SINGLE SHOT FIRE
EXTINGUISHING SYSTEM
20 AUG 10
INSTALLATION OF AN AIDS
20 AUG 10
LIGHTS - INSTALLATION OF STROBE LIGHTS
SYNCHRONISED MODE
20 AUG 10
AIR CONDITIONING - VENTILATION SYSTEM FOR
FWD CARGO COMPARTMENT
20 AUG 10
WATER WASTE-INSTALL VACUUM TOILET SYSTEM
Applicable to: ALL
K0052
Applicable to: ALL
K0064
Applicable to: ALL
K0066
Applicable to: ALL
K0082
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 2/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
K0151
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
K10003
EQUIPMENT FURNISHINGS ESCAPE FACILITIES
INSTALL SLIDE RAFTS (AIRCRUISERS)
07 APR 11
Applicable to: ALL
K10009
AIRBORNE AUXILIARY POWER - CONTROL AND
MONITORING INTRODUCE SOFTWARE VERSION
06.00.000
20 AUG 10
Applicable to: ALL
K1014
EQUIPMENT/FURNISHINGS - CURTAINS AND
PARTITIONS INTRODUCE IMPROVED STRIKES FOR
COCKPIT DOOR
20 AUG 10
Applicable to: ALL
K10359
WATER/WASTE-RELOCATION OF POT.WATER TANK
FROM SECTION 18 TO SECTION 15 AND REDESIGN
OF POT.WATERSYSTEM
20 AUG 10
Applicable to: ALL
K10463
LIGHTS - EMERGENCY LIGHTING - DEFINE FLOOR
MOUNTED LUFTHANSA TECHNIK 900 SERIES
EEPMS
25 NOV 11
Applicable to: ALL
K10494
AIR CONDITIONING PACK TEMPERATURE CONTROL
INTRODUCE IMPROVED AIR CONDITIONING
CONTROLLER P/N 1803B0000-02
20 AUG 10
Applicable to: ALL
K11047
AIRBORNE AUXILIARY POWER - CHANGE
STANDARD APU HONEYWELL GTCP36-300 TO APIC
APS3200
20 AUG 10
Applicable to: ALL
K1119
COMMUNICATION - ANTI HIJACK CAMERA
MONITORING - INSTALL COCKPIT DOOR
SURVEILLANCE SYSTEM DISPLAYEDON SD
20 AUG 10
Applicable to: ALL
K11694
EQUIPMENT FURNISHINGS-C.C-REARRANGE
COMPARTMENT 4 INTO TWO ZONES
07 APR 11
Applicable to: ALL
K1420
EQUIPMENT/FURNISHINGS-MISCELLANEOUS
EMERGENCY EQUIPMENT-INSTALLATION OF
ELT(406AFN) WITH RCP IN COCKPIT AND NAV
PROVISIONS-HONEYWELL
20 AUG 10
DOORS-FWD/AFT CARGO DOOR-INTRODUCTION OF
LOCKING INDICATION
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 3/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
K1806
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
K2335
AIR CONDITIONING SYSTEM POWER SUPPLY MODIFY POWER TO FLOW CONTROL VALVE
20 AUG 10
Applicable to: ALL
K2393
LAVATORY SMOKE DETECTION - IMPROVEMENT OF
SMOKE DETECTION
20 AUG 10
Applicable to: ALL
K2450
AIR COND.-CABIN PRESSURE CONTROL-IMPROVE
CONTROLLER TO ENABLE USE OF EXTERNAL
MODE
20 OCT 11
Applicable to: ALL
K2938
AUXILIARY POWER UNIT - INTRODUCTION OF APIC
APS-3000
20 AUG 10
Applicable to: ALL
K2962
DOORS - C.C.DOOR HYDRAULIC SYSTEM INTRODUCE MODIFIED ELECTRICAL (MANUAL)
SELECTOR VALVE -
20 AUG 10
Applicable to: ALL
K3118
HYDRAULIC POWER - MAIN BLUE HYDRAULIC
POWER - IMPROVE MAINTENACE STATUS OF BLUE
HYDRAULIC RESERVOIR -
20 AUG 10
Applicable to: ALL
K3279
AUXILIARY POWER UNIT - CONTROL AND
MONITORING - INTRODUCTION OF NEW ECB P/N
304817-1
20 AUG 10
Applicable to: ALL
K3471
AUXILIARY POWER UNIT - CONTROL AND
MONITORING - MODIFIED WIRE HARNESSES TO
NEW ECB
20 AUG 10
Applicable to: ALL
K3599
GENERAL - INCREASE DESIGN WEIGHT TO 61T
MZFW
20 AUG 10
Applicable to: ALL
K3901
AIR CONDITIONING - COCKPIT AND CABIN
TEMPERATURE CONTROL - INTRODUCE IMPROVED
ZONE TEMPERATURE CONTROLLER -03
20 AUG 10
COMMUNICATIONS - CIDS - MODIFICATION OF
DIRECTOR POWER SUPPLY PRINCIPLE
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 4/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
K4574
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
K4725
AIR CONDITIONING-FLOW CONTROL AND
INDICATING- INTRODUCE IMPROVED AIR
CONDITIONING PACKAGE FOR FLOW CONTROL
06 JUL 16
Applicable to: ALL
K4726
DOORS - CARGO COMPARTMENT DOOR FWD AND
AFT - MODIFY CARGO DOORS
20 AUG 10
WATER/WASTE-TOILET SYSTEM-INTRODUCE
IMPROVED TOILET ASSY
20 AUG 10
LIGHTS - INTRODUCTION OF A COMMON EPSU
20 AUG 10
Applicable to: ALL
K4913
AIR CONDITIONING-AIR COOLING
SYSTEM-INTRODUCE AN IMPROVED RAM OUTLET
(RAO)
20 AUG 10
Applicable to: ALL
K5157
HYDRAULIC POWER - AUXILIARY HYDRAULIC
POWER - INSTALL A319 RAM AIR TURBINE ON A320
20 AUG 10
Applicable to: ALL
K5213
OXYGEN-PASSENGER OXYGEN-INTRODUCE
IMPROVED OPTIONAL CHEMICAL OXYGEN
CONTAINER (22 MIN) TO REPLACE "HIGH FLOW"
CONTAINER
20 AUG 10
Applicable to: ALL
K5446
AIR CONDITIONING - PACK TEMPERATURE
CONTROL - INTRODUCE IMPROVED PACK
TEMPERATURE CONTROLLER
20 AUG 10
Applicable to: ALL
K5549
INDICATING/RECORDING SYSTEMS - INSTALLATION
OF A COMBINED FDIU/DMU
20 AUG 10
Applicable to: ALL
K5801
OXYGEN - PASSENGER OXYGEN - INTRODUCE
CHEMICAL OXYGEN CONTAINER (15MIN) WITH
IMPROVED ACTUATOR (VENDOR PURITAN)
20 AUG 10
AIR CONDITIONING-PRESSURE CONTROL AND
MONITORING- INTRODUCE MODIFIED PRESSURE
CONTROLLER P/N 9022-15702-10
Applicable to: ALL
K4787
Applicable to: ALL
K4793
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 5/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
K6156
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
K6164
AIR CONDITIONING-PACK TEMPERATURE
CONTROL- INTRODUCE MODIFIED PACK
TEMPERATURE CONTROLLER
20 AUG 10
Applicable to: ALL
K6318
GENERAL-INCREASE A320 DESIGN WEIGHTS TO
77,0T MTOW; 66,0T MLW AND 62.5T MZFW
20 OCT 11
Applicable to: ALL
K6443
APU-CONTROL AND MONITORING-INTRODUCE APIC
ECB SOFTWARE VERSION 5
20 AUG 10
Applicable to: ALL
K6936
AIR CONDITIONING_AIR COOLING INSTALL A NEW
ECS
20 AUG 10
Applicable to: ALL
K7072
AUXILIARY POWER UNIT (APU)-GENERALINCREASE OPERATION ENVELOPE TO 39800 FT.
FOR GTCP36-300
20 AUG 10
Applicable to: ALL
K7755
LIGHTS-EMERGENCY LIGHTING- EPSU LOAD
DISTRIBUTION IMPROVEMENT
20 AUG 10
Applicable to: ALL
K7790
EQUIPMENT/FURNISHINGS PAX COMPARTMENT
INTRODUCE A MODIFIED INTRUSION AND
PENETRATION RESISTANCE COCKPIT DOOR
20 AUG 10
Applicable to: ALL
K8400
DOORS PASSENGER COMPARTMENT FIXED
PARTITIONS INTERIOR DOOR-ELECTRICAL
COCKPIT DOOR RELEASE SYSTEM
20 AUG 10
Applicable to: ALL
K8734
COMMUNICATIONS CABIN INTERCOMMUNICATION
MODIFY CABIN INTERCOMMUNICATION DATA
SYSTEM ON A319
25 NOV 11
Applicable to: ALL
K8905
AIR CONDITIONING - AIR COOLING ADAPT A318 ECS
TO A320
20 AUG 10
EQUIPMENT/FURNISHINGS -CURTAINS AND PAR
INSTALL A DEADBOLT FOR THE REINFORCED
COCKPIT DOOR
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 6/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
K9458
Linked SB
Incorp. Date
Title
25 NOV 11
Applicable to: ALL
K9473
AIR CONDITIONING - PACK TEMPERATURE
CONTROL IMPROVED AIR CONDITIONING SYSTEM
CONTROLLER P/N 1803B0000-01
20 AUG 10
Applicable to: ALL
K9877
AIR CONDITIONING-PRESSURE CONTROL AND
MONITORING-INTRODUCE RESIDUAL PRESSURE
CONTROL UNIT (RPCU)
20 AUG 10
Applicable to: ALL
P0033
EQUIPMENT / FURNISHINGS - CURTAINS AND
PARTITIONS - MODIFY DEADBOLT FOR REFORCED
COCKPIT DOOR
07 APR 11
COMMUNICATIONS - HF1 SYSTEM PROVISION FOR
HF1 SYSTEM
07 APR 11
SINGLE HF SYSTEM
20 AUG 10
4TH OCCUPANT SEAT
20 AUG 10
ALTERNATIVE FLIGHT CREW OXYGEN BOTTLE
(77.1CU/FT) IN COMPOSITE MATERIAL FOR FIXED
SYSTEM
20 AUG 10
COMMUNICATIONS - INSTALLATION OF A 3RD RMP
20 AUG 10
DESIGN WEIGHT-MTOW 72T-STRUCTURAL
REINFORCEMENT
07 APR 11
COMMUNICATIONS-SINGLE HF SYSTEM
INSTALLATION
07 APR 11
NAVIGATION-REPLACE EXISTING VOR DDRMI WITH
A COMBINED VOR ADF DDRMI COLLINS
20 AUG 10
COMMUNICATIONS-HOT MIKE RECORDING
07 APR 11
ENGINE FUEL AND CONTROL FADEC SYSTEM
INTRODUCE NEW "5BO" ECU SOFTWARE STD ON
CFM56-5B ENGINES - CNF CFM 109B -
Applicable to: ALL
P0034
Applicable to: ALL
P0040
Applicable to: ALL
P0091
Applicable to: ALL
P0143
Applicable to: ALL
P0147
Applicable to: ALL
P0197
Applicable to: ALL
P0287
Applicable to: ALL
P0415
Applicable to: ALL
P10022
23-1365 15
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 7/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P10098
Linked SB
24-1120 04
Incorp. Date
Title
20 AUG 10
ELECTRICAL POWER AC ESSENTIAL GENERATION
SWITCHING INSTALL AUTO SWITCHING SYSTEM
FOR AC&DC ESS BUS.
20 AUG 10
NAVIGATION - RADIO MAGNETIC INFORMATION
SWITCHING AND INDICATING : RE-INSTALL THALES
DDRMI VOR/DME INDICATORS (ANTI-MOD 33503)
22-1289 01
07 APR 11
AUTO-FLIGHT - GENERAL - REMOVE AFM
LIMITATION ON NON PRECISION APPROACHES
WITH ONE ENGINE OUT
31-1334 04
31-1414 03
20 AUG 10
Applicable to: ALL
P10439
INDICATING/RECORDING SYSTEMS FLIGHT
WARNING COMPUTER (FWC) INSTALL FWC
STANDARD H2-F5
22-1248 01
20 AUG 10
Applicable to: ALL
P10443
AUTO-FLIGHT FMGC INSTALL FMGC HNWL STD
P1C12 ON CFM A/C
27-1182 04
07 APR 11
Applicable to: ALL
P10686
FLIGHT CONTROL - ELAC SYSTEM - INTRODUCE
ELAC "L93" SOFTWARE STANDARD
22-1266 03
07 APR 11
Applicable to: ALL
P10762
AUTO-FLIGHT - FMGC INSTALL HONEYWELL
PERFORMANCE DATABASE RELEASE 1A
(PS4087592-901)
22-1269 05
20 AUG 10
Applicable to: ALL
P11325
AUTO FLIGHT - FMGC INSTALL FMGC HWL H2C12
(RELEASE 1A) ON CFM A/C
73-1095 02
18 MAR 15
Applicable to: ALL
P11473
ENGINE FUEL AND CONTROL - FADEC SYSTEM
INTRODUCE ECU SOFTWARE STANDARD "5BR" ON
CFM56-5B ENGINES
22-1315 05
22 MAR 16
Applicable to: ALL
P11856
AUTO FLIGHT - FLIGHT MANAGEMENT SYSTEM
(FMS) ACTIVE BARO RADIO SETTING FUNCTION
22-1315 05
07 APR 11
AUTO - FLIGHT FMGC: ACTIVATE NO AP
DISCONNECTION BELOW MDA/MDH UNTIL MISSED
APPROACH POINT
Applicable to: ALL
P10267
Applicable to: ALL
P10321
Applicable to: ALL
P10383
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 8/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P1237
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
P1302
INDICATING RECORDING SYSTEM-TOGGLE
SWITCHES RELOCATED IN 25VU ON OVERHEAD
PANEL
20 AUG 10
Applicable to: ALL
P1312
LANDING GEAR-POST EIS STANDARD 4 OF BSCU
EQUIPMENT
07 APR 11
LIGHTS-COCKPIT-INTEGRALLY LIGHTED PLACARD
25VU,ANTI ICE PART MODIFIED
20 AUG 10
ELECTRICAL GENERATION-BCL'S CHANGE
20 AUG 10
NAVIGATION - ATC MODE "S" - ACTIVATION OF
SELECTIVE INTERROGATION FUNCTION
20 AUG 10
ELECTRICAL POWER-"BAT OFF"INDICATOR LIGHT
POWER SOURCE MODIFIED
20 AUG 10
NAVIGATION - MODIFY GPWC WARNINGS
20 AUG 10
Applicable to: ALL
P1752
AIR CONDITIONING-AVIONICS VENTILATION ADD A
NON RETURN VALVE AT AIR INLET
20 AUG 10
Applicable to: ALL
P1850
HYDRAULICS-MODIFICATION OF ELECTRICAL
ROUTING OF GREEN LEAKAGE MEASUREMENT
ELECTROVALVE CONTROL
20 AUG 10
Applicable to: ALL
P1873
FLIGHT CONTROLS-ELAC SYSTEM-EFCS ELAC
-SOFTWARE L62
20 AUG 10
AIR CONDITIONING-ESSENTIAL DC SUPPLY FOR
FORWARD CARGO COMPARTMENT SHUT-OFF
VALVES
20 AUG 10
FLIGHT CONTROLS-FCDC L 40
20 AUG 10
ENGINES FUEL AND CONTROL-EIU FOR CFMI
POWERPLANT (SOFTWARE VERSION 11)
20 AUG 10
COMMUNICATIONS-INSTALL HF1 IN EMERGENCY
CONFIG. (ETOPS)
Applicable to: ALL
P1390
Applicable to: ALL
P1450
Applicable to: ALL
P1485
Applicable to: ALL
P1631
Applicable to: ALL
P1669
Applicable to: ALL
P1883
Applicable to: ALL
P1906
Applicable to: ALL
P1970
23-1365 15
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 9/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P2040
Applicable to: ALL
P2196
Linked SB
Incorp. Date
Title
20 AUG 10
OXYGENE-COCKPIT-MODIFY LP VALVE
20 AUG 10
BATCH OF MINOR IMPROVEMENTS OF SERIES A/C
DESIGN (AS ZONE) FROM A/C N 268
20 AUG 10
FIRE PROTECTION - REPLACE ENGINE/APU FIRE
PANEL
20 AUG 10
NAVIGATION - TCAS II COMPLETE PROVISIONS
20 AUG 10
NAVIGATION - INSTALLATION OF GPWC MARK V
WITH INTERFACE WITH CFDS
20 AUG 10
ENGINE FUEL AND CONTROL - CFM 56
POWERPLANT EIU VERSION 12
20 AUG 10
AUTOFLIGHT - ACTIVATE WINDSHEAR FUNCTION
20 AUG 10
COCKPIT - INSTALL A340 TYPE PILOT SEATS
20 AUG 10
Applicable to: ALL
P2547
INDICATING/RECORDING SYSTEMS INSTRUMENTS - DEFINE SDAC STANDARD FOR
A321 COF A
07 APR 11
Applicable to: ALL
P2588
INDICATING/RECORDING SYSTEMS INSTRUMENTS - DEFINE DMC STANDARD FOR A321
COF A
20 AUG 10
Applicable to: ALL
P2590
OXYGEN - COCKPIT - REPLACE BASIC AIR LIQUIDE
PBE BY DRAEGER
20 AUG 10
Applicable to: ALL
P2842
NAVIGATION - INSTALL A TCAS II COLLISION
AVOIDANCE SYSTEM
06 JUL 16
Applicable to: ALL
P2879
GENERAL - EXTEND FLIGHT ENVELOPE FOR IAE
V2500
20 AUG 10
INDICATING RECORDING SYSTEM - SDAC - DEFINE
A PIN PROGRAM FOR FWD C.C VENTILATION
Applicable to: ALL
P2205
Applicable to: ALL
P2218
Applicable to: ALL
P2223
Applicable to: ALL
P2294
Applicable to: ALL
P2316
Applicable to: ALL
P2493
Applicable to: ALL
P2546
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 10/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P2960
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
P2963
CERTIFICATION DOCUMENTS - GENERAL CERTIFICATION FOR TAKING OFF WITH 15 KNOT
TAILWING
20 AUG 10
Applicable to: ALL
P3004
AIR CONDITIONING - IMPROVE CABIN
PRESSURIZATION CONTROL ON 25VU -
20 AUG 10
LIGHTS-COCKPIT LIGHTING-IMPROVE COCKPIT
LIGHTING
20 AUG 10
FMS - FMS CROSS LOAD
20 AUG 10
NAVIGATION -ADAPT SHELVES FOR INSTALLATION
OF 4MCUADIRS -
20 AUG 10
AUTO FLIGHT - FCU-CPIP1 STANDARD
20 AUG 10
ENGINE FUEL AND CONTROL - CFM 56 - EIU
VERSION 13
20 AUG 10
GENERAL - OPERATION FROM HIGH ALTITUDE
AIRPORTS (CFM ENGINES) (PRESSURE ALTITUDE
LIMIT 9200 FT)
20 AUG 10
AUTOFLIGHT - FCU - CPIP 2 STANDARD M10
20 AUG 10
AUTO FLIGHT - FMGC - A320/A321 STANDARD WITH
SOFTWARE OPTIONS + 400 KILOWORDS DATA
BASE OPTION + ACARS HARDWARE PROVISION (B1
CFM VERSION)
20 AUG 10
ICE PROTECTION - ICING INDICATOR ILLUMINATION
20 AUG 10
INDICATING/RECORDING SYSTEMS - GENERAL DEFINE PIN PROGRAMMING FOR STD VERSIONS
22 MAR 16
A320/321 ENERGY MANAGEMENT FUNCTIONS ACTIVATION BY PIN PROGRAMMING FOR IAE AND
CFM ENGINES
Applicable to: ALL
P3011
Applicable to: ALL
P3044
Applicable to: ALL
P3102
Applicable to: ALL
P3105
Applicable to: ALL
P3197
Applicable to: ALL
P3202
Applicable to: ALL
P3204
Applicable to: ALL
P3365
Applicable to: ALL
P3379
Applicable to: ALL
P3420
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 11/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P3510
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
P3511
NAVIGATION - ADIRS - IMPROVED STANDARD OF
A320 ADIRU
20 AUG 10
Applicable to: ALL
P3524
AUTO FLIGHT - FLIGHT AUGMENTATION - AFS
COMPUTER A320/A321 FAC CFM/IAE
20 AUG 10
Applicable to: ALL
P3588
ELECTRICAL GENERATION - APU GENERATOR NEW
STANDARD
20 AUG 10
Applicable to: ALL
P3594
LANDING GEAR - A320/A321 TWIN WHEELS BSCU
STANDARD 7 (70B VERSION)
20 AUG 10
Applicable to: ALL
P3660
INDICATING/RECORDING SYSTEMS - ELECTRICAL
CLOCK - INSTALLATION OF A CLOCK SMITHS TYPE
2610
20 AUG 10
Applicable to: ALL
P3686
FLIGHT CONTROLS - EFCS EQUIPMENT - MODIFY
SEC STANDARD FOR A320 AND A321
20 AUG 10
Applicable to: ALL
P3694
AUTO FLIGHT: FLIGHT AUGMENTATION COMPUTER
INTRODUCE FAC POST CDN ON A320/321.
20 OCT 11
Applicable to: ALL
P3756
AUTO FLIGHT-FMGC-A320/321-FG STANDARD FOR
A321 CFM CAT III
20 AUG 10
Applicable to: ALL
P3790
AUTO FLIGHT - GENERAL - EXTEND CAT III B
AUTOMATICLANDING CAPABILITY (FOR CFM
ENGINES)
20 AUG 10
Applicable to: ALL
P3830
NAVIGATIOIN-AIRS-IMPROVED STANDARD OF
HONEYWELL 4 MCU ADIRU
20 AUG 10
FLIGHT CONTROLS-PARTIAL LIFT DUMPING
FUNCTION ACTIVATION
20 AUG 10
FLIGHT CONTROL-ELAC SYSTEM-INSTALL ELAC 69J
07 APR 11
NACELLES/PYLONS-IAE/CFM-ADAPT PYLON
PRIMARY STRUCTURE FOR A321 GROWTH
VERSION
Applicable to: ALL
P3878
Applicable to: ALL
P3955
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 12/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P3957
Linked SB
Incorp. Date
Title
06 JUL 16
ATA 2900 HYDRAULIC POWER-GENERAL INSTALL
AN HYDRAULIC SHUT-OFF VALVE ON THE CFM
THRUST REVERSER SYSTEM
20 AUG 10
NAVIGATION-WEATHER RADAR SYSTEM-NEW
SEXTANT ATC/TCAS CONTROL PANEL -SFE WITH
FULL TIME AND ABOVE BELOW FUNCTIONS
20 AUG 10
GENERAL - HIGH ALTITUDE CERTIFICATION UP TO
14.500 FT
20 AUG 10
AUTOFLIGHT-FCU-INSTALL M11 STANDARD
20 AUG 10
Applicable to: ALL
P4089
NAVIGATION-ADIRS-INSTALL HONEYWELL ADIRS
PROVIDING THE GPS PRIMARY NAVIGATION
CAPABILITY
20 AUG 10
Applicable to: ALL
P4121
AUTO-FLIGHT - FMGC - REDUCE VAPP FOR A320
CFM/IAE
20 AUG 10
Applicable to: ALL
P4151
EXHAUST - THRUST REVERSER CONTROL AND
INDICATING -ACTIVATE ADDITIONAL THRUST
REVERSER LOCK CONTROL
20 AUG 10
Applicable to: ALL
P4155
INDICATING/RECORDING SYSTEMS - UP AND DOWN
DATA LOADING SYSTEM - INSTALL A "PORTABLE
DATA LOADER" CONNECTOR AND DISK STOWAGE.
20 AUG 10
Applicable to: ALL
P4170
AUTOFLIGHT - FLIGHT MANAGEMENT AND
GUIDANCE COMPUTER - ACTIVATION OF ACARS
AND PRINTER INTERFACES IN F.M.S ( CFM
ENGINES)
20 AUG 10
Applicable to: ALL
P4191
FLIGHT CONTROLS - FCDC - PROVIDE A VISUAL
INDICATION FOR SIMULTANEOUS SIDE STICK
ACTION
20 AUG 10
NAVIGATION AND COMMUNICATIONS REPLACE BFE
EQUIPMENT BY SFE EQUIPMENT
Applicable to: ALL
P3964
Applicable to: ALL
P4023
Applicable to: ALL
P4054
Applicable to: ALL
P4087
35-1025 07
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 13/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P4205
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
P4230
AUTOFLIGHT - FMGC - ACTIVATE PRINTER
INTERFACE IN FMS (CFM AND IAE ENGINES)
20 AUG 10
Applicable to: ALL
P4234
POWER PLANT-GENERAL INTRODUCTION OF
CFM56-5B/P
20 AUG 10
Applicable to: ALL
P4281
ICE AND RAIN PROTECTION-WINDSHIELD RAIN
PROTECTION DESACTIVATION OF RAIN REPELLENT
SYSTEM.
20 AUG 10
ENGINE FUEL AND CONTROL-CONTROLLING
INTRODUCE OF A NEW ECU SOFTWARE STANDARD
5BE-1 FOR CFM56-5B SAC ENGINES
20 AUG 10
Applicable to: ALL
P4319
INDICATING-RECORDING SYSTEM FWC DEFINE
OEB REMINDER NEW FUNCTION IN FWC
20 AUG 10
Applicable to: ALL
P4320
AUTO FLIGHT/FCU DEFINE FD ENGAGEMENT IN
CROSSED BARS AT GO AROUND
20 AUG 10
AUTO FLIGHT - ACTIVATE GLOBAL SPEED
PROTECTION AND FD DISENGAGEMENT UPON
SPEED CONDITIONS
20 AUG 10
Applicable to: ALL
P4395
CERTIFICATION - GENERAL - CERTIFICATION FOR
HIGH ALTITUDE AIRPORT OPERATION
20 AUG 10
Applicable to: ALL
P4419
INDICATING/RECORDING SYSTEMS.EIS.UNITS OF
UNITS OF INDICATION "RUNWAY LENGHTS"IN FEET.
25 NOV 11
Applicable to: ALL
P4425
NAVIGATION - ADIRS - INSTALL HONEYWELL ADIRU
4 MCU STANDARD WITH OPTIMIZED HARDWARE
P/N "AD09"
25 NOV 11
Applicable to: ALL
P4495
NAVIGATION-ADIRS-INSTALL HONEYWELL ADIRU 4
MCU STANDARD, CAPABLE OF A319 IAE AIRCRAFT
20 AUG 10
INDICATING/RECORDING SYSTEMS- DISPLAY
MANAGEMENT COMPUTER (DMC) DEFINE DMC V32
STANDARD
Applicable to: ALL
P4287
Applicable to: ALL
P4378
31-1264 04
00-1054 19
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 14/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P4497
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
P4502
DOORS-EMERGENCY ESCAPE SLIDE RELEASE
AND OVERPRESSURE WARNING SYSTEMS-MODIFY
CONTROL LOGIC OF THE OVERPRESSURE WARING
SYSTEM
20 AUG 10
Applicable to: ALL
P4528
INFORMATION SYSTEMS - ATIMS - INSTALL ATSU
COMPUTER FOR PRE-FANS CONFIGURATION
20 AUG 10
Applicable to: ALL
P4539
ENGINE FUEL AND CONTROL -CONTROLLINGINTRODUCE AN ECU SOFTWARE STD 5BH FOR
CFM56-5B SAC ENGINES.
20 AUG 10
Applicable to: ALL
P4576
AUTO FLIGHT-GENERAL/FLIGHT CONTROL UNITDEFINE AND INSTALL SEXTANT MODULAR FCU
20 AUG 10
Applicable to: ALL
P4647
LANDING GEAR-GENERAL WHEELS AND BRAKES
EQUIPMENT COST REDUCTION ELECTRICAL
ALTERNATE BRAKING
20 AUG 10
Applicable to: ALL
P4706
NAVIGATION - WEATHER RADAR SYSTEM - COLLINS
DUAL PWS ACTIVATOR
22 MAR 16
NAVIGATION - ADF - INSTALLATION OF 1 ADF
QUANTUM LINE P/N 066-50014-0202
20 AUG 10
LANDING WITH A 15 KNOT TAILWIND
20 AUG 10
Applicable to: ALL
P4773
NAVIGATION - WEATHER RADAR SYSTEM. INSTALL
FULL PROVISION FOR THE SECOND TRANSCEIVER.
20 AUG 10
Applicable to: ALL
P4786
NAVIGATION - INSTALL DUAL COLLINS ADF 700 - P/N
622-5222-020
07 APR 11
Applicable to: ALL
P4789
COCKPIT PROTECTIVE BREATHING EQUIPMENT
(PBE)-SCOTT AVIATION
20 AUG 10
Applicable to: ALL
P4801
NAVIGATION-MMR-INSTALLATION OF SEXTANT
MULTICI-MODE RECEIVERS PROVIDING ILS (FM
IMMUNE) AND GPS PRIMARY FUNCTION
20 AUG 10
ELECTRICAL POWER - GENERATION SYSTEM
- DEFINE AND INSTALL ON A320 FAMILY
Continued on the following page
Applicable to: ALL
P4709
Applicable to: ALL
P4770
00-1043 56
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PLP-LOM P 15/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
Linked SB
Incorp. Date
Title
NEW ELECTRICAL GENERATION CONCEPT
(WIRING/EQUIPMENT)
Applicable to: ALL
P4808
20 AUG 10
Applicable to: ALL
P4859
LANDING GEAR - GENERAL - WHEELS AND BRAKES
- EQUIPMENT COST REDUCTION BSCU REDESIGN
22 MAR 16
Applicable to: ALL
P4867
NAVIGATION - ADF - INSTALL AN ADF 900 RECEIVER
P/N 822-0299-020
22 MAR 17
Applicable to: ALL
P4885
NAVIGATION - EGPWS - INSTL. NEW SPECIFICATION
INSTALLATION OF EGPWC (NEW SPECIFICATION)
20 AUG 10
Applicable to: ALL
P4916
NAVIGATION - EGPWS - ACTIVATION OF ENHANCED
FUNCTIONS OF THE EGPWS
20 AUG 10
Applicable to: ALL
P4954
FLIGHT CONTROL - GENERAL - ELAC-SYSTEM INSTALL ELAC COMPATIBLE A320/321/319 (EM2
PROGRAM)
20 AUG 10
AUTO FLIGHT - FMGC - DEFINE AND INSTALL FMGC
B546CAM0102 FOR A319 AUTOLAND CFM ENGINES
(CAPABLE OF GPS/ACARS FUNCTION)
20 AUG 10
Applicable to: ALL
P4983
INDICATING/RECORDING SYSTEMS - FWC PROVIDE NEW SYNTHETIC VOICE "DUAL INPUT"
20 AUG 10
Applicable to: ALL
P5020
AUTO FLIGHT - FLIGHT AUGMENTATION - DEFINE
FAC STANDARD B0513
20 AUG 10
Applicable to: ALL
P5071
NAVIGATION - ATC - INSTALL GABLES ATC/TCAS
CONTROL PANEL P/N G6990-40
20 AUG 10
Applicable to: ALL
P5138
ICE AND RAIN PROTECTION-WINDSHIELD RAIN
PROTECTIONREACTIVATE RAIN REPELLENT
SYSTEM WITH FLUID COMPATIBLE WITH OZONE
PROTECTION RULES
20 AUG 10
FLIGHT CONTROLS-GENERAL-ELAC SYSTEMINSTALL ELAC STANDARD L80
Applicable to: ALL
P4977
31-1264 04
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 16/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P5168
Linked SB
Incorp. Date
Title
20 AUG 10
NAVIGATION-MMR-INSTALLATION OF COLLINS
MULTI-MODE RECEIVERS PROVIDING ILS (FM
IMMUNE) AND GPS PRIMARY FUNCTION
20 AUG 10
NAVIGATION - EGPWS - INTRODUCE OPTIONAL
AURAL WARNINGS FOR EGPWS
07 APR 11
Applicable to: ALL
P5239
INDICATING/RECORDING SYSTEM-FWC-ACTIVATE
THE HI ALT SET" RIGH MEMO FOR HIGH ALTITUDE
AIRPORT OPERATION
20 AUG 10
Applicable to: ALL
P5241
NAVIGATION-ATC MODE "S"-INSTALL ATC/TCAS
CONTROL UNIT P/N C12240B02
20 AUG 10
NAVIGATION-WEATHER RADAR SYSTEMS-INSTALL
COLLINS SINGLE WITH PROVISION FOR THE
SECOND SYSTEM
20 AUG 10
NAVIGATION ADIRS REMOVE ADIRS CDU
20 AUG 10
Applicable to: ALL
P5429
AUTO FLIGHT - GENERAL - MULTIPURPOSE
CONTROL AND DISPLAY UNIT (MCDU) - INSTALL
MCDU HONEYWELL 2ND GENERATION P/N :
4077880-980
20 AUG 10
Applicable to: ALL
P5451
ENGINE FUEL AND CONTROL - GENERAL FADEC
SYSTEM A320/CFM56-5B - INTRODUCE ECU
SOFTWARE STANDARD 5BI
20 AUG 10
Applicable to: ALL
P5459
ELECTRICAL POWER - GENERAL AC & DC MAIN
DISTRIBUTION - INSTALL A/C AND DC SHEDDABLE
BUSBARS
20 AUG 10
Applicable to: ALL
P5465
POWER PLANT - GENERAL - ADD RELAY LOGIC FOR
CONTROL PACK CLOSURE AT ENGINE START
20 AUG 10
INDICATING/RECORDING SYSTEMS - CLOCKS
- INSTALL AIR PRECISION CLOCK P/N APE5100
CAPABLE OF GPS TIME
Applicable to: ALL
P5224
Applicable to: ALL
P5228
Applicable to: ALL
P5253
Applicable to: ALL
P5314
31-1118 20
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 17/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P5518
Linked SB
Title
20 AUG 10
Applicable to: ALL
P5567
LANDING GEAR - GENERAL - NORMAL BRAKING INTRODUCE STD 8 BSCU TWIN VERSION
20 AUG 10
Applicable to: ALL
P5583
INDICATING/RECORDING SYSTEM - DMC - DEFINE
DMC V40 STANDARD
20 AUG 10
Applicable to: ALL
P5638
NAVIGATION - ADIRS - REDUCED VERTICAL
SEPARATION MINIMUM (RVSM) USING ADR 1 AND
ADR 2 ONLY (A319/A320/A321 APPLICABLE)
20 AUG 10
Applicable to: ALL
P5669
NAVIGATION - STANDBY DATA : ALTITUDE AND
HEADING -INSTALL ISIS (INTEGRATED STANDBY
INSTRUMENT SYSTEM) - SERIAL SOLUTION -
20 AUG 10
NAVIGATION - TCAS - INSTALL ALLIED SIGNAL TCAS
COMPUTER P/N 066-50000-2220 (WITH CHANGE 7.0)
(BFE)
20 AUG 10
Applicable to: ALL
P5768
INDICATING/RECORDING SYSTEMS- FLIGHT
WARNING COMPUTER (FWC) INSTALL FWC STD
H2/E3
20 AUG 10
Applicable to: ALL
P5895
ELECTRICAL POWER - AC EMERGENCY
GENERATION - ACTIVATE ON A320 SAME
ELECTRICAL EMERG. CONFIGURATION THAN A321
20 AUG 10
Applicable to: ALL
P6030
NAVIGATION-GPWS-INSTALL EGPWS P/N-206-206 &
INHIBIT AUTOMATIC DEACTIVATION OF ENHANCED
FUNCTIONS.
05 SEP 17
Applicable to: ALL
P6044
ELECTRICAL POWER - AC GENERATION - INSTALL
ELECTRICAL OUTLETS IN COCKPIT
20 AUG 10
Applicable to: ALL
P6125
ICE AND RAIN PROTECTION - GENERAL WINDSHIELD RAIN PROTECTION INSTALL
IMPROVED GAGE ASSY P/N 4020W35-2
25 NOV 11
NAVIGATION - ADIRU - INSTALL HNWL ADIRU 4
MCU AD11 (NEW HARD) WITH 4 TRIMS OF ANEMO
CORRECTION LAWS POSSIBILITIES AND MAGVAR
TABLES UPDATED
Applicable to: ALL
P5706
32-1336 01
Incorp. Date
31-1257 01
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 18/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P6142
Linked SB
Incorp. Date
Title
20 AUG 10
Applicable to: ALL
P6146
NAVIGATION -STANDBY BY DATA-ATTITUDE AND
HEADING-COMPLETE PROVISIONS FOR ISIS
ELECTRICAL SUPPLY
20 AUG 10
Applicable to: ALL
P6201
INDICATING/RECORDING SYSTEM - FWC INTRODUCE "F/CTL FLAP LVR NOT ZERO" RED
WARNING
20 AUG 10
Applicable to: ALL
P6251
GENERAL-FLIGHT ENVIRONMENTAL ENVELOPEEXTENSION TO 12100 M
20 AUG 10
Applicable to: ALL
P6375
ICE AND RAIN PROTECTION - GENERAL WINDSHIELD RAIN PROTECTION - INSTALL NEW
GAGE ASSYWITHOUT INPUT VALVE FUNCTION P/N
4020W35-3
20 AUG 10
Applicable to: ALL
P6544
LANDING GEAR-PARKING/ULTIMATE EMERGENCY
BRAKING -INSTALL A PRESSURE SWITCH (PARKING
BRAKE SYSTEM IMPROVEMENT
20 AUG 10
Applicable to: ALL
P6578
INDICATING RECORDING SYSTEM - FWC ACTIVATE
SPECIFIC FWC PROCEDURE
20 AUG 10
Applicable to: ALL
P6588
INDICATING/RECORDING SYSTEMS - ELECTRONIC
INSTRUMENT SYSTEM INSTALL DMC, DU AND
DISKETTES FOR EIS2
20 AUG 10
Applicable to: ALL
P6589
INFORMATION SYSTEM - ATIMS IMPROVE ATSU
AIRCRAFT INTERFACE SOFTWARE TO UPDATE
SERVICE PROVIDERS LIST AND MANAGEMEN
20 AUG 10
INDICATING/RECORDING SYSTEMS - CFDIU
INTRODUCE CFDIU STANDARD 9B
20 AUG 10
CERTIFICATION DOCUMENTS - GENERAL - CERTIFY
AIRCRAFT FOR OPERATION ON RUNWAYS LESS
THAN 45 M WIDTH
20 AUG 10
COMMUNICATION - RADIO MANAGAMENT
INTRODUCE NEW RMP STANDARD 2 P/N
C12848AB02
Applicable to: ALL
P6630
Applicable to: ALL
P6687
00-1058 97
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 19/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
Linked SB
Incorp. Date
07 APR 11
COMMUNICATIONS - RADIO MANAGEMENT INSTALL
A THIRD RADIO MANAGEMENT PANEL
22-1079 08
22-1102 02
22-1226 04
20 AUG 10
AUTO FLIGHT - FLIGHT AUGMENTATION COMPUTER
INSTALL NEW FAC SOFTWARE STANDARD P/N
B397BAM0515
26 JAN 16
NAVIGATION - ILS (MMR) - INSTALL HONEYWELL
MMR PROVIDING ILS (FM IMMUNE) AND GPS
PRIMARY FUNCTIONS (HYBRID ARCHITECTURE)
07 APR 11
INFORMATION SYSTEM - ATIMS UPGRADE ATSU
HARDWARE FOR NEW ARINC 429 I/O BOARD
20 AUG 10
INDICATING RECORDING SYSTEM - FWC INSTALL
FWC STANDARD H2E4
20 AUG 10
INFORMATION SYSTEMS - ATIMS - DEFINE AND
INSTALL NEW SOFTWARE ATSU A/C INTERFACE
UPGRADED
20 AUG 10
FLIGHT CONTROLS - ELAC SYSTEM - INTRODUCE
ELAC SOFTWARE "L90" CAPABLE OF A318
20 AUG 10
INDICATING/RECORDING SYSTEM : FROM FWC-F1
PIN-PROGRAMMING FOR IMPROVING THE
MONITORING ABOUT THE NORMAL BRAKING
SYSTEM
20 AUG 10
Applicable to: ALL
P6985
AUTO FLIGHT - FLIGHT AUGMENTATION COMPUTER
(FAC SYSTEM) - INTRODUCE FAC SOFTWARE
"BAM0516" CAPABLE OF A318
20 AUG 10
Applicable to: ALL
P6987
NAVIGATION - ADIRS - INSTALL HONEYWELL ADIRU
4MCU CAPABLE OF A318 A/C
20 AUG 10
AUTO FLIGHT - FMGC INSTALL FMGC P/N
B546CAM0103 (CFM GPS/ACARS)
20 AUG 10
LANDING GEAR - NORMAL BRAKING - INTRODUCE
STD 9 BSCU (TWIN VERSION)
P6688
Applicable to: ALL
P6703
Applicable to: ALL
P6766
Applicable to: ALL
P6777
Applicable to: ALL
P6801
31-1257 01
Applicable to: ALL
P6832
Applicable to: ALL
P6901
27-1160 01
Applicable to: ALL
P6911
Applicable to: ALL
P6954
Applicable to: ALL
P7005
22-1102 02
22-1226 04
32-1336 01
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Title
Continued on the following page
PLP-LOM P 20/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
Linked SB
Incorp. Date
20 AUG 10
INDICATING/RECORDING SYSTEM - EIS - ACTIVATE
FUEL FLOW/DELTA ISA FUNCTION BY PIN
PROGRAMMING ON DMC
31-1257 01
20 AUG 10
Applicable to: ALL
P7148
INDICATING/RECORDING SYSTEMS - FWC - INSTALL
FWC STANDARD H2 F1 ON A318 PW
20 AUG 10
Applicable to: ALL
P7175
COMMUNICATIONS - HF SYSTEM - ACTIVATE DATA
LINK FUNCTION FOR HFDR 1
20 AUG 10
Applicable to: ALL
P7185
ELECTRICAL POWER - GENERAL - INSTALL A
COMMERCIAL SHEDDING PUSH-BUTTON SWITCH IN
COCKPIT
19 JUN 17
Applicable to: ALL
P7186
NAVIGATION - EGPWS INSTALL ENHANCED GPWS
P/N 965-1676-001
20 AUG 10
Applicable to: ALL
P7187
NAVIGATION - EGPWS ACTIVATE PEAKS MODE
OF EGPWS IN CONJUNCTION WITH THE TERRAIN
DISPLAY
20 AUG 10
Applicable to: ALL
P7188
NAVIGATION - EGPWS ACTIVATE GEOMETRIC
ALTITUDE FUNCTION IN THE EGPWS
20 AUG 10
Applicable to: ALL
P7218
NAVIGATION - EGPWS ACTIVATE OBSTACLE
OPTION ON THE EGPWS
22 MAR 16
Applicable to: ALL
P7247
AUTOFLIGHT - FLIGHT MANAGEMENT AND
GUIDANCE COMPUTER (FMGC) DEVELOP FMS 2ND
GENERATION HONEYWELL STEP1
20 AUG 10
Applicable to: ALL
P7268
FLIGHT CONTROLS - ELAC SYSTEM - INSTALL ELAC
STANDARD L81
20 AUG 10
Applicable to: ALL
P7278
NAVIGATION - ADIRU RESTORE RVSM 3 CIRCUITS
CAPABILITIES - SERIAL SOLUTION
20 AUG 10
INDICATING RECORDING SYSTEM - EIS2 INSTALL
EIS2 SOFTWARE CAPABLE OF A318 A/C
P7092
Applicable to: ALL
P7125
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Title
Continued on the following page
PLP-LOM P 21/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P7300
Linked SB
Incorp. Date
Title
05 SEP 17
Applicable to: ALL
P7397
ELECTRICAL POWER - AC GENERATION - INSTALL
ELECTRICAL OUTLETS IN COCKPIT 4MM AND 4.8MM
DIA. PLUGS
01 DEC 15
Applicable to: ALL
P7407
NAVIGATION - ADIRS INSTALL HONEYWELL ADIRU
4MCU CAPABLE OF A318
07 APR 11
Applicable to: ALL
P7425
COMMUNICATION - RADIO MANAGEMENT INSTALL
RMP STANDARD 3 WITH MLS AND GLS FUNCTION
CAPABILITY
06 JUL 16
Applicable to: ALL
P7455
NAVIGATION - ATC - INSTALL HONEYWELL ATC
TRA67A INCORPORATING EUROPEAN MODE S
REGULATIONS
20 AUG 10
Applicable to: ALL
P7519
ELECTRICAL POWER - GENERAL IN FLIGHT
ENTERTAINMENT (IFE) POWER SUPPLY ON
SHEDDABLE BUSBARS CONTROLED BY "GALY &
CAB" SW
20 AUG 10
AUTOFLIGHT - FMGC - INSTALL FMGC CFM
C13042AA01 (EQUIPPED WITH FMS2 HONEYWELL)
Applicable to: ALL
P7635
27-1160 01
20 AUG 10
Applicable to: ALL
P7721
FLIGHT CONTROLS - ELAC SYSTEM INTRODUCE
ELAC SOTWARE L82
32-1247 02
20 AUG 10
Applicable to: ALL
P7790
LANDING GEAR - WHEELS AND BRAKES REMOVE
THE TEMPORARY REVISIONS 5.02.00/23 AND
5.03.00/23 ON FLIGHT MANAL
20 AUG 10
Applicable to: ALL
P7919
AUTO FLIGHT FLIGHT MANAGEMENT AND
GUIDANCE SYSTEM ACTIVATE FMA ENHANCEMENT
FUNCTION
20 AUG 10
Applicable to: ALL
P7929
ENGINE FUEL AND CONTROL - FADEC SYSTEM INTRODUCE NEW FADEC SOFTWARE "5BK" ON SAC
CFM56-5B ENGINES
20 AUG 10
NAVIGATION - WEATHER RADAR SYSTEM INSTALL
COLLINS DUAL CONTROL PANEL TO ACTIVATE
MULTISCAN FUNCTION
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 22/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P8069
Linked SB
Title
20 AUG 10
Applicable to: ALL
P8076
ENGINE FUEL AND CONTROL - FADEC SYSTEM
INTRODUCE NEW ECU SOFTWARE STANDARD "5BL"
FOR CFM56-5B ENGINES CAPABLE OF A318 CFM
A/C
20 AUG 10
Applicable to: ALL
P8175
LANDING GEAR NORMAL BRAKING INSTALL BSCU
STD L4.5
20 AUG 10
Applicable to: ALL
P8176
INDICATING/RECORDING SYSTEMS - SDAC ACTIVATE IAS DISCREPANCY MONITORING BY PIN
PROGRAMMING
07 APR 11
Applicable to: ALL
P8194
INDICATING/RECORDING SYSTEMS - SDAC ACTIVATE DUAL PITOT MONITORING BY PIN
PROGRAMMING
20 AUG 10
NAVIGATION - ADIRS ACTIVATE ALIGNMENT
IMPROVEMENT FUNCTION ON ADIRU
20 AUG 10
Applicable to: ALL
P8241
INDICATING/RECORDING SYSTEMS - FWC INTRODUCE IAS DISCREPANCY AND DUAL PITOT
MONITORING ON FWC H2F1
07 APR 11
Applicable to: ALL
P8243
PLACARDS AND MARKINGS - CABIN CONFIGURATE THE CABIN FOR NON SMOKING
FLIGHT
20 AUG 10
CERTIFICATION DOCUMENTS / EXTEND OPERATING
FLIGHT ENVELOPE TO MINUS 2000FT PRESSURE
ALTITUDE
22-1102 02
22-1226 04
20 AUG 10
AUTO FLIGHT FLIGHT AUGMENTATION COMPUTER
INSTALL FAC STANDARD BAM0617 FOR A318 EIS
31-1257 01
20 AUG 10
INDICATING RECORDING SYSTEM FWC INSTALL
FWC STANDARD H2F2
20 AUG 10
NAVIGATION DDRMI REMOVE DDRMI VOR/ADF/DME
INDICATORS
Applicable to: ALL
P8232
Applicable to: ALL
P8256
Applicable to: ALL
P8274
Applicable to: ALL
P8303
73-1080 01
Incorp. Date
31-1266 02
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 23/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P8440
Linked SB
Title
20 AUG 10
Applicable to: ALL
P8564
LANDING GEAR - WHEELS AND BRAKES
INTRODUCE GOODRICH DURACARB CARBON
BRAKES WITH ANTI - OXYDAN "M1"
20 AUG 10
Applicable to: ALL
P8626
INDICATING/RECORDING SYSTEM EIS ACTIVATE
ENGINE AVAIL DISPLAY
20 AUG 10
Applicable to: ALL
P8671
NAVIGATION - STANDBY DATA (ISIS) - INSTALL ISIS
STANDARD VA01 WITH CORRECTION OF "OUT OF
ORDER" MESSAGE & "NEW IMU STANDARD"
20 AUG 10
INDICATING RECORDING SYSTEM EIS INSTALL DMC
SOFTWARE EIS2 S4-2 TO CORRECT TEMPORARY
LOSS OF ALL EIS2 IMAGES
20 AUG 10
Applicable to: ALL
P8710
AUTOFLIGHT - FMGC INSTALL FMS2 HONEYWELL
P1C11 ON A/C FITTED WITH CFMI PPS
20 AUG 10
Applicable to: ALL
P8751
NAVIGATION - WEATHER RADAR SYSTEM - INSTALL
COLLINS TRANSCEIVER FULLY COMPLIANT WITH
MULTISCAN FUNCTION
20 AUG 10
Applicable to: ALL
P8799
NAVIGATION - EGPWS - INSTALL AN EGPWC
CAPABLE OF PEAKS/OBSTACLE FUNCTIONS WITH
EIS1 & OF USING GPS LATERAL POSITION
20 AUG 10
Applicable to: ALL
P8850
NAVIGATION - EGPWS - INSTALL AN EGPWC
CAPABLE OF PEAKS/OBSTACLE FUNCTIONS WITH
EIS1 & OF USING GPS LATERAL POSITION
20 AUG 10
Applicable to: ALL
P8863
PNEUMATIC - ENGINE BLEED AIR SUPPLY INTRODUCE BMC STD 9 CAPABLE OF A318 PW
20 AUG 10
Applicable to: ALL
P8866
INDICATING/RECORDING SYSTEM FWC
ACQUISITION INTERFACE CONNECT FWC TO RPWS
TO PREVENT DOOR OPENING WITH RESIDUAL
CABIN PRESSURE
20 AUG 10
LANDING GEAR NORMAL BRAKING INSTALL BSCU
STD L4.8 (EM2)
Applicable to: ALL
P8708
32-1291 01
Incorp. Date
22-1168 01
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
PLP-LOM P 24/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
Linked SB
Incorp. Date
20 AUG 10
AUTO FLIGHT MCDU INSTALL LCD MCDU
HONEYWELL
31-1267 03
31-1300 02
20 AUG 10
Applicable to: ALL
P9196
INDICATING/RECORDING SYSTEM FLIGHT
WARNING COMPUTER - FWC - INSTALL FWC
STANDARD H2 F3
07 APR 11
Applicable to: ALL
P9207
NAVIGATION - STANDBY DATA (ISIS) INSTALL ISIS
STD WB01 WITH CORRECTION OF "OUT OF ORDER"
MESSAGE
20 AUG 10
Applicable to: ALL
P9225
NAVIGATION - ATC / MODE S - CERTIFY EHS
FUNCTION
20 AUG 10
Applicable to: ALL
P9333
INDICATING / RECORDING SYSTEM : ELECTRONIC
INSTRUMENT SYSTEM (EIS) - INSTALL DISPLAY
MANAGEMENT COMPUTER SOFTWARE EIS2 S6-1
01 DEC 15
Applicable to: ALL
P9508
NAVIGATION - AIR DATA/INERTIAL REFERENCE
SYSTEM - INSTALL HONEYWELL ADIRU P/N
HG2030-AE23
20 AUG 10
Applicable to: ALL
P9522
INDICATING/RECORDING SYSTEMS - SDAC ACQUISITION/INTERFACE CONFIGURATION CABIN
FOR NO PED FLIGHTS
20 AUG 10
AUTO FLIGHT - MCDU ACTIVATE BACK UP NAV
FUNCTION
20 AUG 10
Applicable to: ALL
P9824
ENGINE FUEL AND CONTROL - FADEC SYSTEM
INSTALL "5BM" STANDARD ECU SOFTWARE FOR
CFM 56-5B ENGINES
20 AUG 10
Applicable to: ALL
P9873
INDICATING / RECORDING SYSTEMS NSTALL
DISPLAY MANAGEMENT COMPUTER SOFTWARE
EIS2 S7 ELECTRONIC INSTRUMENT SYSTEM
20 AUG 10
POWER PLANT - GENERAL INTRODUCE
CFM56-5BX/3 ENGINE (SAC) "TECH INSERTION
PROGRAM"
P9038
Applicable to: ALL
P9107
Applicable to: ALL
P9552
73-1086 00
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Title
Continued on the following page
PLP-LOM P 25/26
05 SEP 17
PRELIMINARY PAGES
LIST OF MODIFICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
M
Continued from the previous page
MODIFICATION
P9920
Linked SB
Incorp. Date
Title
07 APR 11
Applicable to: ALL
27-1230 01
GENERAL - TECHNICAL DOCUMENTATION
EXTENSION OF FLEX TEMPERATURE - UPDATE FM
& FCOM DOCUMENTATION
31 JUL 14
Applicable to: ALL
27-1238 00
FLIGHT CONTROLS - SPOILER AND ELEVATOR
COMPUTER (SEC) - INSTALL SEC 123 HARDWARE B
06 JUL 16
Applicable to: ALL
31-1373 00
FLIGHT CONTROLS - ELAC - INSTALL L97
STANDARD ON ELAC B WITHOUT DATALOADING
CAPABILITY
31 JUL 14
Applicable to: ALL
34-1412 06
INDICATING/RECORDING SYSTEMS - FLIGHT
WARNING COMPUTER (FWC) - INSTALL FWC
STANDARD H2-F6
22 MAR 17
Applicable to: ALL
34-1443 03
NAVIGATION - EGPWS - INSTALL EGPWC PN
965-1676-003.
06 JUL 16
Applicable to: ALL
34-1506 34
NAVIGATION - WEATHER RADAR SYSTEM - INSTALL
COLLINS TRANSCEIVER FULLY COMPLIANT WITH
MULTISCAN FUNCTION PN 822-1710-203.
22 MAR 17
NAVIGATION - TCAS - INSTALL A NEW HONEYWELL
TCAS TPA-100B
Applicable to: ALL
(1) Evolution code : N=New, R=Revised, E=Effectivity
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PLP-LOM P 26/26
05 SEP 17
GENERAL INFORMATION
Intentionally left blank
GENERAL INFORMATION
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TABLE OF CONTENTS
Aircraft Configuration Summary...............................................................................................................................A
If Installed Table...................................................................................................................................................... B
Main FCOM Changes..............................................................................................................................................C
FCOM Purpose........................................................................................................................................................D
List of Effective Sections/Subsections (LESS) - Paper ONLY................................................................................E
List of Effective Operations Engineering Bulletins (LEOEB)................................................................................... F
List of Effective Documentary Units (LEDU) - Paper Only..................................................................................... G
List of Effective Temporary Documentary Units (LETDU) - Paper Only.................................................................H
Aircraft Allocation Table (AAT) - Paper Only........................................................................................................... I
List of Modifications (LOM) - Paper Only................................................................................................................ J
FCOM Use and Organization..................................................................................................................................K
FCOM Format and Style Information - Paper only..................................................................................................L
FCOM Revisions..................................................................................................................................................... M
Abbreviations........................................................................................................................................................... N
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
GEN-PLP-TOC P 1/2
05 SEP 17
GENERAL INFORMATION
PRELIMINARY PAGES
A318/A319/A320/A321
TABLE OF CONTENTS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
GEN-PLP-TOC P 2/2
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AIRCRAFT CONFIGURATION SUMMARY
Applicable to: ALL
Ident.: GEN-ACS-00016449.0001001 / 26 JUN 15
For awareness and for the specified aircraft, the following table provides the flight crew with a list of
optional aircraft systems and functions related to flight and aircraft operations.
Ident.: GEN-ACS-00018963.0001001 / 04 MAR 16
Item
System
Ident.: GEN-ACS-00015613.0001001 / 23 JUN 15
ADS-B OUT
Ident.: GEN-ACS-00016448.0001001 / 23 JUN 15
AP Automatic Disconnection at Minima
Ident.: GEN-ACS-00015927.0001001 / 26 JUN 15
AP /FD TCAS
Ident.: GEN-ACS-00015892.0002001 / 19 FEB 16
Automatic FD Bar Engagement
Ident.: GEN-ACS-00016009.0002001 / 23 JUN 15
Backup Navigation Function of the MCDU
Ident.: GEN-ACS-00016014.0001001 / 23 JUN 15
BUSS
Ident.: GEN-ACS-00016010.0001001 / 23 JUN 15
CPDLC
Ident.: GEN-ACS-00015917.0001001 / 23 JUN 15
Derated Takeoff
Ident.: GEN-ACS-00019728.0002001 / 06 JUN 16
Descent Profile Optimization (DPO)
Ident.: GEN-ACS-00015912.0001001 / 23 JUN 15
FLS Function in the FMS
Ident.: GEN-ACS-00015913.0005001 / 23 JUN 15
FMS 2 Release 1A
Ident.: GEN-ACS-00015899.0001001 / 23 JUN 15
GLS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
Installed
SURV
No
AUTO FLT
No
AUTO FLT
No
AUTO FLT
Yes
AUTO FLT
Yes
NAV
No
DATALINK
No
ENG
No
AUTO FLT
No
AUTO FLT
No
AUTO FLT
Yes
AUTO FLT
No
GEN P 1/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-ACS-00015924.0002001 / 23 JUN 15
GPS
Ident.: GEN-ACS-00016553.0002001 / 23 JUN 15
GPS PRIMARY Function
Ident.: GEN-ACS-00015926.0001001 / 23 JUN 15
Metric Altitude Indications on the PFD
Ident.: GEN-ACS-00015900.0001001 / 23 JUN 15
MLS
Ident.: GEN-ACS-00015923.0001001 / 19 FEB 16
NAV Mode automatically Engaged (Armed) in Go-Around
Ident.: GEN-ACS-00016013.0002001 / 23 JUN 15
PWS
Ident.: GEN-ACS-00015920.0001001 / 23 JUN 15
QFE BARO Setting
Ident.: GEN-ACS-00019573.0001001 / 10 MAY 16
RAAS
Ident.: GEN-ACS-00015897.0001001 / 23 JUN 15
RNP AR
Ident.: GEN-ACS-00016008.0001001 / 23 JUN 15
ROW / ROPS
Ident.: GEN-ACS-00016015.0001001 / 22 MAR 17
Soft Go-Around
NAV
Yes
NAV
Yes
EIS
No
AUTO FLT
No
AUTO FLT
No
SURV
Yes
NAV
No
SURV
No
AUTO FLT
No
SURV
No
ENG
No
IF INSTALLED TABLE
Applicable to: ALL
Ident.: GEN-IFIT-00016590.0001001 / 23 JUN 15
The "If Installed Table" provides a list of optional systems and functions of the aircraft.
For most of the optional systems or functions associated with the "if installed" symbol in the
FCOM, the table indicates if the optional systems or functions are installed, or not installed.
Note:
Highly customized options such as cabin installations are not covered in the following table.
Ident.: GEN-IFIT-00018965.0001001 / 22 MAR 16
Item
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
System
Installed
GEN P 2/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00015896.0002001 / 17 MAR 17
L13
4th Occupant Folding Seat
4th Occupant
Fourth Occupant
EQUIPMENT
Yes
OXY
Yes
ELEC
Yes
FUEL
No
NAV
No
NAV
Yes
Ident.: GEN-IFIT-00016012.0002001 / 21 MAR 16
L13
4th Oxygen Mask
Four
Ident.: GEN-IFIT-00018779.0002001 / 21 MAR 16
AC ESS FEED Auto Switching
Ident.: GEN-IFIT-00016516.0001001 / 21 MAR 17
L13
ACT
1 ACT
2 ACTs
ACT 1
ACT 2
ACT 1 OR 2
ACT PUMP
ACT PUMP LO PR
ACT XFR FAULT
ACT1
ACT2
ACTs
Additional center tank
Ident.: GEN-IFIT-00020299.0002001 / 13 SEP 16
L13
1 ADF
ADF 1
ADF1
Ident.: GEN-IFIT-00020300.0002001 / 13 SEP 16
L13
2 ADF s
2 ADF
ADF 1
ADF 1
ADF 2
ADF 2
ADF s
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
GEN P 3/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00016641.0001001 / 23 JUN 15
ADS-B OUT
SURV
No
COND
No
FIRE
Yes
VENT
No
F/CTL
No
Ident.: GEN-IFIT-00015891.0001001 / 21 MAR 16
L13
AFT Cargo Heating
AFT CRG HOT AIR
temperature selector
HOT AIR pb
AFT CRG HEAT
AFT CARGO HEAT
AFT CARGO DUCT OVHT
AFT Cargo heat controller
Cargo Heat
Cargo Temperature Regulation
CRG HEAT
Forward (aft) cargo heat controller
HOT AIR
Ident.: GEN-IFIT-00015901.0002001 / 21 MAR 16
L13
AFT Cargo Smoke Detector
SMOKE AFT CARGO SMOKE
SMOKE AFT CRG DET FAULT
AFT CRG DET
AFT CARGO SMOKE
AFT CRG DET FAULT
Ident.: GEN-IFIT-00015931.0001001 / 21 MAR 16
L13
AFT Cargo Ventilation
Cargo Ventilation
AFT ISOL VALVE
AFT CRG VENT
AFT CRG VENT FAULT
AFT Cargo isol valves
FWD (AFT) CARGO DUCT OVHT
FWD (AFT) CRG HEAT
FWD (AFT) CRG HEAT FAULT
FWD (AFT) CRG ISOL VALVE
FWD (AFT) CRG VENT FAULT
FWD (AFT) CRG VENT
Forward (aft) cargo isolation valves
isolation valves
Ident.: GEN-IFIT-00016522.0001001 / 23 JUN 15
Aileron Anti Droop
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
GEN P 4/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00015919.0002001 / 21 MAR 16
L13
Air Conditioning System Controller ( ACSC )
ACSC
ACSC 1
ACSC 2
Air Conditioning System Controllers
Ident.: GEN-IFIT-00016523.0001001 / 23 JUN 15
AP / FD TCAS
COND
Yes
AUTO FLT
No
SURV
No
AUTO FLT
Yes
ENG
Yes
AUTO FLT
Yes
NAV
Yes
BRAKE
No
Ident.: GEN-IFIT-00016640.0001001 / 21 MAR 16
L13
ATSAW
ADS-B IN
Ident.: GEN-IFIT-00016524.0002001 / 23 JUN 15
Automatic FD Bar Engagement
Ident.: GEN-IFIT-00018780.0002001 / 21 MAR 16
L13
Avail Indication During Engine Start
AVAIL Indication
Ident.: GEN-IFIT-00016681.0002001 / 21 MAR 16
L13
Backup Navigation Function of the MCDU
BACK UP NAV
Ident.: GEN-IFIT-00016525.0002001 / 21 MAR 16
L13
BARO /RADIO Instead of MDA / MDH / DH
BARO
BARO /RADIO
Ident.: GEN-IFIT-00016526.0001001 / 21 MAR 16
L13
Brake Fans
Brake cooling fans
BRK FAN
Brake Fan
Brake fans 1, 2, 3 and 4
Brake fans 5, 6, 7 and 8
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
GEN P 5/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00015875.0002001 / 21 MAR 16
L13
Bulk Cargo Door
Bulk Cargo Compartment Door
Bulk Door
DOORS
Yes
NAV
No
VENT
Yes
FUEL
No
FUEL
Yes
OXY
Yes
SMOKE
Yes
EQUIPMENT
Yes
Ident.: GEN-IFIT-00018781.0001001 / 21 MAR 16
L13
BUSS
Backup Speed/Altitude Scale
Backup Speed Scale
Ident.: GEN-IFIT-00021488.0002001 / 17 MAR 17
L13
Cargo ventilation system
Cargo isolation valves
Extraction fan
Ident.: GEN-IFIT-00016535.0001001 / 22 MAR 17
L13
Center Fuel Tank Transfer Valves
Center Tank Transfer Valves
L CTR TK XFR valve
CTR TK XFR valve R
Ident.: GEN-IFIT-00021220.0001001 / 22 MAR 17
L13
Center Fuel Tank Pumps
CTR TK PUMP 1
CTR TK PUMP 2
Ident.: GEN-IFIT-00015930.0002001 / 21 MAR 16
L13
Chemical Oxygen System 22 min
Chemical Oxygen System
22 min
Ident.: GEN-IFIT-00016625.0002001 / 17 MAR 17
L13
CIDS-SDF
CIDS 1 SMOKE DETECT
Smoke Detection Function ( SDF )
Ident.: GEN-IFIT-00015929.0002001 / 17 MAR 17
L13
Cockpit Door Deadbolt
Deadbolt
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
GEN P 6/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00018782.0002001 / 21 MAR 16
Cockpit Door Escape Panel
DOOR
Yes
OXY
No
COND
No
EQUIPMENT
No
EQUIPMENT
Yes
ELEC
Yes
COM
No
COM
No
ELEC
No
NAV
Yes
Ident.: GEN-IFIT-00016690.0001001 / 21 MAR 16
L13
Cockpit Fixed Second Oxygen Bottle
Two
Ident.: GEN-IFIT-00016612.0001001 / 23 JUN 15
Cockpit Foot Heater
Ident.: GEN-IFIT-00016639.0001001 / 17 MAR 17
L13
Cockpit Foot Warmer
Foot Warmer System
Foot Warmer ON/OFF Control Switch
Ident.: GEN-IFIT-00021875.0002001 / 25 JUL 17
L13
Cockpit Power Outlet
Power Outlet
Ident.: GEN-IFIT-00016614.0002001 / 21 MAR 16
L13
COMMERCIAL pb
COMMERCIAL
Ident.: GEN-IFIT-00016615.0001001 / 23 JUN 15
CVR Datalink Function
Ident.: GEN-IFIT-00016626.0001001 / 23 JUN 15
CVR ERASE pb
Ident.: GEN-IFIT-00016647.0001001 / 21 MAR 17
L13
DC BUS Entertainment
TR Entertainment
DC BUS Ent
DC BUS Entertainment
TR Ent
TR Ent.
Ident.: GEN-IFIT-00016527.0002001 / 21 MAR 16
L13
DDRMI
Digital Distance and Radio Magnetic Indicator
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
GEN P 7/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00016528.0001001 / 21 MAR 16
L13
Derated Takeoff
DERATE
ENG
No
AUTO FLT
No
EIS
Yes
ICE
No
LIGHTS
Yes
SURV
Yes
L/G
Yes
COM
Yes
COM
Yes
AUTO FLT
Yes
ENG
Yes
Ident.: GEN-IFIT-00019730.0002001 / 06 JUN 16
L13
Descent Profile Optimization
DPO
Ident.: GEN-IFIT-00016580.0002001 / 21 MAR 16
L13
Display of Delta ISA
Delta ISA
Ident.: GEN-IFIT-00016529.0001001 / 23 JUN 15
Dual Ice Detection System
Ident.: GEN-IFIT-00016574.0002001 / 23 JUN 15
Dual Navigation Lights
Ident.: GEN-IFIT-00016628.0002001 / 17 MAR 17
L13
EGPWS
Ident.: GEN-IFIT-00016530.0002001 / 23 JUN 15
Electrical Alternate Braking
Ident.: GEN-IFIT-00016575.0002001 / 23 JUN 15
ELT sw
Ident.: GEN-IFIT-00020758.0002001 / 18 MAY 17
L13
EVAC Panel
COMMAND PB (guarded)
COMMAND PB
Evacuation ( EVAC ) signalling
EVAC HORN
HORN SHUT OFF PB
CAPT and PURS/CAPT SW
Ident.: GEN-IFIT-00021713.0001001 / 03 AUG 17
Expedite
Ident.: GEN-IFIT-00015918.0002001 / 23 JUN 15
Extended FLEX Takeoff
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
GEN P 8/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00016531.0002001 / 21 MAR 16
L13
External Ice Detector Light
ICE IND
ICE
Yes
FANS
No
FANS
No
FANS
No
VENT
No
FIRE
Yes
FIRE
Yes
Ident.: GEN-IFIT-00021527.0001001 / 17 MAR 17
FANS A+
DCDU
ATC MSG pb
Ident.: GEN-IFIT-00021529.0001001 / 17 MAR 17
FANS B
DCDU
ATC MSG pb
Ident.: GEN-IFIT-00021530.0001001 / 17 MAR 17
FANS B+
DCDU
ATC MSG pb
Ident.: GEN-IFIT-00015909.0001001 / 21 MAR 16
L13
Fan Speed Controller (FSC)
Two Operating Speeds
Ident.: GEN-IFIT-00016629.0003001 / 21 MAR 16
L13
Fire Extinguishing in the AFT Cargo
SMOKE FWD (AFT) CRG BTL 1(2) FAULT
Forward (aft) cargo fire extinguishing
Ident.: GEN-IFIT-00016630.0005001 / 21 MAR 16
L13
Fire Extinguishing in the FWD Cargo
SMOKE FWD (AFT) CRG BTL 1(2) FAULT
Forward (aft) cargo fire extinguishing
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
GEN P 9/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00015898.0001001 / 21 MAR 17
L13
FLS
F-G/S
F-G/S BASED ON ISA
F-G/S-F-LOC
F-G/S-LOC
F-LOC
F-LOC*/F-LOC
FLS 1
FLS 2
FLS function
NO FLS FOR THIS APPR
Ident.: GEN-IFIT-00016579.0002001 / 23 JUN 15
FMS Crossload
Ident.: GEN-IFIT-00016589.0004001 / 23 JUN 15
HONEYWELL FMS 2 Release 1A H2
Ident.: GEN-IFIT-00015617.0001001 / 23 JUN 15
FTIS
Ident.: GEN-IFIT-00016532.0001001 / 23 JUN 15
Fuel Leak Detection
Ident.: GEN-IFIT-00016533.0001001 / 23 JUN 15
Fuel Tank Overflow Alert
AUTO FLT
No
AUTO FLT
Yes
AUTO FLT
Yes
FUEL
No
FUEL
No
FUEL
No
COND
No
Ident.: GEN-IFIT-00015893.0001001 / 21 MAR 16
L13
FWD Cargo Heating
Temperature Selector
FWD (AFT) CARGO DUCT OVHT
FWD (AFT) CRG HEAT
FWD (AFT) CRG HEAT FAULT
FWD CRG HEAT
Cargo Heat
Cargo Temperature Regulation
CRG HEAT
Forward (aft) cargo heat controller
HOT AIR
Fwd cargo heat controller
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
GEN P 10/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00015925.0002001 / 21 MAR 16
L13
FWD Cargo Smoke Detector
SMOKE FWD CARGO SMOKE
FWD CARGO SMOKE
SMOKE FWD CRG DET FAULT
FWD CRG DET
FIRE
Yes
VENT
Yes
ELEC
No
ELEC
Yes
OXY
No
AUTO FLT
No
Ident.: GEN-IFIT-00015932.0002001 / 21 MAR 16
L13
FWD Cargo Ventilation
FWD Cargo Outlet Isolation Valve
Cargo Ventilation
FWD ISOL Valve
FWD CRG VENT
FWD CARGO ISOL VALVE
Forward (aft) cargo isolation valves
Fwd cargo isol valves
Ident.: GEN-IFIT-00016617.0001001 / 21 MAR 16
L13
Galley Bus Automatic Shedding
Galley Load Automatic Shedding
Ident.: GEN-IFIT-00016618.0002001 / 21 MAR 16
L13
GAPCU
Ground and Auxiliary Power Control Unit
Ident.: GEN-IFIT-00019705.0001001 / 13 MAY 16
L13
Gaseous Oxygen Generators in lavatories
Gaseous Generators
Ident.: GEN-IFIT-00016534.0001001 / 21 MAR 16
L13
GLS
GLS Autoland
GLS1
GLS2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
GEN P 11/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00016649.0002001 / 21 MAR 16
L13
GPS
FM / GPS POS DISAGREE
GPS 1(2) FAULT
GPS 1
GPS 2
GPS 1+2
NAV
Yes
NAV
Yes
COM
No
COM
Yes
COM
Yes
OXY
Yes
SURV
No
NAV
Yes
NAV
Yes
Ident.: GEN-IFIT-00016650.0002001 / 21 MAR 16
L13
GPS PRIMARY Function
GPS PRIMARY
Ident.: GEN-IFIT-00020297.0001001 / 17 MAR 17
GSM Onboard
Ident.: GEN-IFIT-00015911.0002001 / 21 MAR 17
L13
HF Datalink
HF 1(2) DATA FAULT
HF DATA LINK
Ident.: GEN-IFIT-00020132.0002001 / 22 MAR 17
L13
HF System
HF
HF 1
HF 2
Ident.: GEN-IFIT-00016644.0002001 / 21 MAR 16
L13
HI ALT pb
Operation on High Altitude Airfields
HI ALT LANDING pb-sw
HI ALT LANDING pb-sw
Ident.: GEN-IFIT-00018783.0001001 / 21 MAR 16
HUD
Ident.: GEN-IFIT-00016651.0002001 / 23 JUN 15
IRS Alignment Based on GPS Position
Ident.: GEN-IFIT-00015618.0002001 / 23 JUN 15
ISIS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
GEN P 12/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00020693.0001001 / 17 MAR 17
L13
ITP
ATSA ITP
ITP TRAFFIC LIST page
IN TRAIL PROCEDURE
IN TRAIL PROCEDURE page
Ident.: GEN-IFIT-00016594.0002001 / 23 JUN 15
LAF
SURV
No
F/CTL
No
NAV
No
AUTO FLT
No
LIGHTS
Yes
SURV
Yes
WATER
Yes
WATER
Yes
EIS
No
AUTO FLT
No
AUTO FLT
No
Ident.: GEN-IFIT-00016596.0001001 / 21 MAR 16
L13
LAT DEV SCALE pb
L/DEV deviation scale
Ident.: GEN-IFIT-00016600.0001001 / 23 JUN 15
LOC B/C
Ident.: GEN-IFIT-00016602.0002001 / 21 MAR 16
L13
Logo Light
LOGO
Logo Lights
Ident.: GEN-IFIT-00020306.0001001 / 17 MAR 17
Man-made Obstacle Function
Ident.: GEN-IFIT-00016604.0002001 / 23 JUN 15
Manual Flush Control
Ident.: GEN-IFIT-00016605.0002001 / 21 MAR 16
Manual Shutoff Valves
Ident.: GEN-IFIT-00016688.0001001 / 23 JUN 15
Metric Altitude Indications on the PFD
Ident.: GEN-IFIT-00016536.0001001 / 21 MAR 16
L13
MLS
MLS1
MLS2
Ident.: GEN-IFIT-00016603.0001001 / 23 JUN 15
NAV Mode automatically Engaged (Armed) in Go-Around
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GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00016645.0002001 / 23 JUN 15
OEB Reminder
EIS
Yes
FANS
No
DOORS
Yes
BRAKE
No
SURV
Yes
AUTO FLT
Yes
AUTO FLT
Yes
SURV
Yes
RECORDING
No
Ident.: GEN-IFIT-00021528.0001001 / 17 MAR 17
Optional Applications:
DCL
OCL
D-ATIS
Ident.: GEN-IFIT-00016597.0003001 / 21 MAR 16
L13
2 Pairs of Overwing Emergency Exit
Overwing Escape Route
FWD EMER EXIT
Ident.: GEN-IFIT-00016538.0001001 / 21 MAR 16
L13
Parking Brake Monitoring
PARK BRK FAULT
Ident.: GEN-IFIT-00021553.0002001 / 17 MAR 17
Predictive GPWS
Ident.: GEN-IFIT-00016608.0002001 / 22 MAR 16
L13
Printer Function in FMS
PRINT FUNCTION
PRINTER NOT AVAILABLE
Ident.: GEN-IFIT-00016609.0002001 / 21 MAR 16
Push to Level Off
Ident.: GEN-IFIT-00016648.0002001 / 17 MAR 17
L13
PWS
Windshear DET
WINDSHEAR DETECTION
PRED W/S DET FAULT
W/S AHEAD
WINDSHEAR AHEAD
Windshear
PRED W/S DET
predictive windshear system
PWS SCAN
Ident.: GEN-IFIT-00016695.0001001 / 23 JUN 15
QAR
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GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00016643.0001001 / 21 MAR 16
L13
QFE BARO Setting
QFE OPTION
Ident.: GEN-IFIT-00016610.0001001 / 23 JUN 15
RAAS
NAV
No
SURV
No
RAIN
Yes
COM
No
NAV
No
SURV
No
CAB PR
Yes
COM
No
SMOKE
No
FIRE
No
Ident.: GEN-IFIT-00016539.0003001 / 21 MAR 16
L13
Rain Repellent System
Rain Repellent
RAIN RPLNT pb
RAIN RPLNT
Ident.: GEN-IFIT-00016737.0001001 / 23 JUN 15
RMP Load Function
Ident.: GEN-IFIT-00016581.0001001 / 23 JUN 15
RNP pb
Ident.: GEN-IFIT-00016582.0001001 / 21 MAR 16
L13
ROW / ROPS
ROW /ROP
Ident.: GEN-IFIT-00016583.0002001 / 23 JUN 15
RPCU
Ident.: GEN-IFIT-00016642.0001001 / 22 MAR 17
L13
SATCOM
SATCOM DATA FAULT
SATCOM FAULT
Satellite Communications (SATCOM)
SATCOM System
Ident.: GEN-IFIT-00016646.0001001 / 17 MAR 17
L13
SDCU
Smoke Detection Control Unit SDCU
Ident.: GEN-IFIT-00016584.0001001 / 23 JUN 15
Second Fire Extinguishing Bottle
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←B→
GEN P 15/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Ident.: GEN-IFIT-00018784.0001001 / 22 MAR 17
L13
Soft Go-Around
SOFT GA
Go-Around soft
ENG
No
NAV
No
SURV
No
SURV
No
EIS
No
COND
Yes
ENG
No
WHEEL
No
SURV
No
EIS
No
RAIN
No
Ident.: GEN-IFIT-00018785.0001001 / 21 MAR 16
L13
Steep Approach Capability
STEEP APPR
Ident.: GEN-IFIT-00016586.0001001 / 23 JUN 15
T2CAS
Ident.: GEN-IFIT-00016587.0001001 / 23 JUN 15
T3CAS
Ident.: GEN-IFIT-00016588.0001001 / 21 MAR 17
L13
Tail Strike Pitch Limit Indicator
Tailstrike Pitch Limit Indicator
Ident.: GEN-IFIT-00018786.0002001 / 21 MAR 16
Temperature Control Panel
Ident.: GEN-IFIT-00016541.0001001 / 23 JUN 15
Thrust Bump
Ident.: GEN-IFIT-00016011.0001001 / 21 MAR 16
L13
TPIS
TYRE LO PR
Ident.: GEN-IFIT-00017055.0001001 / 17 MAR 17
HZD switch ON
Weather Hazard Prediction Function
WX+T+H
WX+T+HZD
Ident.: GEN-IFIT-00020783.0001001 / 20 DEC 16
Weight and Balance System (WBS)
Ident.: GEN-IFIT-00016543.0001001 / 21 MAR 16
L13
Wiper Intermittent Position
Intermittent Sweep Function
Intermittent Sweeping
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FCOM
←B
GEN P 16/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
MAIN FCOM CHANGES
Ident.: GEN-00012867.0001001 / 03 AUG 17
Applicable to: ALL
The purpose of the Main FCOM Changes is to provide operators with general information about the
most significant changes that are introduced in the current revision of the manual.
The main FCOM changes are available on the Airbus World portal, under the path: Content Library /
Flight Operations / Manuals / Main FCOM - FCTM - MMEL Changes.
In addition, every revised Documentary Unit (DU) has a revision highlight (HL) that:
‐ Indicates the change(s) made to the DU
‐ Can be found in the associated “Preliminary Pages – Summary of Highlights” subchapter.
In addition to the Main FCOM Changes, the Modification Operational Impact (MOI ) documents
available on the Airbus World portal provide the operational impact linked to a MOD number.
FCOM PURPOSE
Ident.: GEN-00012627.0001001 / 17 MAR 17
Applicable to: ALL
FCOM PURPOSE
The Flight Crew Operating Manual (FCOM) is a support documentation for flight crew.
The purpose of the FCOM is to:
‐ Provide all necessary operating limitations, procedures, performance and system information
the flight crew needs to safely and efficiently operate A320 family aircraft during normal,
abnormal, and emergency situations
‐ Serve directly as Flight Crew Operating Manual, or as a basis for Operators to develop their
own customized Airline Operations Manual, in accordance with applicable requirements
‐ Serve as a comprehensive reference guide during initial and refresher flight crew training.
Note:
This manual is not designed:
‐ To teach basic piloting skills
‐ To provide basic piloting techniques applicable to jet aircraft, or information, that are
considered as basic airmanship for trained flight crews who are familiar with that type
of aircraft and its general handling characteristics.
The Flight Crew Operating Manual (FCOM ) complements the Airplane Flight Manual (AFM).
If the FCOM data differs from the AFM data, the AFM remains the reference.
As a supplement to the FCOM , the FCTM may provide additional information that the flight
crew should read in conjunction with the FCOM. For more information, Refer to FCTM/GI FCTM
Purpose.
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GEN P 17/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
For any questions or comments related to this manual, the Operator’s Flight Operations
Management can contact the Airbus Flight Operations Support & Training Standards department.
FCOM CONTENTS
The FCOM has five sections:
‐ Aircraft Systems
: This section is divided into ATA chapters for each aircraft system.
This section includes a specific description of each system and its
associated cockpit interfaces.
‐ Procedures
: This section contains the following chapters:
‐ Normal Procedures that include the SOP , the SRP, and the
Supplementary Procedures
‐ Abnormal and Emergency Procedures
‐ Special Operations.
‐ Limitations
:
This section provides the aircraft and system limitations that the
flight crew must know or refer to in operations.
‐ Operations Engineering Bulletins (OEB)
‐ Performance
: This section includes the aircraft performance for each flight phase.
DOCUMENTARY UNITS
The FCOM is made of Documentary Units (DU ). The DU is the smallest part of information with a
technical content.
The DUs are listed on a separate "List of Effective Documentary Units" (LEDU). Refer to the
General section.
Note:
1. DU s can be grouped into Group of DU (GDU)
2. Temporary information may be provided via Temporary DU (TDU).
IDENTIFICATION STRIP
Below the title of the DU, the identification strip provides:
‐ The list of MSN the DU is applicable to
‐ For TDU , the reference to the DU impacted by the TDU.
LIST OF EFFECTIVE SECTIONS/SUBSECTIONS (LESS) - PAPER ONLY
Ident.: GEN-00013786.0001001 / 23 JUN 15
Applicable to: ALL
The List of Effective Sections/Subsections (LESS ) summarizes all the sections and subsections
contained in the FCOM . For each revision, a new LESS is issued when at least one DU of the
section/subsection is changed.
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GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
The LESS consists of:
‐ The "M" field that may provide the following evolution code:
•
•
•
•
The "N" letter indicates a new section introduced by the revision
The "R" letter indicates a section in which the content has been revised
The "E" letter indicates an aircraft validity change within the section
The "M” letter indicates a section that have move within the FCOM
‐ The “Localization” field that allows localizing the section within the manual with the product
structure
‐ The “Subsection title” field
‐ The “Rev. Date” field that indicated the date at which the section was changed.
LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETINS (LEOEB)
Ident.: GEN-00013787.0001001 / 17 MAR 17
Applicable to: ALL
Refer to OEB-GEN OEB Content and Management
LIST OF EFFECTIVE DOCUMENTARY UNITS (LEDU) - PAPER ONLY
Ident.: GEN-00013789.0001001 / 23 MAR 11
Applicable to: ALL
For each revision, a new List of Effective Documentary Units (LEDU ) is issued at the section level.
The LEDU provides information about the DU localization, applicability, identification and issue date.
The LEDU consists of:
‐ The "M" field that may provide the following Evolution Code:
• The "N" letter indicates a new DU introduced by the revision
• The "R" letter indicates a revised DU: The content of the DU is updated by the revision. A
vertical line in the margin of the DU locates the modified part
• The "E" letter indicates an aircraft validity change for the DU: The list of MSNs for which the DU
is effective has been changed compared to the previous LEDU, by addition or deletion of one or
several MSN
‐ The “Localization” field that allows localizing the DU in the manual with the product structure of the
manual
‐ The "T" field (Temporary Information) that contains a cross if the associated DU is a TDU
‐ The "DU title" that provides the title of the DU
‐ The “DU identification” that identifies the DU with its own unique identification number or the GDU
with its own unique code.
‐ The “DU date” that indicates when the DU has been released
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GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
‐ The DU criteria which lists the technical or operational criteria for which the DU and solution is
applicable to.
‐ The “Applicable to” which provides the list of aircraft this DU and solution is applicable to
‐ The “Impacted by TDU” which is the identification of the TDU superseding the DU
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS (LETDU) - PAPER ONLY
Ident.: GEN-00013803.0001001 / 23 JUN 15
Applicable to: ALL
The List of Effective Temporary Documentary Units (LETDU) provides a summary of the Temporary
DU impacting the section.
The LETDU consists of:
‐ The "M" field that may provide the following Evolution Code:
• The "N" letter indicates a new TDU introduced by the revision
• The "R" letter indicates a revised TDU: The content of the TDU is updated by the revision. A
vertical line in the margin of the TDU locates the modified part
• The "E" letter indicates an aircraft validity change for the TDU: The list of MSNs the TDU is
applicable to has been changed compared to the previous LETDU, by addition or deletion of
one or several MSN
‐ The “Localization” field that allows localizing the TDU in the manual with the product structure of
the manual
‐ The “TDU Title” that provides the title of the TDU
‐ The “TDU identification” that identifies the TDU with its identification number with its own unique
code
‐ The “TDU date” that indicates when the TDU has been released
‐ The TDU criteria which lists the technical or operational criteria, the it is applicable to
‐ The “Applicable to” which provides the list of aircraft this TDU is applicable to
‐ The “Impacted DU” which is the Identification of DU superseded by the TDU
‐ The “Reason for issue” of the TDU
Note:
1. TDU is displayed on a yellow background
2. within the QRH the TDU replaces the impacted DU
AIRCRAFT ALLOCATION TABLE (AAT) - PAPER ONLY
Ident.: GEN-00013804.0001001 / 23 JUN 15
Applicable to: ALL
The Aircraft Allocation Table (AAT ) provides a view of the fleet covered in the FCOM . For each
aircraft, the AAT provides its MSN, its registration number and the model.
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GEN P 20/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
LIST OF MODIFICATIONS (LOM) - PAPER ONLY
Ident.: GEN-00013805.0001001 / 23 JUN 15
Applicable to: ALL
The List of Modifications (LOM) lists the criteria (Modification Proposal (MP ) or Service Bulletins (SB
)) which the installation on the aircraft affects the FCOM.
Note:
Each MP has one or more associated MODs. The MP/MOD correlation is available in
AirN@v / Engineering.
The LOM also indicates:
‐ The title of the criteria
‐ The date of incorporation of the criteria in the FCOM
‐ The list of aircraft that have the criteria
‐ The "M" field that may indicate the following evolution code
‐ The "E" letter indicates an aircraft validity change of the criteria. The list of aircraft to which the
criteria applies has changed compared to the previous FCOM revision, by addition or deletion of
one or several aircraft.
‐ The "N" letter indicates new criteria added by this FCOM revision
‐ The "R" letter indicates a change in the criteria title or associated SB
FCOM USE AND ORGANIZATION
Ident.: GEN-00012688.0001001 / 21 MAR 16
Applicable to: ALL
DEFINITIONS OF WARNINGS, CAUTIONS AND NOTES
The following are the official definitions of warnings, cautions and notes taken directly from the
JAR25/CS-25 and applicable to Airbus flight operation documentation:
WARNING
An operating procedure, technique, etc. that may result in personal injury or
loss of life if not followed.
CAUTION
An operating procedure, technique, etc. that may result in damage to
equipment if not followed.
NOTE
An operating procedure, technique, etc. considered essential to emphasize.
Information contained in notes may also be safety related.
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J to K →
GEN P 21/48
05 SEP 17
GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
INFORMATION TYPE AND LAYERS
The FCOM has technical information that may be used for:
‐ Flight crew operations in flight, or on ground
‐ Airlines operations on ground
‐ Training.
To take the above-noted objectives into account, the FCOM is organized in three layers as follows:
‐ Layer 1: "Need to know"
Layer 1 presents information that is necessary in the cockpit.
‐ Layer 2: "Nice to know"
Layer 2 presents information that is used as a reference, in order to fully understand the logic of
the aircraft and pilot interfaces.
‐ Layer 3: Detailed information
Layer 3 provides more detailed explanations, that are not necessarily needed in flight.
Note:
For paper only, the following examples show the visual characteristics of each kind of
layer
EXAMPLE
L2
EXAMPLE
L3
EXAMPLE
L1
EXAMPLE
‐ Text in layer 1
Layer 1 is the default layer. No symbology when not following layer 2 or layer 3
information.
‐ Text in layer 2
‐ Text in layer 3
‐ Text in layer 1 (as this text follows a text in layer 2 or 3, symbology "L1")
OPTIONAL EQUIPMENT
The legend (if installed) indicates that a paragraph or an illustration is applicable only if the
related optional equipment is installed.
FCOM FORMAT AND STYLE INFORMATION - PAPER ONLY
Ident.: GEN-00013793.0001001 / 21 MAR 16
Applicable to: ALL
TABLE OF CONTENTS
Each TOC entry has an alphabetical index that identifies this TOC entry within its subsection. The
manual user can easily find a TOC entry content within the manual thanks to this alphabetical
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GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
index and the subsection identification. Both are indicated in the TOC and both cross-refer to the
paper page footer (see the TOC indexing part below).
HEADER AND FOOTER
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GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
1. Airline logo
2. Aircraft types and manual
3. Level 2 chapter (PSL level 2 : GEN, DSC, PRO, LIM, OEB, PER)
4. Level 3 chapter
5. Level 4 chapter
6. Revision mark
7. Key product (document identification and aircraft designation)
8. Key product (manual code)
9. Page index
10. Last evolution date
11. Identification strip (list of impacted aircraft)
12. PSL path
REVISION MARK
In the paper format, a vertical bar in the margin of the DU identifies the modified part. Each
vertical bar has a numerical index that refers to the associated reason of the change in the
Summary of Highlight.
This Summary of Highlight lists all the changes and associated reasons of the change (if
necessary) that the revision has introduced.
TOC INDEXING
In the paper page footer, the TOC indexing is of the following type:
A
: The paper page contains the whole "A" TOC entry content
A to B
: The paper page contains the whole "A" and "B" TOC entries contents
A→
: The "A" TOC entry content starts on this paper page and continues on
the following paper page
←A
: The "A" TOC entry content starts on a previous paper page and finishes
on this paper page
←A→
: The "A" TOC entry content starts on a previous paper page and
continues on the following paper page
A to C→
: The paper page contains the whole "A" and "B" TOC entries contents
but the "C" TOC entry content starts on this paper page and continues
on the following paper page
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GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
← A to C
:
← A to C →
:
Note:
The paper page contains the whole "B" and "C" TOC entries contents
but the "A" TOC entry content starts on a previous paper page and
finishes on this paper page
The paper page contains the whole "B" TOC entry content but the "A"
TOC entry content starts on a previous paper page and finishes on this
paper page and the "C" TOC entry content starts on this paper page and
continues on the following paper page
1. The indexes follow the alphabetical order: A, B, C, ..., Z, AA, AB, AC, ..., AZ, BA,
BB, BC, ...
2. For each subsection, the index starts again from A.
3. When a TOC entry content continues on the following paper page, the text
"Continued on the following page" is also indicated.
FCOM REVISIONS
Ident.: GEN-00012634.0001001 / 24 OCT 14
Applicable to: ALL
FCOM REVISION
FCOM revisions are issued to add, update, or revise information. The Operator determines the
revision periodicity.
When necessary, a revision may be issued in between the defined periodicity (e.g. need for urgent
update).
A vertical bar appears to the left of all revised parts of the manual.
TEMPORARY INFORMATION
Some FCOM sections may need a temporary update (e.g. to explain a system behavior that will
be modified by a future standard). In such cases, the applicable FCOM section is updated with a
Temporary Documentary Unit (TDU).
Information contained in the TDU is highlighted in the manual and the initial content of the FCOM
remains available for consultation and comparison and is highlighted (identification strip) as being
impacted by the TDU.
A List of Effective Documentary Units (LEDU ) is provided in the FCOM
OPERATIONS ENGINEERING BULLETINS
Operations Engineering Bulletins (OEB) are issued, when it is necessary, to rapidly transmit
technical and procedural information.
The OEB chapter provides a list of all applicable OEBs.
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GENERAL INFORMATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ABBREVIATIONS
Ident.: GEN-00012598.0001001 / 05 SEP 17
Applicable to: ALL
A
Abbreviation
A>B
A≥B
A 1 750 ft/min (resets at 1 650 ft/min).
(4)
ΔP PSI (cabin differential pressure)
The analog and digital presentations appear in green when ΔP is in the normal range.
They appear in amber when ΔP ≤ –0.4 PSI or ≥ 8.5 PSI.
The digital presentation pulses if Δp > 1.5 PSI (resets at 1 PSI) during flight phase 7. (Refer to
DSC-31-15 Flight Phases).
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DSC-21-20-40 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRESSURIZATION - CONTROLS AND INDICATORS
(5)
CAB ALT FT (cabin altitude)
The analog and digital presentations appear in green, in normal range.
They appear in red if the cabin altitude goes above 9 550 ft.
The digital presentation pulses if the cabin altitude is at or above 8 800 ft (resets at 8 600 ft).
(6)
Active system indication (SYS 1 or SYS 2 or MAN)
SYS 1 or SYS 2 appears in green when active and in amber when faulty. When either system
is inactive, its title does not appear.
MAN appears in green when the MODE SEL switch is in MAN.
(7)
Safety valve position
SAFETY appears in white and the diagram in green when both safety valves are fully closed.
SAFETY and the diagram appear in amber when either valve is not closed.
Note:
(8)
The safety valve opens when the cabin differential pressure is between 8.2 and
8.9 PSI. The range is due to the reduced accuracy of ΔP measurements (in MAN
mode), combined with the decrease in cabin differential pressure that occurs
immediately after the safety valves open.
Outflow valve position
The diagram is green when the valve is operating normally.
The diagram becomes amber when the valve opens more than 95 % during flight.
ECAM CRUISE PAGE
Ident.: DSC-21-20-40-00000336.0002001 / 09 OCT 12
Applicable to: ALL
(1)
LDG ELEV AUTO/MAN
Identifical to the CAB PRESS page
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← B to C →
DSC-21-20-40 P 4/6
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRESSURIZATION - CONTROLS AND INDICATORS
(2)
CAB V/S FT/MIN (cabin vertical speed)
Green, in normal range.
Pulses, when the V/S > 1 750 ft/min (resets at 1 650 ft/min).
(3)
CAB ALT FT (cabin altitude)
Green, in normal range.
Red, for excessive cabin altitude : ≥ 9 550 ft.
Pulses for cabin altitude at, or above, 8 800 ft (resets at 8 600 ft).
(4)
ΔP indication
It is normally green. Pulses green when CAB ΔP ≥ 1.5 PSI before landing.
It becomes amber, when out of normal range Δp ≤ -0.4 PSI or ≥ 8.5 PSI.
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←C
DSC-21-20-40 P 5/6
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
PRESSURIZATION - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
ECAM DOOR/OXY PAGE
Ident.: DSC-21-20-40-00000337.0003001 / 21 MAR 16
Applicable to: ALL
(1)
V/S (cabin vertical speed)
This number only appears during flight phases 5, 6 and 7. (Refer to DSC-31-15 Flight Phases
for flight phase definitions).
‐ It is normally green.
‐ It pulses, when the V/S is greater than 1 750 ft/min and stops pulsing, when less than
1 650 ft/min.
‐ It becomes amber, when the V/S is greater than 2 000 ft/min, or less than -2 000 ft/min.
MEMO DISPLAY
Ident.: DSC-21-20-40-00016761.0001001 / 21 MAR 16
Applicable to: ALL
MAN LDG
ELEV
:
This memo appears in green, if the LDG ELEV knob is not in the AUTO position.
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D to E
DSC-21-20-40 P 6/6
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
VENTILATION - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-21-30-10-00017790.0001001 / 21 MAR 16
Applicable to: ALL
The ventilation system includes ventilation for:
‐ The avionics, controlled by the Avionics Equipment Ventilation Controller (AEVC),
‐ The batteries,
‐ The lavatories and galleys.
Note:
For more information about cargo ventilation , Refer to DSC-21-40-10 General.
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A
DSC-21-30-10 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
VENTILATION - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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DSC-21-30-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
VENTILATION - AVIONICS VENTILATION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-21-30-20-00000341.0001001 / 24 FEB 11
Applicable to: ALL
The avionics ventilation system is fully automatic.
It cools the electrical and electronic components in the avionics compartment and on the flight deck,
including the instrument and circuit breaker panels. It uses two electric fans to force the circulation of
cooling air.
Whatever the configuration of the avionics ventilation system is, a part of the avionics ventilation air
is sucked from the cockpit through the different cockpit panels.
MAIN COMPONENTS
Ident.: DSC-21-30-20-00017791.0001001 / 21 MAR 16
Applicable to: ALL
FANS
Two electric fans continuously circulate air around the avionics equipment, when the aircraft is
electrically supplied.
The Fan Speed Controller (FSC) controls the avionics ventilation fan speed as a function of
temperature::
1. High speed when the ventilation air temperature is above +40 °C (104 °F )
2. Low speed when the ventilation air temperature is below +35 °C ( 95 °F)
SKIN AIR INLET AND OUTLET VALVES
These valves admit air from outside the aircraft and evacuate hot air from the avionics equipment.
SKIN EXCHANGE INLET AND OUTLET BYPASS VALVES
These valves enable air to circulate between the avionics bay and the space under the cargo
compartment floor.
AIR CONDITIONING INLET VALVE
This valve opens to enable the air conditioning circuit to supply fresh air to the avionics bay.
SKIN EXCHANGE ISOLATION VALVE
This valve connects or isolates the skin heat exchanger.
AVIONICS EQUIPMENT VENTILATION CONTROLLER (AEVC)
The AEVC controls the operation of all fans and valves in the avionics ventilation system.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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DSC-21-30-20 P 1/8
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
VENTILATION - AVIONICS VENTILATION
NORMAL OPERATION, OPEN-CIRCUIT CONFIGURATION
Ident.: DSC-21-30-20-00000343.0001001 / 16 APR 14
Applicable to: ALL
GROUND OPERATIONS
The open-circuit configuration operates when skin temperature is above the on-ground threshold.
On-ground threshold = +12 °C (53 °F), temperature increasing, or
+9 °C (48 °F), temperature decreasing.
(*)
Note:
In some cases, the opening of the skin air valves can be delayed even if the skin
temperature is above the on-ground thresholds: This is to avoid condensation
phenomenon when the temperature inside the avionic compartment is too cold.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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C
DSC-21-30-20 P 2/8
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
VENTILATION - AVIONICS VENTILATION
NORMAL OPERATION, CLOSE-CIRCUIT CONFIGURATION
Ident.: DSC-21-30-20-00000345.0001001 / 09 OCT 12
Applicable to: ALL
FLIGHT OPERATIONS
The close-circuit configuration operates when skin temperature is beneath the in-flight threshold.
In flight threshold
= +35 °C (95 °F), temperature increasing, or
+32 °C (90 °F), temperature decreasing.
GROUND OPERATIONS
The close-circuit configuration operates when skin temperature is beneath the on-ground
threshold.
On ground threshold = +12 °C (53 °F), temperature increasing, or
+9 °C (48 °F), temperature decreasing.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
VENTILATION - AVIONICS VENTILATION
NORMAL OPERATION, INTERMEDIATE CONFIGURATION
Ident.: DSC-21-30-20-00000344.0001001 / 09 OCT 12
Applicable to: ALL
FLIGHT OPERATIONS
The intermediate configuration operates when skin temperature is above the in-flight threshold.
In flight threshold
= +35 °C (95 °F), temperature increasing, or
+32 °C (90 °F), temperature decreasing.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
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24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
VENTILATION - AVIONICS VENTILATION
The measuring range of the skin temperature sensed is between -50 °C and 80 °C.
Outside of this range, the AEVC sets the avionics ventilation configuration to the
intermediate configuration (partially open) until the temperature is within the operation
range again.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
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AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
VENTILATION - AVIONICS VENTILATION
FLIGHT CREW
OPERATING MANUAL
ABNORMAL OPERATION
Applicable to: ALL
Ident.: DSC-21-30-20-A-00000346.0001001 / 20 JAN 15
BLOWER FAULT OR EXTRACT FAULT ALERT
When the BLOWER or the EXTRACT pushbutton switch is set at the OVRD (override) position,
the system is in closed-circuit configuration and adds air from the air conditioning system to the
ventilation air.
When the BLOWER pushbutton switch is set at OVRD, the blower fan is stopped and the extract
fan continues to run.
When the EXTRACT pushbutton switch is set at OVRD, the extract fan is controlled directly from
the pushbutton. Both fans continue to run.
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AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
VENTILATION - AVIONICS VENTILATION
Ident.: DSC-21-30-20-A-00000347.0001001 / 09 OCT 12
SMOKE CONFIGURATION
When the smoke detector detects smoke in the avionics ventilation air the BLOWER and the
EXTRACT FAULT lights come on.
When both the BLOWER and the EXTRACT pushbuttons are set to the OVRD position, the air
conditioning system supplies cooling air, which is then exhausted overboard. The blower fan
stops.
Ident.: DSC-21-30-20-A-00000348.0001001 / 21 MAR 16
CONTROLLER FAILURE
The system goes to the same configuration as above, except that the skin exchange isolation
valve stays open.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
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AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
VENTILATION - AVIONICS VENTILATION
The inlet valve and the skin exchange inlet bypass valve remain in the position they were in before
the failure occurred.
The extract fan keeps running.
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FCOM
←F
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AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
VENTILATION - BATTERY VENTILATION
FLIGHT CREW
OPERATING MANUAL
BATTERY VENTILATION
Ident.: DSC-21-30-40-00000350.0001001 / 21 MAR 16
Applicable to: ALL
A venturi in the skin of the aircraft draws air from the space around the batteries and vents it
overboard. The resulting airflow ventilates the batteries.
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FCOM
A
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AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
VENTILATION - BATTERY VENTILATION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
VENTILATION - LAVATORY AND GALLEY VENTILATION
LAVATORY AND GALLEY
Ident.: DSC-21-30-50-00000351.0001001 / 09 OCT 12
Applicable to: ALL
An extraction fan draws ambient cabin air through the lavatories and galleys and exhausts it near the
outflow valve.
The extraction fan runs continually when electric power is available.
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A
DSC-21-30-50 P 1/2
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AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
VENTILATION - LAVATORY AND GALLEY VENTILATION
Intentionally left blank
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24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
VENTILATION - CONTROLS AND INDICATORS
OVERHEAD PANEL
Ident.: DSC-21-30-60-00000352.0001001 / 24 FEB 11
Applicable to: ALL
(1)
BLOWER pb-sw and EXTRACT pb-sw
AUTO: : When both pushbutton switches are on AUTO:
‐ On the ground before the application of TO power, the ventilation system is in
open circuit configuration (closed configuration when the skin temperature is
below the ground threshold).
‐ On the ground after the application of TO power, and in flight, the ventilation
system is in closed circuit configuration.
OVRD: : When either pushbutton switch is on OVRD:
‐ The system goes to closed circuit configuration.
‐ Air from the air conditioning system is added to ventilation air. (The blower fan
stops if the BLOWER pushbutton switch is in the OVRD position).
When both pushbutton switches are on OVRD:
‐ Air flows from the air conditioning system and then overboard.
‐ The extract fan continues to run.
FAULT : Lights up amber (and ECAM activates)
lt:
in the blower switch, if : ‐ blowing pressure is low (See *)
‐ duct overheats (See *)
‐ computer power supply fails
‐ smoke warning is activated
in the extract switch, if : ‐ extract pressure is low (See *)
‐ computer power supply fails
‐ smoke warning is activated.
*
If the warning occurs on the ground when the engines are stopped, the
external horn sounds.
(2)
Refer to DSC-21-10-50 Controls on Overhead Panel
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-21-30-60 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
VENTILATION - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
ECAM CAB PRESS PAGE
Ident.: DSC-21-30-60-00000353.0003001 / 03 APR 13
Applicable to: ALL
(1)
BLOWER, VENT and EXTRACT Indications
VENT message normally appears in white. It becomes amber, if there is a BLOWER FAULT,
EXTRACT FAULT, or AVNCS SYS FAULT.
BLOWER message appears in amber if there is a BLOWER FAULT.
EXTRACT message appears in amber if there is an EXTRACT FAULT.
(2)
INLET and OUTLET Indications
Normally white. The corresponding indication becomes amber, when the inlet valve or the
outlet valve is failed.
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AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(3)
VENTILATION - CONTROLS AND INDICATORS
INLET and OUTLET Valve Diagrams
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-21-30-60 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
VENTILATION - CONTROLS AND INDICATORS
Intentionally left blank
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AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
CARGO - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-21-40-10-00017795.0001001 / 21 MAR 16
Applicable to: ALL
CARGO VENTILATION
An extraction fan draws air from forward cargo compartment or aft cargo compartment, and
exhausts it overboard. Air from the cabin replaces the exhausted air, thus ventilating the cargo
compartments.
CARGO TEMPERATURE REGULATION
The system can mix hot bleed air with the air coming from the cabin, therefore giving the flight
crew control of the temperature in the forward or aft cargo compartment.
SCHEMATIC
Ident.: DSC-21-40-10-00000357.0001001 / 22 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-21-40-10 P 1/2
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AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
CARGO - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
CARGO - SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
FWD CARGO VENTILATION
Ident.: DSC-21-40-20-00017796.0001001 / 21 MAR 16
Applicable to: ALL
Air from the cabin goes via the inlet isolation valve to the forward cargo compartment, driven either
by an extraction fan or by differential pressure in flight. A skin-mounted venturi discharges the air
overboard via the outlet isolation valve. The cargo ventilation controller controls the operation of the
inlet and outlet isolation valves and the extraction fan.
The ventilation system operates in two modes:
‐ On the ground or when ▵P ≤ 1 PSI in flight, the controller opens the isolation valves, then starts
the extraction fan
‐ In flight when ▵P > 1 PSI, the controller stops the fan, and differential pressure maintains the
ventilation.
The controller closes the isolation valves and stops the extraction fan when:
‐ The flight crew sets the FWD ISOL VALVE pb-sw to OFF, or
‐ The forward cargo smoke detection unit detects smoke.
The outlet valve closes and the extraction fan stops when the flight crew sets the DITCHING pb-sw
to ON.
AFT CARGO VENTILATION
Ident.: DSC-21-40-20-00017797.0001001 / 21 MAR 16
Applicable to: ALL
Air from the cabin goes via the inlet isolation valve to the aft cargo compartment, driven by an
extraction fan. Air is controlled by the outlet isolation valve and then goes outboard through the
outflow valve.
The cargo ventilation controller controls the operation of the inlet and outlet isolation valves and the
extraction fan.
When the isolation valves are fully open, the extraction fan operates continuously when the aircraft is
on the ground and during flight.
The controller closes the isolation valves and stops the extraction fan when:
‐ The flight crew sets the AFT ISOL VALVE pb-sw to OFF, or
‐ The aft cargo smoke detection unit detects smoke.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-21-40-20 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
CARGO - SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
AFT CARGO HEATING
Ident.: DSC-21-40-20-00017798.0001001 / 21 MAR 16
Applicable to: ALL
The ventilation system for the aft cargo compartment uses hot engine bleed air (upstream of the
packs), mixing it with the ambient cabin air that flows through the cargo compartment.
The cargo regulating valve regulates the pressure of this hot air supply, and the trim air valve, which
is modulated electrically by the controller, controls the flow.
The cargo pressure regulating valve is pneumatically operated and electrically controlled from the
HOT AIR pb on the CARGO HEAT panel.
The hot air is controlled by the cargo trim air valve which is modulated electrically by the controller.
The hot air is then mixed with air from the cabin and supplied to the cargo compartment through the
ventilation inlet isolation valve.
According to the temperature selector demand, the controller regulates the amount of hot air added
by the trim air valve, until the desired temperature is reached.
If the inlet temperature exceeds 70 °C, the controller closes the trim air valve.
If the inlet temperature exceeds 88 °C, the controller interprets this as a duct overheat and closes the
pressure regulating valve. This valve then remains closed until the flight crew resets the system by
pressing the HOT AIR pb — which it cannot do until the temperature drops below 70 °C.
FWD CARGO HEATING
Ident.: DSC-21-40-20-00017799.0001001 / 21 MAR 16
Applicable to: ALL
The ventilation system for the forward cargo compartment uses hot engine bleed air, which is also
used for cockpit and cabin temperature control, mixing it with the ambient cabin air that flows through
the cargo compartment.
The cockpit and cabin hot air pressure regulating valve regulates the pressure of this hot air supply,
and the cargo trim air valve, which is modulated electrically by the controller, controls the flow.
The hot air mixes with air from the cabin as it supplied to the cargo compartment through the
ventilation inlet isolation valve.
The controller regulates the amount of hot air added by the trim air valve to get the desired
temperature, per the temperature selector.
If the inlet temperature exceeds 70 °C, the controller closes the trim air valve. If the inlet temperature
reaches 88 °C, the controller interprets this as a duct overhead and closes the pressure regulating
valve. This valve then remains closed until the flight crew resets the system by pressing the HOT AIR
pb - which it cannot do until the temperature drops below 70 °C.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D
DSC-21-40-20 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
CARGO - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-21-40-30-00017800.0001001 / 20 MAR 17
Applicable to: ALL
(1)
FWD ISOL VALVE pb-sw
The switch controls the forward isolation valves and the extraction fan.
Auto
: The inlet and outlet isolation valves open, extraction fan runs if there is no smoke
detected in the fwd cargo bay.
OFF
: The inlet and outlet isolation valves and the trim air valve close, the extraction fan
stops.
FAULT lt : The light, associated with the ECAM caution, comes on amber when either inlet
or outlet valve is not in the selected position.
(2)
AFT ISOL VALVE pb-sw
The switch controls the isolation valves and the extraction fan.
Auto
: The inlet and outlet isolation valves open, extraction fan runs if there is no smoke
detected in the aft cargo bay.
OFF
: The inlet and outlet isolation valves and the trim air valve close, the extraction fan
stops.
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A→
DSC-21-40-30 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FAULT lt :
CARGO - CONTROLS AND INDICATORS
The light, associated with the ECAM caution, comes on amber when either inlet
or outlet valve is not in the selected position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-21-40-30 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
AIR CONDITIONING / PRESSURIZATION / VENTILATION
A318/A319/A320/A321
CARGO - ECAM COND PAGE
FLIGHT CREW
OPERATING MANUAL
ECAM COND PAGE
Ident.: DSC-21-40-35-00006005.0009001 / 22 MAY 12
Applicable to: ALL
(1)
Zone indication
It is white.
(2)
Inlet isolation valve
In line – Green
Crossline – Amber
:
:
Valve is open.
Valve is closed.
(3)
Outlet isolation valve
Crossline – Green :
In line – Amber
:
Valve is open.
Valve is closed.
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A
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
CARGO - ECAM COND PAGE
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
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AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_10-10 Description
FMGC Standard.......................................................................................................................................................A
Preamble.................................................................................................................................................................. B
Description............................................................................................................................................................... C
General Philosophy................................................................................................................................................. D
Flight Management Guidance Computer (FMGC).................................................................................................. E
Multipurpose Control and Display Unit (MCDU)......................................................................................................F
Flight Control Unit (FCU)........................................................................................................................................ G
Flight Augmentation Computer (FAC).....................................................................................................................H
Other Flight Crew Interfaces.....................................................................................................................................I
Flight Crew Interface with FMGC............................................................................................................................ J
DSC-22_10-20 System Interface Diagram
System Interface Diagram....................................................................................................................................... A
DSC-22_10-30 FMGS Modes of Operation
General.....................................................................................................................................................................A
Dual Mode................................................................................................................................................................B
Independent Mode...................................................................................................................................................C
Single Mode.............................................................................................................................................................D
Back Up Navigation Mode.......................................................................................................................................E
DSC-22_10-40 Pilot Interface
DSC-22_10-40-05 Management of the Displays
General.....................................................................................................................................................................A
DSC-22_10-40-10 MCDU
MCDU.......................................................................................................................................................................A
DSC-22_10-40-20 FCU
FCU.......................................................................................................................................................................... A
FCU Philosophy....................................................................................................................................................... B
Speed/Mach Control Area....................................................................................................................................... C
Lateral Control Area................................................................................................................................................ D
AP-A/THR Control Area...........................................................................................................................................E
Vertical Control Area................................................................................................................................................F
DSC-22_10-40-30 Thrust Levers
Thrust Levers........................................................................................................................................................... A
Continued on the following page
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AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_10-40-40 Primary Flight Display
Continued from the previous page
PFD.......................................................................................................................................................................... A
Climb Phase.............................................................................................................................................................B
Approach Phase...................................................................................................................................................... C
DSC-22_10-40-50 Navigation Display
ND............................................................................................................................................................................ A
Arc Mode..................................................................................................................................................................B
Plan Mode................................................................................................................................................................C
Rose Modes.............................................................................................................................................................D
Flight Plan Display Colors....................................................................................................................................... E
DSC-22_10-50 Speeds Definition
DSC-22_10-50-10 General
General.....................................................................................................................................................................A
DSC-22_10-50-20 Characteristic Speeds
Characteristic Speeds..............................................................................................................................................A
DSC-22_10-50-30 Limit Speeds
Limit Speeds............................................................................................................................................................ A
DSC-22_10-50-40 Protection Speeds
Protection Speeds....................................................................................................................................................A
DSC-22_10-50-50 Other Speeds
Other Speeds...........................................................................................................................................................A
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AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
FMGC STANDARD
Ident.: DSC-22_10-10-00014871.0005001 / 24 JUL 13
Applicable to: ALL
The aircraft is equipped with FMS 2 HONEYWELL Release 1A H2 and FG C12.
PREAMBLE
Ident.: DSC-22_10-10-00010067.0001001 / 17 AUG 10
Applicable to: ALL
This section gives a general description of the Auto Flight System and its functions:
‐ Architecture
‐ Function description
‐ Basic principle of systems:
• Reversion
• Protection
• Managed and selected guidance modes.
‐ Mode information
‐ Display characteristics
‐ Operational principles
‐ Flight crew interface (MCDU pages)
‐ Degraded modes of operations.
DESCRIPTION
Ident.: DSC-22_10-10-00010068.0001001 / 17 AUG 10
Applicable to: ALL
The Flight Management Guidance System (FMGS) contains the following units:
‐ Two Flight Management Guidance Computers (FMGC)
‐ Two Multipurpose Control and Display Units (MCDU ) (third MCDU optional)
‐ One Flight Control Unit (FCU)
‐ Two Flight Augmentation Computers (FAC).
GENERAL PHILOSOPHY
Ident.: DSC-22_10-10-00010069.0001001 / 17 AUG 10
Applicable to: ALL
The Flight Management and Guidance System (FMGS) provides predictions of flight time, mileage,
speed, economy profiles and altitude.
It reduces cockpit workload, improves efficiency, and eliminates many routine operations generally
performed by the flight crew.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
The Flight Management Guidance System (FMGS) operates as follows:
‐ During cockpit preparation the flight crew uses the Multipurpose Control and Display Unit (MCDU
) to insert a preplanned route from origin to destination. This route includes SID , EN ROUTE,
WAYPOINTS, STAR , APPROACH, MISSED APPR , and ALTN route as available from the
navigation database.
‐ Subsequently the system defines a vertical profile and a speed profile, taking into account ATC
requirements and performance criteria.
Either FMGC performs all operations, if one FMGC fails.
The FMGS computes the aircraft position continually, using stored aircraft performance data and
navigation data. Therefore it can steer the aircraft along a preplanned route and vertical and speed
profiles. This type of guidance is said to be “managed”.
If the flight crew wants to modify any flight parameter (SPD , V/S , HDG , etc.) temporarily, they may
do so by using the various Flight Control Unit (FCU ) selectors. The FMGS then guides the aircraft
to the target value of this parameter that they have selected. This type of guidance is said to be
“selected”.
The two available types of guidance, then, are:
‐ Managed guidance guides the aircraft along the preplanned route and the vertical and
speed/Mach profile. (The FMGS computes the target values of the various flight parameters).
‐ Selected guidance guides the aircraft to the target values of the various flight parameters the flight
crew selects by using the FCU selectors.
Selected guidance always has priority over managed guidance.
FLIGHT MANAGEMENT GUIDANCE COMPUTER (FMGC)
Ident.: DSC-22_10-10-00010073.0002001 / 17 AUG 10
Applicable to: ALL
Each FMGC is divided into two main parts:
‐ The Flight Management (FM) part controls the following functions:
• Navigation and management of navigation radios
• Management of flight planning
• Prediction and optimization of performance
• Display management.
‐ The Flight Guidance (FG) part performs the following functions:
• Autopilot (AP) command
• Flight Director (FD) command
• Autothrust (A/THR) command.
Each FMGC has its own set of databases. The individual databases can be independently loaded
into their respective FMGC , or independently copied from one FMGC to the other.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
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DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Each FMGC contains these main databases:
1. The Navigation database (2.8 Mbytes) contains standard navigation data: Navaids, waypoints,
airways, enroute information, holding patterns, airports, runways, procedures (SID s, STARs, etc.),
company routes, alternates.
The airline updates this part every 28 days, and is responsible for defining, acquiring, updating,
loading, and using this data. The updating operation takes 20 min to complete or 5 min if cross
loaded from the opposite FMGC.
2. The Airline Modifiable Information (AMI ), also described as the FM Airline Configuration file,
contains:
‐ Airline policy values: THR RED altitude, ACC altitude, EO ACC altitude, PERF factor, IDLE
factor.
‐ Fuel policy values: Fuel for taxi, % of route reserve, maximum and minimum values of route
reserve, etc.
‐ AOC functions customization.
3. The Aircraft Performance database includes the Engine model, Aerodynamical model, and
Performance model. The airline cannot modify this database.
4. The Magnetic Variation database.
5. Each FMGC contains elements stored by the flight crew that enable them to create 20 waypoints,
10 runways, 20 navaids, and 5 routes.
MULTIPURPOSE CONTROL AND DISPLAY UNIT (MCDU)
Ident.: DSC-22_10-10-00010074.0002001 / 17 AUG 10
Applicable to: ALL
Two MCDU s are installed on the pedestal for flight crew loading and display of data. The use of
the MCDU allows the flight crew to interface with the FMGC by selection of a flight plan for lateral
and vertical trajectories and speed profiles. The flight crew may also modify selected navigation
or performance data and specific functions of Flight Management (revised flight plan, engine-out,
secondary flight plan, etc.). Additional data from peripherals (Centralized Fault Display System
(CFDS ), ARINC Communication Addressing and Reporting System (ACARS ), Air Traffic Service
Unit (ATSU )...) can also be displayed. Data that is entered into the MCDU that is illogical or beyond
the aircraft capabilities will either be disregarded or will generate an advisory message.
The MCDU s allow the activation of the back–up navigation in the case of a dual FM Failure.
FLIGHT CONTROL UNIT (FCU)
Ident.: DSC-22_10-10-00010075.0001001 / 17 AUG 10
Applicable to: ALL
The FCU located on the glareshield, is the short-term interface between the flight crew and the
FMGC . It is used to select any flight parameters or modify those selected in the MCDU. The
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AIRCRAFT SYSTEMS
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DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
autopilots and autothrust functions may be engaged or disengaged. Different guidance modes can
be selected to change various targets (speed, heading, track, altitude, flight path angle, vertical
speed).
FLIGHT AUGMENTATION COMPUTER (FAC)
Ident.: DSC-22_10-10-00010076.0001001 / 17 AUG 10
Applicable to: ALL
The FAC controls rudder, rudder trim and yaw damper inputs. It computes data for the flight envelope
and speed functions. The FAC also provides warning for low-energy and windshear detection if these
functions are installed.
OTHER FLIGHT CREW INTERFACES
Applicable to: ALL
Ident.: DSC-22_10-10-A-00010077.0001001 / 23 JUN 15
THRUST LEVERS
The thrust levers are the main interface between the Flight Management Guidance Computer
(FMGC ), the Full Authority Digital Engine Control System (FADEC), and the flight crew.
The thrust levers:
‐ Arm the autothrust at takeoff, when FLX or TOGA is selected
‐ Limit the maximum thrust by their position when autothrust is active
‐ Disconnect the autothrust system when the flight crew sets them to IDLE
‐ Command the thrust manually when autothrust is not active
‐ Engage the common modes (takeoff or go-around) when TOGA (or FLX for takeoff) is set
‐ Set the autothrust to the active mode when they are between IDLE and CL detent (MCT in
engine out).
Ident.: DSC-22_10-10-A-00010078.0001001 / 17 AUG 10
ELECTRONIC FLIGHT INSTRUMENTS (EFIS)
Two Primary Flight Displays (PFD ) and Navigation Displays (ND ) provide the flight crew with
full-time flight guidance, navigation and system advisory information for all flight phases. An EFIS
control panel is located at each end of the glareshield and is used to control both Primary and
Navigation Displays. This panel includes controls to select various modes within the PFD . A
selector allows the barometric altimeter setting to be displayed on the PFD . Various distance
ranges can be selected on the ND , and two switches allow either the left or right VOR /ADF
bearing pointers to be displayed on the ND.
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DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_10-10-A-00010079.0001001 / 17 AUG 10
PRIMARY FLIGHT DISPLAYS
The PFDs combine several conventional flight instrument indications on one color display panel,
for centralized reference of flight data.
This centralized color display includes:
‐ Flight Director attitude guidance targets
‐ Armed and engaged modes
‐ Navigation and instrument approach information
‐ Altimeter setting
‐ Barometric altitude
‐ System messages.
Ident.: DSC-22_10-10-A-00010080.0002001 / 17 AUG 10
NAVIGATION DISPLAYS
Five different color navigation compass displays can be selected:
‐ ARC (map mode)
‐ ROSE NAV (map mode)
‐ ROSE VOR
‐ ROSE LS
‐ PLAN.
Information displayed on these modes uses the aircraft’s position as a reference point for the flight
plan navigation data (lateral and vertical information).
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DESCRIPTION
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OPERATING MANUAL
FLIGHT CREW INTERFACE WITH FMGC
Ident.: DSC-22_10-10-00010082.0002001 / 14 MAY 12
Applicable to: ALL
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AIRCRAFT SYSTEMS
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SYSTEM INTERFACE DIAGRAM
FLIGHT CREW
OPERATING MANUAL
SYSTEM INTERFACE DIAGRAM
Ident.: DSC-22_10-20-00010084.0001001 / 01 OCT 12
Applicable to: ALL
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SYSTEM INTERFACE DIAGRAM
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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FMGS MODES OF OPERATION
GENERAL
Ident.: DSC-22_10-30-00010085.0002001 / 17 AUG 10
Applicable to: ALL
The FMGS has four modes of operation:
‐ Dual mode (the normal mode)
‐ Independent mode. Each FMGC being controlled by its associated MCDU
‐ Single mode (using one FMGC only)
‐ Back–up navigation mode.
DUAL MODE
Ident.: DSC-22_10-30-00010086.0001001 / 01 OCT 12
Applicable to: ALL
This is the normal mode. The two FMGCs are synchronized: each performs its own computations
and exchanges data with the other through a crosstalk bus.
One FMGC is the master, the other the slave, so that some data in the slave FMGC comes from the
master.
All data inserted into any MCDU is transferred to both FMGCs and to all peripherals.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FMGS MODES OF OPERATION
MASTER FMGC LOGIC
‐ If one autopilot (AP ) is engaged, the related FMGC is master:
• It uses the onside FD for guidance
• It controls the A/THR
• It controls the FMA 1 and 2.
‐ If two AP s are engaged, FMGC1 is master.
‐ If no AP is engaged, and
• The FD1 pb is on, then FMGC1 is master
• The FD1 pb is off, and FD2 pb on then FMGC2 is master.
‐ If no AP /FD is engaged, A/THR is controlled by FMGC1.
INDEPENDENT MODE
Ident.: DSC-22_10-30-00010087.0001001 / 01 OCT 12
Applicable to: ALL
The system automatically selects this degraded mode under specific abnormal conditions (e.g.
different database validity on both FMGCs).
Both FMGCs work independently and are linked only to peripherals on their own sides of the flight
deck (“onside” peripherals).
When this occurs, the “INDEPENDENT OPERATION” message is displayed on both MCDU
scratchpads.
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FMGS MODES OF OPERATION
Each MCDU transmits data it receives from its onside FMGC . It affects only the onside EFIS
(Electronic Flight Instrument System) and RMP (Radio Management Panel).
On the POS MONITOR page (and GPS MONITOR page ), FMGS position (and GPS position
) from the opposite FMGC is not displayed.
On the RAD NAV page (and PROG page, if the FMGS GPS is not installed), navaids tuned on the
opposite MCDU are not displayed. Corresponding fields are blank.
PROCEDURES ON GROUND
If each FMGC is loaded with a different database, the FMGS will only operate in
independent mode.
CHECK the database number and validity.
CROSSLOAD the database to restore the dual operation.
Crossload function is available on ground only (in preflight or done phase), when an
independent operation is detected.
PROCEDURES IN FLIGHT
DO NOT SWITCH the navigation databases.
MAKE the same entries on both MCDU s to have both AP /FDs similar orders.
Both FG s being valid, 2 AP s may be engaged for CAT II or CAT III operations.
In the event of a go-around and when the second AP is disconnected:
ENSURE that the FMGC in command has correct flight plan orders and an updated nav
database.
Airbus does not recommend pulling one FMGC circuit breaker to force the system to operate
in SINGLE mode.
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FMGS MODES OF OPERATION
FLIGHT CREW
OPERATING MANUAL
SINGLE MODE
Ident.: DSC-22_10-30-00010088.0004001 / 01 OCT 12
Applicable to: ALL
The system automatically selects this degraded mode when one FMGC fails.
When this occurs, the failed FMGC displays “OPP FMGC IN PROCESS” in white on the MCDU
scratchpad.
On the ND usually associated with the failed FM:
‐ If the ND s are not both in the same mode or range, the associated ND displays "MAP NOT
AVAIL" and "SET OFFSIDE RNG/MODE".
‐ If the ND s are in the same mode and range, the associated ND displays the "OFFSIDE FM
CONTROL" amber message.
Both POS MONITOR pages display the same position (operative FMGC position).
Both FD s are driven by the same FMGC . Any entry on either MCDU is sent to the operative FMGC.
PROCEDURES
If a transient failure triggers a single mode of operation:
DO NOT USE the MCDU(s) until the PLEASE WAIT message is suppressed.
SET both NDs on the same range and mode to display the same information from the
operative FMGC.
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AIRCRAFT SYSTEMS
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FMGS MODES OF OPERATION
FLIGHT CREW
OPERATING MANUAL
When convenient, RESET the failed FMGC. (Refer to DSC-22_20-90-10 Manual FMGC
Reset - General).
BACK UP NAVIGATION MODE
Ident.: DSC-22_10-30-00010089.0001001 / 01 OCT 12
Applicable to: ALL
The flight crew selects on the MCDU MENU page this degraded mode when both FMGC s fail. They
recover the navigation function through the MCDU and IRS /GPS .
The MCDU continuously memorizes the active flight plan in its memory.
If both FMGCs fail, the back up navigation provides the following functions:
‐ Flight Planning
‐ Aircraft position using onside IRS , IRS 3, or GPIRS position (if GPS )
‐ F-PLN display on ND
‐ No AP /FD NAV mode
‐ Limited lateral revision
‐ F-PLN automatic sequencing.
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OPERATING MANUAL
Intentionally left blank
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PILOT INTERFACE - MANAGEMENT OF THE DISPLAYS
GENERAL
Ident.: DSC-22_10-40-05-00010083.0001001 / 17 AUG 10
Applicable to: ALL
The flight management system displays navigation, performance and guidance information on the:
‐ Multipurpose Control and Display Unit (MCDU)
‐ Navigation Display (ND ) of the Electronic Flight Instrument System (EFIS)
‐ Primary Flight Display (PFD ) of the EFIS.
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Intentionally left blank
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PILOT INTERFACE - MCDU
MCDU
Applicable to: ALL
Ident.: DSC-22_10-40-10-A-00010090.0003001 / 14 MAY 12
MCDU INTERFACE
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PILOT INTERFACE - MCDU
Ident.: DSC-22_10-40-10-A-00010091.0002001 / 13 DEC 12
GENERAL
The Multipurpose Control and Display Unit (MCDU ) has a Liquid Crystal Display (LCD) with 14
lines of 24 characters each, including:
‐ A title line that gives the name of the current page in large letters
‐ Six label lines, each of which names the data displayed just below it (on the data field line)
‐ Six data field lines that display computed data or data inserted by the flight crew
‐ The scratchpad line that displays:
• Specific messages
• Information the flight crew has entered by means of the number and letter keys and which
can then be moved to one of the data fields.
Ident.: DSC-22_10-40-10-A-00010092.0001001 / 17 AUG 10
LINE SELECT KEYS
There is a column of Line Select Keys (LSKs) on each side of the screen.
The flight crew uses these keys to:
‐ Move a parameter they have entered in the scratchpad to the appropriate line on the main
screen
‐ Call up a specific function page indicated by a prompt displayed on the adjacent line
‐ Call up lateral or vertical revision pages from the flight plan page.
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PILOT INTERFACE - MCDU
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_10-40-10-A-00010093.0002001 / 17 AUG 10
KEYBOARD
The keyboard includes:
‐ Function and Page
keys
↑ ↓ (or SLEW) keys
← → keys
Call up functions and pages the flight crew uses for flight management
functions and computations.
Move a page up or down to display portions that are off the screen.
Moves to the next page of a multi-page element. An arrow in the top right
corner indicates that another page is available.
AIRPORT key
Calls up the flight plan page that contains the next airport along the
current flight plan. Successive pushes on the key show the alternate
airport, the origin airport (before takeoff), and the next airport again.
‐ Number and letter keys allow the flight crew to insert data in the scratchpad so that they can use
a line select key to enter it in the main display.
‐ Three keys have special functions:
CLR (clear) key
Erases material (messages or inserted data) from the scratchpad or from
certain areas of displayed pages.
OVFY (overfly) key Allows the aircraft to overfly a selected waypoint.
SP (space) key
Allows to insert a space in specific message.
Ident.: DSC-22_10-40-10-A-00010094.0002001 / 17 AUG 10
ANNUNCIATORS (ON THE SIDE OF THE KEYBOARD)
FAIL (amber)
MCDU MENU (white)
FM (white)
Indicates that the Multipurpose Control and Display Unit (MCDU) has
failed.
Indicates that the flight crew should call up a peripheral linked to the
MCDU (such as ACARS , ATSU or CFDS).
Comes on while the flight crew is using the MCDU to display peripherals.
This light tells the flight crew that the FMGC has an important message
to deliver. The flight crew accesses the message by pressing the MCDU
MENU key and the line select key adjacent to the FMGC prompt.
Ident.: DSC-22_10-40-10-A-00010757.0002001 / 17 AUG 10
ANNUNCIATORS (ON THE TOP OF THE KEYBOARD)
FM 1 and FM 2 (amber) The onside FM is failed
IND (amber)
The onside FM detects an independent mode of operation while both FM
are healthly.
RDY (green)
MCDU has passed its power up test after it was turned off using its DIM
key.
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AIRCRAFT SYSTEMS
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PILOT INTERFACE - MCDU
Ident.: DSC-22_10-40-10-A-00010750.0001001 / 17 AUG 10
BRT AND DIM KEYS
Control the light intensity of the entire MCDU . MCDU power up is performed with the BRT key and
MCDU shut down is performed with the DIM key.
Ident.: DSC-22_10-40-10-A-00010097.0001001 / 17 AUG 10
DATA ENTRY
The flight crew enters data by typing it into the scratchpad on the MCDU . Next, pressing the line
select key (LSK ) will load the data from the scratchpad into the desired field. An error message
displays if the data is out of range or not formatted correctly. To correct data, the flight crew may
clear the message with the clear (CLR) key and then retype the message into the scratchpad.
Pressing the CLR key when the scratchpad is empty displays “CLR”. To clear data from a field,
select CLR from the scratchpad to the data field to be cleared.
Ident.: DSC-22_10-40-10-A-00010098.0001001 / 17 AUG 10
MCDU ENTRY FORMAT
The flight crew enters information into the MCDU at the bottom line of the scratchpad. When data
has lead zeros, they may be omitted if desired. For example a three-digit wind direction of 060
may be typed as 60. The display will still show 060. To enter an altitude below 1 000 ft, the lead
zero must be added as 0400 for 400 ft. This differentiates the altitude from a flight level.
To enter a double data entry such a speed/altitude, the separating slash must be used. If entering
only the first part of a double entry, omit the slash. To enter only the second part of a double entry,
a leading slash must be used i.e. /0400.
Ident.: DSC-22_10-40-10-A-00010099.0001001 / 17 AUG 10
MESSAGES
The scratchpad displays various messages for flight crew information. Theses messages are
prioritized by importance to the flight crew as either amber or white.
Amber messages are:
‐ Navigation messages
‐ Data entry messages
‐ EFIS repeat messages.
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FLIGHT CREW
OPERATING MANUAL
Amber messages are categorized into two types:
‐ Type 1 message that is a direct result of a flight crew action. Type 1 messages are displayed
immediately in the scratchpad ahead of other messages.
‐ Type 2 messages inform the flight crew of a given situation or request a specific action. Stored
in “last in”, “first out” message queue that holds maximum of 5 messages.
Type 2 messages are displayed in the scratchpad only if there are no Type 1 messages or other
data and will remain until all the messages have been viewed and cleared with the CLR key.
White messages are advisory only.
Ident.: DSC-22_10-40-10-A-00010101.0001001 / 17 AUG 10
CHARACTERS
Small and large fonts are displayed according to the following rules:
‐ The title line and the scratchpad are displayed in large font
‐ Datafields are usually displayed in large font
‐ Label lines are displayed in small font
‐ Flight crew entries and modifiable data are displayed in large font
‐ Defaulted/computed and non modifiable data are displayed in small font.
Ident.: DSC-22_10-40-10-A-00010102.0001001 / 17 AUG 10
COLORS
DATA
TITLES, COMMENTS, <, >, ↑ ↓,
← →, DASHES, MINOR MESSAGES
‐ MODIFIABLE DATA
‐ SELECTABLE DATA
‐ BRACKETS
‐ NON MODIFIABLE DATA
‐ ACTIVE DATA
‐
‐
‐
‐
MANDATORY DATA (BOXES)
FLIGHT CREW ACTION REQUIRED
IMPORTANT MESSAGES
MISSED CONSTRAINT
‐ CONSTRAINTS
‐ MAX ALTITUDE
PRIMARY F-PLN
TEMPORARY F-PLN
GLG A318/A319/A320/A321 For A/C: HC-CRU
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WHITE
MCDU COLOR
BLUE
GREEN
AMBER
MAGENTA
GREEN WAYPOINTS, WHITE LEGS
YELLOW WAYPOINTS, WHITE LEGS
Continued on the following page
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DATA
SECONDARY F-PLN
MISSED APPROACH (not active)
ALTERNATE F-PLN (not active)
OFFSET
TUNED NAVAID
"TO" WAYPOINT AND DESTINATION
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PILOT INTERFACE - MCDU
Continued from the previous page
MCDU COLOR
WHITE WAYPOINTS AND LEGS
BLUE WAYPOINTS, WHITE LEGS
BLUE WAYPOINTS, WHITE LEGS
GREEN WAYPOINTS, WHITE LEGS,
OFST DISPLAYED IN THE TITLE OF THE F-PLN PAGE
BLUE
WHITE
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PILOT INTERFACE - MCDU
Ident.: DSC-22_10-40-10-A-00010103.0001001 / 14 MAY 12
SCREEN PROMPTS
Ident.: DSC-22_10-40-10-A-00010104.0002001 / 23 JUN 15
MCDU FUNCTION KEYS
The function keys on the Multipurpose Control and Display Units allow the flight crew to call up
MCDU pages quickly.
The following is a summary of the purpose of each key:
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DIR
PROG
PERF
INIT
DATA
F-PLN
RAD NAV
PILOT INTERFACE - MCDU
Calls up the DIR TO page, and enables the flight crew to proceed directly from
the present position to any waypoint, entered manually or selected in the active
flight plan.
Calls up the progress page corresponding to the phase of the active flight plan
that is in progress.
This page displays navigation information and active data such as the optimum
and maximum recommended cruise flight levels. It enables the flight crew to
update the FMGS position and to obtain a bearing and distance to any location.
Calls up the performance pages, that display the optimum speed or Mach number
for each phase. The flight crew can amend these pages. The first page to be
displayed is the one corresponding to the current flight phase (except for preflight
and done phases).
The flight crew can then use the appropriate 6L or 6R LSK to call up pages
corresponding to future flight phases.
Calls up the flight plan initialization A page, which also gives the flight crew
access to the B page. The flight crew uses the INIT pages to initialize Flight
Management for the flight.
The flight crew uses the INIT A page primarily to insert his flight plan and to align
the inertial reference system.
The flight crew uses the INIT B page to insert aircraft weight, fuel on board, CG
and various fuel requirements. The FMGS uses this data to compute predictions
and fuel planning parameters.
The flight crew has access to the INIT A page only in the preflight phase.
INIT B page (not accessible after engine start) is called up by pressing the "NEXT
PAGE" key.
Calls up the data index page. This gives the flight crew access to various
reference pages that show aircraft position, aircraft status, runways, waypoints,
navaids, routes, and data stored by the flight crew.
Calls up the flight plan A and B pages, which contain a leg-by-leg description of
the active primary flight plan.
The flight crew can use the slewing keys to review the entire active flight plan.
They can make all lateral and vertical revisions to the flight plan through these
pages, using the left LSKs for lateral revision and the right keys for vertical
revision.
Calls up the radio navigation page. This page displays the Radio Navaids tuned
automatically or manually through the FMGC.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_10-40-10 P 8/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FUEL PRED
SEC F-PLN
ATC COMM
MCDU MENU
PILOT INTERFACE - MCDU
Calls up the fuel prediction page. Once the engines are started, this page
displays the fuel predicted to be remaining at the destination and the alternate, as
well as fuel management data.
Calls up the index page for the secondary flight plan. The flight crew can use
this page to call up the secondary flight plan and all the functions related to it
(copying, deleting, reviewing, activating, and the INIT and PERF pages).
Calls up the ATC applications (not activated).
Calls up the MCDU MENU page, which displays the subsystems currently
addressed via the MCDU. The key next to the name of a subsystem enables the
flight crew to select that subsystem.
When the MCDU MENU annunciator lights up, the flight crew should press the
MCDU MENU key. The menu will have [REQ] displayed next to the name of the
subsystem that requires attention.
Ident.: DSC-22_10-40-10-A-00010107.0005001 / 01 OCT 12
MCDU DISPLAY
The MCDUs display:
‐ Position and accuracy information
‐ Tuned navaids
‐ Lateral and vertical flight plans (waypoints, pseudo waypoints, constraints)
‐ Predictions (SPD , TIME, ALT, WIND)
‐ Fuel predictions and fuel management information (estimated fuel on board, extra fuel)
‐ Performance data.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_10-40-10 P 9/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PILOT INTERFACE - MCDU
←A
DSC-22_10-40-10 P 10/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW
OPERATING MANUAL
FCU
Ident.: DSC-22_10-40-20-00010112.0003001 / 03 AUG 17
Applicable to: ALL
The Flight Control Unit (FCU ) is located on the glareshield and is constituted of three control panels:
One for the automatic flight controls and two for the Electronic Flight Instrument System (EFIS ). The
FCU has two channels, each of which can independently command the central control panel. If one
channel fails, the other channel can control all the functions.
FCU PHILOSOPHY
Ident.: DSC-22_10-40-20-00010113.0002001 / 14 MAY 12
Applicable to: ALL
The flight crew can use two types of guidance to control the aircraft in auto flight. One type is
managed by the Flight Management Guidance System (FMGS). The other uses target quantities
which are manually entered by the flight crew.
When the aircraft uses target quantities from the FMGS (managed guidance), the FCU windows
display dashes and the white dots next to those windows light up. When the aircraft uses target
quantities, entered by the flight crew (selected guidance), the windows display the selected numbers
and the white dots do not light up.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_10-40-20 P 1/8
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW
OPERATING MANUAL
Note:
The altitude window always displays an altitude selected by the flight crew (never dashes).
The FCU has four knobs:
‐ SPD-MACH
‐ HDG -TRK
‐ ALT
‐ V/S -FPA.
The knobs can be rotated, pushed in, and pulled out:
‐ In order to arm or engage managed guidance for a given mode, the flight crew pushes in the
associated knob. If, for example, they push in the HDG knob, they engage or arms the NAV mode.
‐ In order to engage a selected guidance mode, the flight crew turns the knob to set the desired
value, then pulls the knob out to engage the mode with a target value equal to the selected value.
Note:
In managed guidance (lateral, vertical guidance or managed speed), the corresponding
window is dashed. Turning a knob without pulling it, displays a value that is the sum of the
current target and the turn action value. The display remains 45 s on the HDG /TRK and
V/S windows and 10 s on the SPD/MACH window before the dashes reappear. This rule
does not apply to the ALT knob/window.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-22_10-40-20 P 2/8
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW
OPERATING MANUAL
SPEED/MACH CONTROL AREA
Ident.: DSC-22_10-40-20-00010114.0002001 / 14 MAY 12
Applicable to: ALL
SPD/MACH knob
Display range: between 100 and 399 kt for speed, between 0.10 and 0.99 for Mach number.
One rotation of the knob corresponds to approximately 32 kt or M 0.32.
SPD/MACH pb
Pushing this pushbutton changes the SPD target to the corresponding MACH target and vice
versa.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-22_10-40-20 P 3/8
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW
OPERATING MANUAL
LATERAL CONTROL AREA
Ident.: DSC-22_10-40-20-00010115.0007001 / 14 MAY 12
Applicable to: ALL
HDG/TRK knob
Display range: between 0 ° and 359 °.
One rotation of the knob corresponds to 32 ° (1 ° per click).
LOC pb
Pushing this pushbutton arms, engages, or disengages the LOC mode.
HDG V/S – TRK FPA pb
The flight crew uses this pushbutton to select HDG (associated with V/S ) or TRK (associated with
FPA). Pushing it:
‐ Displays the Flight Path Vector (FPV ) on the Primary Flight Display (PFD) or deletes it.
‐ On the PFD , changes the FD crossbar display (with the aircraft attitude as its reference) to the
aircraft Flight Path Director (with the flight path vector as its reference) and vice versa.
‐ Changes heading reference into track reference in the HDG /TRK window and vice versa.
‐ Changes vertical speed reference target into flight path angle reference target in the V/S -FPA
window and vice versa.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
DSC-22_10-40-20 P 4/8
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW
OPERATING MANUAL
AP-A/THR CONTROL AREA
Ident.: DSC-22_10-40-20-00010116.0001001 / 14 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
DSC-22_10-40-20 P 5/8
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW
OPERATING MANUAL
AP1 pb AND AP2 pb
The flight crew uses these pushbuttons to engage or disengage the autopilots. The buttons
illuminate green when the autopilot is engaged.
A/THR pb
The flight crew uses this pushbutton to arm, activate, or disconnect the autothrust (A/THR ). This
button illuminates green if the A/THR is armed or active.
VERTICAL CONTROL AREA
Ident.: DSC-22_10-40-20-00010117.0006001 / 22 MAY 12
Applicable to: ALL
The FCU altitude window always displays a target value selected by the flight crew. It never displays
dashes.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F →
DSC-22_10-40-20 P 6/8
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW
OPERATING MANUAL
Altitude knob (INNER AND OUTER)
Display range: 100 to 49 000 ft
‐ The outer knob has two positions: 100 and 1000
‐ The inner knob sets the altitude in the FCU window in increments of 100 or 1 000 ft, depending
upon the position of the outer knob.
EXPED pb
This pushbutton is used to engage the expedite mode. Refer to DSC-22_30-70-90 General.
METRIC ALT pb
This pushbutton is used to display the FCU altitude target in meters on the ECAM , or the current
altitude and FCU /FM altitude target in meters on the PFD .
V/S or FPA knob
Range (V/S) :
–6 000 to +6 000 ft/min
2 clicks = 100 ft/min
If the flight crew turns the knob slowly, each click equals 100 ft/min.
Range (FPA) : –9.9 ° to +9.9 °
1 click = 0.1 °
The flight crew turns this knob to set the value of the vertical speed (V/S ) or flight path angle (FPA
) to be displayed in the V/S or FPA window (They choose which, V/S or FPA, is to be displayed by
pushing the HDG V/S - TRK FPA pb).
One rotation of the knob corresponds to 32 clicks. One complete rotation sets:
FPA = 3.2 °
V/S = 1 600 ft/min
When the flight crew pushes in the V/S or FPA knob, the system commands an immediate level-off
by engaging the V/S or FPA mode with a target of zero. The flight mode annunciator (FMA ) then
displays "V/S = 0" in green when V/S or FPA is nulled. If the flight crew now turns the knob to put
in a new setting for V/S or FPA, the aircraft changes flight path accordingly.
APPR pb
This pushbutton arms, disarms, engages, or disengages the approach modes:
‐ LOC and G/S modes, if an ILS approach is selected in the active F-PLN.
‐ APP NAV -FINAL modes, if a non precision approach is selected in the active F-PLN.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
DSC-22_10-40-20 P 7/8
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - FCU
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_10-40-20 P 8/8
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - THRUST LEVERS
FLIGHT CREW
OPERATING MANUAL
THRUST LEVERS
Ident.: DSC-22_10-40-30-00010119.0001001 / 14 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-22_10-40-30 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - THRUST LEVERS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_10-40-30 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PILOT INTERFACE - PRIMARY FLIGHT DISPLAY
PFD
Ident.: DSC-22_10-40-40-00010677.0001001 / 17 AUG 10
Applicable to: ALL
The Flight Management and Guidance System generates the following information to the EFIS
Primary Flight Display:
‐ Armed and engaged modes on the Flight Mode Annunciator (FMA)
‐ FMGS guidance targets (SPD , ALT , HDG)
‐ Vertical deviation from descent profile
‐ Messages
‐ Navigation information.
CLIMB PHASE
Ident.: DSC-22_10-40-40-00010121.0002001 / 14 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-22_10-40-40 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - PRIMARY FLIGHT DISPLAY
FLIGHT CREW
OPERATING MANUAL
APPROACH PHASE
Ident.: DSC-22_10-40-40-00010122.0013001 / 14 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-22_10-40-40 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PILOT INTERFACE - NAVIGATION DISPLAY
ND
Ident.: DSC-22_10-40-50-00010123.0001001 / 17 AUG 10
Applicable to: ALL
The FMGS generates the following information, displayed on the EFIS Navigation Displays:
‐ Flight plan (active secondary, temporary, dashed)
‐ Aircraft position and lateral deviation from the flight plan
‐ Pseudo-waypoints along the flight plan
‐ Raw data from tuned Navaids and type of selected approach
‐ Various display options (waypoints, Navaids, NDBs, airports, constraints)
‐ Wind information and various messages.
ARC MODE
Ident.: DSC-22_10-40-50-00010124.0001001 / 14 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-22_10-40-50 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PILOT INTERFACE - NAVIGATION DISPLAY
PLAN MODE
Ident.: DSC-22_10-40-50-00010125.0001001 / 01 OCT 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-22_10-40-50 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - NAVIGATION DISPLAY
FLIGHT CREW
OPERATING MANUAL
ROSE MODES
Ident.: DSC-22_10-40-50-00010126.0022001 / 09 MAR 15
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
DSC-22_10-40-50 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
PILOT INTERFACE - NAVIGATION DISPLAY
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLAN DISPLAY COLORS
Ident.: DSC-22_10-40-50-00010127.0002001 / 17 AUG 10
Applicable to: ALL
F-PLN
Primary Flight Plan
Color
Track line
Alternate flight plan
Missed approach
Offset flight plan
Temporary flight plan
Engine-out SID (not inserted)
Secondary flight plan
Abeam/Radial
Steady green
Dashed blue
Steady blue
Steady green (Original flight plan: Dashed green)
Dashed yellow
Steady yellow
Steady dimmed white
Dashed blue
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
‐ Managed mode: Steady green
‐ Selected mode: Dashed green
E
DSC-22_10-40-50 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SPEEDS DEFINITION - GENERAL
GENERAL
Ident.: DSC-22_10-50-10-00020369.0001001 / 17 MAR 17
Applicable to: ALL
This chapter shows the speed symbols and definitions.
The source of the computation is also given, when applicable.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-22_10-50-10 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
SPEEDS DEFINITION - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_10-50-10 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SPEEDS DEFINITION - CHARACTERISTIC SPEEDS
CHARACTERISTIC SPEEDS
Ident.: DSC-22_10-50-20-00020370.0002001 / 17 MAR 17
Applicable to: ALL
The characteristic speeds displayed on the PFD are computed by the Flight Augmentation Computer
(FAC), according to aerodynamic data.
VLS (of normal landing configuration: CONF 3 or FULL), F, S and Green Dot speeds are also
displayed on the MCDU TAKEOFF and/or APPR pages.
The speeds displayed by the MCDU are computed by the FMS , based on the aircraft gross weight
(which is computed according to the entered ZFW and the FOB), or the predicted gross weight (for
approach or go-around).
VS : Stalling speed.
Not displayed.
For a conventional aircraft, the reference stall speed, VSmin, is based on a load factor
that is less than 1 g. This gives a stall speed that is lower than the stall speed at 1 g. All
operating speeds are expressed as functions of this speed (for example, VREF = 1.3
VSmin).
Because aircraft of the A320 family have a low-speed protection feature (alpha limit) that
the flight crew cannot override, Airworthiness Authorities have reconsidered the definition of
stall speed for these aircraft.
All the operating speeds must be referenced to a speed that can be demonstrated by flight
tests. This speed is designated VS1g.
Airworthiness Authorities have agreed that a factor of 0.94 represents the relationship
between VS1g for aircraft of the A320 family and VSmin for conventional aircraft types. As a
result, Authorities allow aircraft of the A320 family to use the following factors :
V2 = 1.2 × 0.94 VS1g = 1.13 VS1g
VREF = 1.3 × 0.94 VS1g = 1.23 VS1g
These speeds are identical to those that the conventional 94 % rule would have defined for
these aircraft. The A318, A319, A320 and A321 have exactly the same maneuver margin
that a conventional aircraft would have at its reference speeds.
The FCOM uses VS for VS1g.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-22_10-50-20 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
VLS :
Lowest Selectable Speed.
Represented by the top of an amber strip along the airspeed scale on the PFD.
Computed by the FAC, based on aerodynamic data, and corresponds to 1.13 VS during
takeoff, or following a touch and go.
Becomes 1.23 VS, after retraction of one step of flaps.
Becomes 1.28 VS, when in clean configuration.
Note:
F
:
S
:
O
:
SPEEDS DEFINITION - CHARACTERISTIC SPEEDS
If in CONF 0 VLS were 1.23 VS (instead of 1.28 VS), the alpha protection strip
would hit the VLS strip on the PFD.
Above 20 000 ft, VLS is corrected for Mach effect to maintain a buffet margin of 0.2 g.
In addition, VLS increases when the speedbrakes are extended.
Minimum speed at which the flaps may be retracted at takeoff.
In approach, used as a target speed when the aircraft is in CONF 2 or CONF 3.
Represented by “F” on the PFD speed scale. Equal to about 1.18 VS to 1.22 VS of CONF 1
+ F.
Minimum speed at which the slats may be retracted at takeoff.
In approach, used as a target speed when the aircraft is in CONF 1.
Represented by “S” on the PFD airspeed scale.
Equal to about 1.22 VS to 1.25 VS of clean configuration.
Green dot speed.
Engine-out operating speed in clean configuration.
(Best lift-to-drag ratio speed).
Also corresponds to the final takeoff speed.
Represented by a green dot on the PFD scale.
Below 20 000 ft equal to 2 × weight (tons) +85
Above 20 000 ft, add 1 kt per 1 000 ft
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-22_10-50-20 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
SPEEDS DEFINITION - LIMIT SPEEDS
FLIGHT CREW
OPERATING MANUAL
LIMIT SPEEDS
Ident.: DSC-22_10-50-30-00020383.0001001 / 17 MAR 17
Applicable to: ALL
VA
:
VMCG
:
VMCA
:
VMCL
:
VFE
VLE
VLO
VMO
VFE NEXT
:
:
:
:
:
Maximum design maneuvering speed. This corresponds to the maximum structural
speed permitted for full control deflection, if alternate or direct law is active.
Minimum speed, on the ground during takeoff, at which the aircraft can be controlled
by only using the primary flight controls, after a sudden failure of the critical engine,
the other engine remaining at takeoff thrust.
Minimum control speed in flight at which the aircraft can be controlled with a
maximum bank of 5 °, if one engine fails, the other engine remaining at takeoff thrust
(takeoff flap setting, gear retracted).
Minimum control speed in flight, at which the aircraft can be controlled with a
maximum bank of 5 °, if one engine fails, the other engine remaining at takeoff thrust
(approach flap setting).
Maximum speed for each flap configuration.
Maximum speed with landing gear extended.
Maximum speed for landing gear operation.
Maximum speed.
Maximum speed for the next (further extended) flap lever position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-22_10-50-30 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
SPEEDS DEFINITION - LIMIT SPEEDS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_10-50-30 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
SPEEDS DEFINITION - PROTECTION SPEEDS
FLIGHT CREW
OPERATING MANUAL
PROTECTION SPEEDS
Ident.: DSC-22_10-50-40-00020382.0001001 / 17 MAR 17
Applicable to: ALL
Vα PROT, Vα MAX and VSW are computed by the FAC , based on aerodynamic data. They
are only used for display on the PFD , and not for flight control protection (the activation of the
protections is computed by the ELAC).
Vα PROT : Angle of attack protection speed.
Corresponds to the angle of attack at which the angle of attack protection becomes
active.
Represented by the top of a black and amber strip along the PFD speed scale, in
normal law.
Vα MAX : Maximum angle of attack speed.
Corresponds to the maximum angle of attack that may be reached in pitch normal
law.
Represented by the top of a red strip along the PFD speed scale, in normal law.
VSW
: Stall warning speed.
Represented by a red and black strip along the speed scale when the flight control
normal law is inoperative.
VMAX
: Represented by the bottom of a red and black strip along the speed scale.
Determined by the FAC according to the aircraft configuration.
Is equal to VMO (or speed corresponding to MMO ), VLE or VFE.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-22_10-50-40 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SPEEDS DEFINITION - PROTECTION SPEEDS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_10-50-40 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
SPEEDS DEFINITION - OTHER SPEEDS
FLIGHT CREW
OPERATING MANUAL
OTHER SPEEDS
Ident.: DSC-22_10-50-50-00020384.0004001 / 17 MAR 17
Applicable to: ALL
V1
:
VR
:
V2
:
VREF
:
VAPP
:
The highest speed, during takeoff, at which the flight crew has a choice
between continuing the takeoff or stopping the aircraft.
Represented by “1” on the airspeed scale (or the V1 value when it is off the
airspeed scale).
Inserted manually through the MCDU by the flight crew.
Displayed on the MCDU TAKEOFF page.
The speed at which the pilot rotates in order to reach V2 at an altitude of 35 ft at
the latest after an engine failure.
Inserted manually through the MCDU by the flight crew.
Displayed on the MCDU TAKEOFF page.
Takeoff safety speed that the aircraft attains at the latest at an altitude of 35 ft
with one engine failed, and maintains during the second segment of the takeoff.
Represented by the SPEED SELECT symbol on the speed scale.
Minimum value equal to 1.13 VS for the corresponding configuration.
Inserted manually through the MCDU by the flight crew.
Displayed on the MCDU TAKEOFF page.
Reference speed used for normal final approach.
Equal to 1.23 × VS of CONF FULL.
Displayed on the MCDU APPR page, if landing is planned in CONF FULL (VLS
CONF FULL).
Final approach speed.
Displayed on MCDU APPR page.
Calculated by the FMGCs.
Represents : VAPP = VLS + wind correction
The wind correction is limited to a minimum of 5 kt and a maximum of 15 kt.
The flight crew may modify VAPP through the MCDU.
‐ During autoland or when A/THR is on or in case of ice accretion or gusty
crosswind greater than 20 kt, VAPP must not be lower than VLS +5 kt.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-22_10-50-50 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SPEED
TARGET
:
SPEEDS DEFINITION - OTHER SPEEDS
Represented by a magenta triangle.
Calculated by the FMGCs
Gives efficient speed guidance in approach during various windy conditions.
Represents :
SPEED TARGET = GS mini + actual headwind (measured by ADIRS)
GS mini = VAPP – TOWER WIND (headwind component along runway axis
calculated by FMGC from tower wind entered on MCDU).
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_20-10 General
General.....................................................................................................................................................................A
DSC-22_20-20 Navigation
DSC-22_20-20-05 General
Navigation................................................................................................................................................................ A
DSC-22_20-20-10 Position Computation
General.....................................................................................................................................................................A
MIX IRS Position..................................................................................................................................................... B
GPS Position........................................................................................................................................................... C
Radio Position..........................................................................................................................................................D
FM Position.............................................................................................................................................................. E
Position Monitor....................................................................................................................................................... F
Takeoff Update........................................................................................................................................................ G
Navigation Modes.................................................................................................................................................... H
DSC-22_20-20-20 Evaluation of Position Accuracy
General.....................................................................................................................................................................A
Estimated Position Uncertainty................................................................................................................................B
FM/GPS Position Disagreement..............................................................................................................................C
Predictive GPS Page...............................................................................................................................................D
DSC-22_20-20-30 Radio Navigation Tuning
General.....................................................................................................................................................................A
Architecture.............................................................................................................................................................. B
VOR......................................................................................................................................................................... C
DME......................................................................................................................................................................... D
ADF.......................................................................................................................................................................... E
ILS............................................................................................................................................................................ F
Selection of Navaids on MCDU Pages...................................................................................................................G
Manual Tuning......................................................................................................................................................... H
Navaid Identification.................................................................................................................................................. I
DSC-22_20-20-40 Alignment of Inertial Reference System
Alignment of Inertial Reference System..................................................................................................................A
DSC-22_20-20-50 Navigation Database
General.....................................................................................................................................................................A
Operations with an Outdated Navigation Database................................................................................................B
Continued on the following page
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_20-30 Flight Planning
DSC-22_20-30-05 General
Continued from the previous page
Flight Planning......................................................................................................................................................... A
DSC-22_20-30-10 Lateral Functions
DSC-22_20-30-10-05 General
General.....................................................................................................................................................................A
Manual Legs............................................................................................................................................................ B
Flight Plan Construction.......................................................................................................................................... C
Flight Plan Capacity................................................................................................................................................ D
Lateral Revisions..................................................................................................................................................... E
DSC-22_20-30-10-15 FMS2 HONEYWELL
General.....................................................................................................................................................................A
Temporary F-PLN (TMPY)...................................................................................................................................... B
Inserting an Airway with "Via"................................................................................................................................. C
Inserting a Waypoint................................................................................................................................................D
Fix Info..................................................................................................................................................................... E
Inserting a New Destination.....................................................................................................................................F
Holding Pattern........................................................................................................................................................G
Offset........................................................................................................................................................................H
Alternate Function..................................................................................................................................................... I
Enable ALTN............................................................................................................................................................ J
DIR Key (Direct-to-Function)................................................................................................................................... K
OVFY (Overfly) Key................................................................................................................................................. L
"Update at".............................................................................................................................................................. M
DSC-22_20-30-20 Vertical Functions
DSC-22_20-30-20-05 General
General.....................................................................................................................................................................A
Vertical Flight Planning............................................................................................................................................B
Flight Phases........................................................................................................................................................... C
Vertical Revision...................................................................................................................................................... D
Vertical Constraints (Speed, Altitude, Time)........................................................................................................... E
DSC-22_20-30-20-25 FMS2 Honeywell
General.....................................................................................................................................................................A
Required Time of Arrival (RTA)...............................................................................................................................B
Wind - Temperature - QNH.....................................................................................................................................C
Constant Mach Segment.........................................................................................................................................D
Continued on the following page
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_20-40 Performance
DSC-22_20-40-10 Optimization
Continued from the previous page
General.....................................................................................................................................................................A
Optimization............................................................................................................................................................. B
DSC-22_20-40-20 Cost Index
Cost Index (CI)........................................................................................................................................................ A
DSC-22_20-40-30 Predictions
General.....................................................................................................................................................................A
Predictions for the Primary Flight Plan................................................................................................................... B
Computation of Predictions..................................................................................................................................... C
Predictions Displayed on the Navigation Display................................................................................................... D
Predictions Displayed on the MCDU.......................................................................................................................E
Type of Predictions.................................................................................................................................................. F
Examples of MCDU Predictions..............................................................................................................................G
Constraint Symbols (Star)....................................................................................................................................... H
Vertical Deviation...................................................................................................................................................... I
Operation Rules Concerning Predictions.................................................................................................................J
Other Computations.................................................................................................................................................K
Return-to-Trajectory Assumptions............................................................................................................................L
Energy Circle...........................................................................................................................................................M
Introduction to PERF and IDLE Factors................................................................................................................. N
PERF Factor............................................................................................................................................................O
IDLE Factor..............................................................................................................................................................P
Procedure to Modify the PERF and IDLE Factors................................................................................................. Q
DSC-22_20-50 Controls and Indicators
DSC-22_20-50-10 MCDU - Page Description
DSC-22_20-50-10-25 FMS2 Honeywell
General.....................................................................................................................................................................A
MCDU MENU Page.................................................................................................................................................B
INIT A Page.............................................................................................................................................................C
Route Selection Page..............................................................................................................................................D
IRS INIT Page......................................................................................................................................................... E
WIND Pages............................................................................................................................................................ F
INIT B Page.............................................................................................................................................................G
Fuel Prediction Page............................................................................................................................................... H
Flight Plan Pages......................................................................................................................................................I
Lateral Revision Pages............................................................................................................................................ J
Continued on the following page
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
Fix Info Page........................................................................................................................................................... K
Offset Page.............................................................................................................................................................. L
Airways Page.......................................................................................................................................................... M
Departure Pages......................................................................................................................................................N
Hold Pages.............................................................................................................................................................. O
Direct TO Page........................................................................................................................................................P
ARRIVAL Pages...................................................................................................................................................... Q
Alternate Page......................................................................................................................................................... R
Route Selection Page for Alternate.........................................................................................................................S
VERTICAL REVISION Pages..................................................................................................................................T
Step ALTS Page......................................................................................................................................................U
RTA Page................................................................................................................................................................ V
Data Index Pages................................................................................................................................................... W
Waypoint/Stored Waypoint/New Waypoint Pages...................................................................................................X
NAVAID/Stored NAVAID/New NAVAID Pages....................................................................................................... Y
Runways/Stored Runways/New Runway Pages..................................................................................................... Z
Route/Stored Route/New Route Pages................................................................................................................ AA
Aircraft Status Page.............................................................................................................................................. AB
P/N XLOAD Page................................................................................................................................................. AC
P/N Status Pages..................................................................................................................................................AD
Duplicate Names Page......................................................................................................................................... AE
Position Monitor Page........................................................................................................................................... AF
Position Monitor and Position Frozen Page......................................................................................................... AG
Selected NAVAIDS Page......................................................................................................................................AH
IRS Monitor Page................................................................................................................................................... AI
GPS Monitor Page.................................................................................................................................................AJ
Closest Airports Pages..........................................................................................................................................AK
Equi-Time Point Page............................................................................................................................................AL
Print Function Pages............................................................................................................................................ AM
ACARS Function Page......................................................................................................................................... AN
ACARS Function Page 1......................................................................................................................................AO
Uplink TO Data REQ Pages................................................................................................................................. AP
Uplink MAX TO Data Pages.................................................................................................................................AQ
Uplink FLX TO Data Pages.................................................................................................................................. AR
ACARS Function Page 2...................................................................................................................................... AS
PERF Page............................................................................................................................................................AT
PERF Takeoff Page.............................................................................................................................................. AU
PERF Climb Page................................................................................................................................................. AV
PERF Cruise Page...............................................................................................................................................AW
PERF Descent Page............................................................................................................................................. AX
Continued on the following page
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
PERF APPR Page................................................................................................................................................ AY
PERF Go Around Page.........................................................................................................................................AZ
PROG Pages.........................................................................................................................................................BA
Predictive GPS Pages...........................................................................................................................................BB
Report Page.......................................................................................................................................................... BC
Radio NAV Page...................................................................................................................................................BD
Secondary Pages.................................................................................................................................................. BE
Back Up NAV Pages.............................................................................................................................................BF
DSC-22_20-50-20 MCDU - Messages
DSC-22_20-50-20-35 FMS2 Honeywell
MCDU Message List................................................................................................................................................A
DSC-22_20-50-30 MCDU - Data Format List
MCDU Data Format List..........................................................................................................................................A
DSC-22_20-60 Other Functions
DSC-22_20-60-10 Effect of Baro Reference Setting
GENERAL................................................................................................................................................................ A
MCDU Altitude Predictions...................................................................................................................................... B
Target Altitude on PFD........................................................................................................................................... C
Procedures...............................................................................................................................................................D
DSC-22_20-60-20 Clear Key (Clearing Function)
Clearing the Scratchpad of Data or Messages.......................................................................................................A
Clearing Data Fields................................................................................................................................................ B
DSC-22_20-60-30 How to Execute a Diversion
General.....................................................................................................................................................................A
En Route Diversion with Several Airports Available............................................................................................... B
En Route Diversion over Oceanic or Desertic Area............................................................................................... C
Diversion Preparation on the Secondary Flight Plan..............................................................................................D
Miscellaneous...........................................................................................................................................................E
Execution of the Diversion.......................................................................................................................................F
Diversion to the Alternate Airport............................................................................................................................G
DSC-22_20-60-40 Engine Out
General.....................................................................................................................................................................A
Flight Management Part.......................................................................................................................................... B
Flight Guidance Part................................................................................................................................................C
Autothrust.................................................................................................................................................................D
Engine-Out Conditions.............................................................................................................................................E
Continued on the following page
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
Engine-Out SID........................................................................................................................................................ F
Engine-Out in CLB Phase (above acceleration altitude)........................................................................................ G
Engine-Out in Cruise Phase....................................................................................................................................H
Engine-Out in Descent Phase.................................................................................................................................. I
Engine-Out In Approach Phase............................................................................................................................... J
Engine-Out in Go-Around Phase.............................................................................................................................K
DSC-22_20-60-50 Secondary Flight Plan
Secondary Flight Plan............................................................................................................................................. A
DSC-22_20-60-60 Pilots/Stored Route Function
Stored Route Function.............................................................................................................................................A
DSC-22_20-60-70 Report Page
General.....................................................................................................................................................................A
Report Page Access................................................................................................................................................B
DSC-22_20-60-80 Closest Airports
Closest Airports........................................................................................................................................................A
DSC-22_20-60-90 Time Marker
General.....................................................................................................................................................................A
How to Insert a Time Marker.................................................................................................................................. B
DSC-22_20-60-100 Step ALTS
Step Climb/Step Descent........................................................................................................................................ A
DSC-22_20-60-110 Required Time of Arrival (RTA)
General.....................................................................................................................................................................A
Estimated Takeoff Time (ETT)................................................................................................................................ B
DSC-22_20-60-120 Equitime Point
Equitime Point..........................................................................................................................................................A
Equitime Point Entry................................................................................................................................................ B
DSC-22_20-60-130 MCDU Back Up Navigation
General.....................................................................................................................................................................A
Back Up NAV Selection.......................................................................................................................................... B
Back Up NAV Operation......................................................................................................................................... C
DSC-22_20-60-150 Descent Profile Optimization (if installed)
Descent Profile Optimization ..........................................................................................................................A
Continued on the following page
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_20-70 AOC Functions
Continued from the previous page
Flight Plan Initialization Through ACARS................................................................................................................A
Takeoff Data............................................................................................................................................................ B
Wind Data................................................................................................................................................................ C
DSC-22_20-80 Print Functions
Print Function...........................................................................................................................................................A
Print Function Access..............................................................................................................................................B
On Ground Before Engine Start..............................................................................................................................C
Example (FM Preflight Report)................................................................................................................................D
In Flight.................................................................................................................................................................... E
Example (FM Inflight Report)...................................................................................................................................F
Reaching the Gate After Landing........................................................................................................................... G
Example (FM Postflight Report).............................................................................................................................. H
DSC-22_20-90 Abnormal Operations
DSC-22_20-90-10 FMGC Reset
Automatic FMGC Reset and Resynchronization.....................................................................................................A
Manual FMGC Reset...............................................................................................................................................B
DSC-22_20-90-20 "CHECK GW" or "CHECK WEIGHT" Message
"CHECK WEIGHT" Message...................................................................................................................................A
DSC-22_20-100 Temporary Abnormal Behaviors
DSC-22_20-100-20 FMS2 HONEYWELL Temporary Abnormal Behaviors
Misalignment Of FMS F-PLN Legs For ILS Approaches........................................................................................ A
Incorrect Management Of ETA Entry On Predictive GPS Page............................................................................. B
Flight Number Erased Upon AOC Flight Plan Uplink............................................................................................. C
Loss Of FMS Position Further To IRS Loss........................................................................................................... D
Erroneous Fuel Prediction In The Case Of Descent With Two Altitude Constraints...............................................E
Unexpected Switch Of Speed Target When RTA Is Used......................................................................................F
Undue AP Disconnection or Reversion to V/S during Climb and Descent.............................................................G
VOR/DME and VOR/TACAN Not Automatically Tuned.......................................................................................... H
Optimum Target Speeds not Updated following the Automatic Deletion of a Step Climb........................................ I
Erroneous Lateral Guidance in NAV Mode with LOC Mode Armed during Approach.............................................J
Undue Reduction of the Speed Target in case of DIR TO/ABEAM while Flying a Constant Mach Segment.......... K
Loss of Fuel and Time Predictions During Takeoff Data Insertion..........................................................................L
Erroneous Trajectory during Procedures with a Turn Direction on a Leg with an Altitude Termination.................. M
Erroneous Vertical Profile during LOC B/C Approaches with a MAP Located Before the Runway Threshold........ N
Continued on the following page
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_20-100-40 All FMS Temporary Abnormal Behaviors
Continued from the previous page
Erroneous Predictions..............................................................................................................................................A
Spurious Engine Out Indication...............................................................................................................................B
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GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_20-10-00010128.0001001 / 17 AUG 10
Applicable to: ALL
The flight management and guidance system (FMGS) performs navigation functions and lateral and
vertical flight planning functions. It also computes performance parameters and guides the aircraft
along a preplanned route.
The Flight Management (FM) part controls the following functions:
‐ Navigation
‐ Management of flight planning
‐ Prediction and optimization of performance
‐ Management of navigation radios
‐ Management of displays
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NAVIGATION - GENERAL
FLIGHT CREW
OPERATING MANUAL
NAVIGATION
Ident.: DSC-22_20-20-05-00010129.0001001 / 17 AUG 10
Applicable to: ALL
Essential navigation functions are:
‐ Computation of position
‐ Evaluation of position accuracy
‐ Radio navigation tuning
‐ Alignment of Inertial Reference System.
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NAVIGATION - POSITION COMPUTATION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_20-20-10-00010130.0002001 / 16 MAR 11
Applicable to: ALL
Each FMGC computes its own aircraft position (called the "FM position") from a MIX IRS position and
a computed radio position, or a GPS position.
The FMGS selects the most accurate position, considering the estimated accuracy and integrity of
each positioning equipment.
GPS /INERTIAL is the basic navigation mode, provided GPS data is valid and successfully tested.
Otherwise, navaids plus inertial or inertial only are used. (Refer to DSC-22_20-20-10 Navigation
Modes).
MIX IRS POSITION
Ident.: DSC-22_20-20-10-00010131.0002001 / 01 OCT 12
Applicable to: ALL
Each FMGC receives a position from each of the three IRS s, and computes a mean-weighted
average called the “MIX IRS” position:
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - POSITION COMPUTATION
‐ If one of the IRS s drifts abnormally, the MIX IRS position uses an algorithm that decreases the
influence of the drifting IRS within the MIX IRS position.
‐ If one of the IRS s fails, each FMGC uses only one IRS (onside IRS or IRS 3). Each IRS position
and inertial speed are continuously tested. If the test fails, the corresponding IRS is rejected.
‐ When the "CHECK IRS (1, 2 or 3)/FM POSITION" message appears on the MCDU.
GPS POSITION
Ident.: DSC-22_20-20-10-00010132.0002001 / 23 JUN 15
Applicable to: ALL
Each IRS computes a mixed IRS /GPS position called the GPIRS position. For this, each IRS can
independently select their GPS source in order to maximize the availability of GPS data.
Of the three GPIRS positions that each FMGC receives, the FMS selects one GPIRS position based
on a figure of merit and priority.
The FMS uses the following hierarchy to perform the selection:
‐ Onside GPIRS position
‐ GPIRS 3
‐ Opposite GPIRS position.
If the GPIRS data does not comply with an integrity criterion that is based on a Horizontal Integrity
Limit (HIL) and on the automatic detection of failed satellites, the FMS rejects the GPS mode and
uses the radio position update.
The flight crew can deselect/select the GPS position on the SELECTED NAVAIDS page, if
necessary.
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AUTO FLIGHT - FLIGHT MANAGEMENT
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OPERATING MANUAL
NAVIGATION - POSITION COMPUTATION
Information about the GPS position is displayed on the GPS MONITOR page.
Note:
In nominal case, ADIRU 1 selects GPS 1 and ADIRU 2 selects GPS 2. The GPS selection
by ADIRU 3 depends on the position of the ATT HDG selector switch. If one of the GPS
source is rejected by the ADIRU s, all ADIRU s will select the same GPS source. As a
result, the data of the GPS that is not selected is dashed on the GPS MONITOR page. The
“GPS PRIMARY LOST” message may not be displayed.
RADIO POSITION
Ident.: DSC-22_20-20-10-00010669.0020001 / 01 OCT 12
Applicable to: ALL
Each FMGC uses onside navaids to compute its own radio position. These navaids are displayed on
the SELECTED NAVAIDS page.
The available navaids are:
‐ DME /DME
‐ VOR /DME
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
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OPERATING MANUAL
NAVIGATION - POSITION COMPUTATION
‐ LOC
‐ DME /DME -LOC
‐ VOR /DME -LOC.
It uses LOC to update the lateral position, using LOC beam during ILS approach.
LOC is also used for quick update, when in GPS /IRS mode.
If one or more navaids fail, each FMGC can use offside navaids to compute the VOR /DME , or the
DME /DME radio position.
The radio navaid selection is displayed on the DATA “SELECTED NAVAIDS” page.
(1)
VOR /DME selection (auto or manual) for display (onside VOR).
(2)
DME s automatic selection for DME /DME onside radio position.
(3)
ILS selection (auto or manual) for LOC update computation.
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
NAVIGATION - POSITION COMPUTATION
FLIGHT CREW
OPERATING MANUAL
FM POSITION
Ident.: DSC-22_20-20-10-00010135.0017001 / 17 AUG 10
Applicable to: ALL
At flight initialization, each FMGC displays an FM position that is a MIX IRS /GPS position (GPIRS):
‐ At takeoff, when the FM position is updated to the runway threshold position as stored in the
database, possibly corrected by the takeoff shift entered on PERF TO page.
‐ In flight, the FM position approaches the radio position or the GPS position at a rate depending
upon the aircraft altitude.
Note:
The FM position update at takeoff is inhibited when GPS PRIMARY is active.
BIAS
Each FMGC computes a vector from its MIX IRS position to the radio position or GPIRS position.
This vector is called the “bias”.
Each FMGC updates its bias continuously as long as a radio position or a GPIRS position is
available.
If an FMGC loses its radio/GPIRS position, it memorizes the bias and uses it to compute the FM
position, which equals the MIX IRS position plus the bias. Until the radio or the GPIRS position is
restored, the bias does not change.
The flight crew can update the FM position manually. This also updates the bias.
POSITION MONITOR
Ident.: DSC-22_20-20-10-00010136.0016001 / 07 MAY 13
Applicable to: ALL
The flight crew may check the position computation using the GPS MONITOR or POSITION
MONITOR page.
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FLIGHT CREW
OPERATING MANUAL
TAKEOFF UPDATE
Ident.: DSC-22_20-20-10-00010137.0017001 / 04 AUG 16
Applicable to: ALL
A takeoff update requires that the takeoff runway be part of the flight plan. This provides the most
accurate position update.
If the takeoff run starts at an intersection, enter a takeoff shift on the PERF TO page to refine the
takeoff update.
An accurate takeoff update ensures a precise aircraft position during departure.
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NAVIGATION - POSITION COMPUTATION
FLIGHT CREW
OPERATING MANUAL
NAVIGATION MODES
Ident.: DSC-22_20-20-10-00010138.0001001 / 19 JUL 11
Applicable to: ALL
The FMGS updates the FM position via the use of radio navaids or GPS , if available. It can use four
different FM navigation modes to make this update.
The decreasing order of priority is:
‐ IRS -GPS
‐ IRS -DME /DME
‐ IRS -VOR /DME
‐ IRS only.
During ILS approaches, the system performs a temporary lateral update, via one of the following
modes:
‐ IRS -GPS /LOC
‐ IRS -DME /DME -LOC
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NAVIGATION - POSITION COMPUTATION
‐ IRS -VOR /DME -LOC
‐ IRS -LOC.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
GENERAL
Ident.: DSC-22_20-20-20-00010448.0023001 / 27 MAY 13
Applicable to: ALL
The FMGS continuously computes an Estimated Position Uncertainty (EPU).
It is an estimate of how much the FM position diverged, and it is a function of the navigation mode
that the system uses.
CURRENT NAV MODE
IRS /GPS
EPU
(RATE or THRESHOLD)
(in meters).
IRS /DME /DME
Moves toward 0.28 NM.
IRS /VOR /DME
0.1 NM + 0.05 X DME DIST.
Minimum : 0.28 NM.
+8 nm/h for the first 30 min.
0 nm/h for the following 60 min.
+4 nm/h for the following 30 min.
0 nm/h for the following 60 min.
+2 nm/h after.
IRS ONLY
Note:
REMARK
FOM = Figure of Merit of GPS.
If above 0.28 NM, the FMS rejects the
GPS position.
EPU decreases from initial value to
0.28 NM.
Dependent on the distance between the
aircraft and the VOR /DME.
EPU increases continuously.
After an IRS alignment or at takeoff, the EPU is set to 0.2 NM.
ESTIMATED POSITION UNCERTAINTY
Ident.: DSC-22_20-20-20-00010499.0076001 / 01 OCT 12
Applicable to: ALL
The FMS displays the EPU to the flight crew and compares it with the Required Navigation
Performance (RNP):
‐ If the EPU does not exceed the RNP, accuracy is HIGH
‐ If the EPU exceeds the RNP, accuracy is LOW.
The RNP is displayed in the REQUIRED field of the PROG page. The displayed RNP is (in a
decreasing order of priority):
‐ The value that the flight crew entered
‐ The navigation database procedure value
‐ The system’s default value.
When a flight crew enters an RNP that is higher than the published value, one of the following
messages is displayed : "PROCEDURE RNP IS XX.XX", or "AREA RNP IS XX.XX". When this
occurs, the flight crew should verify the RNP value that was manually entered in the REQUIRED field
of the PROG page, and clear or modify it if necessary.
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
The "AREA RNP IS XX.XX" message is also displayed at the change of flight area if the new RNP
(default value) is smaller than the displayed RNP (manually entered).
EN ROUTE
TERMINAL
APPROACH
DEFAULT AREA RNP VALUES
2.0 NM
1.0 NM
GPS 0.3 NM
OTHER CASES 0.5 NM
When one FMGC changes the NAV accuracy from LOW to HIGH (or HIGH to LOW), the MCDU and
the ND display the "NAV ACCUR UPGRAD" (or DOWNGRAD) message.
These messages are inhibited when the navigation mode is IRS /GPS.
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
When in IRS /GPS mode, the GPS PRIMARY status combines two different criteria:
‐ The accuracy criterion previously described (HIGH/LOW accuracy)
‐ An integrity criterion: This is the capability to detect a failure and provide appropriate warning of it.
This criterion indicates the confidence that the flight crew can have in the FMS position.
If the GPS PRIMARY status complies with both criteria, "GPS PRIMARY" is displayed on the MCDU
(PROG page, [5R] field and scratchpad) and temporarily on the ND.
If the GPS PRIMARY status no longer complies with one of these criteria (Navigation downgraded
or integrity lost), the GPS PRIMARY status is lost and the MCDU and the ND display the "GPS
PRIMARY LOST" message. It is possible to clear the scratchpad message on the MCDU , but not on
the ND.
CAUTION
"HIGH" or "LOW" on the PROG page indicates the FM position accuracy, based
on estimated uncertainty. When GPS PRIMARY mode is lost, the flight crew must
periodically check this position accuracy. In GPS PRIMARY mode, the position
accuracy is always at HIGH.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
When the GPS is manually deselected, the "GPS IS DESELECTED" message is displayed on the
MCDU , 80 NM before the T/D or at approach phase transition.
FM/GPS POSITION DISAGREEMENT
Ident.: DSC-22_20-20-20-00010500.0011001 / 17 AUG 10
Applicable to: ALL
When the GPS PRIMARY function is active, and either of the FM positions deviate from the GPS
positions 1 or 2 by more than:
‐ A longitude threshold that depends on the latitude:
• 0.5' for latitudes below 55°
• 0.9' for latitudes at or above 55°, and below 70°.
‐ A latitude threshold of 0.5', regardless of the latitude,
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
then, the lower ECAM displays the NAV FM /GPS POS DISAGREE amber caution. The master
caution light comes on and the single chime sounds.
This amber caution is inhibited during the takeoff phase.
Above 70° of latitude, a longitude difference does not trigger the alarm.
PREDICTIVE GPS PAGE
Ident.: DSC-22_20-20-20-00010501.0001001 / 16 MAR 11
Applicable to: ALL
The predictive GPS page is only operative with the Honeywell ADIRS equipment. All fields are blank
with Litton ADIRS equipment.
The predictive GPS function predicts the availability of the GPS within ± 15 min of ETA at
destination, or at any waypoint entered by the flight crew.
Predictions are displayed on the predictive GPS page at time intervals of 5 min (+15 and –15 min of
ETA).
To access this page, press the 5L key of the PROG page. This page also enables the deselection of
up to 4 satellites at a time.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - EVALUATION OF POSITION ACCURACY
Intentionally left blank
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - RADIO NAVIGATION TUNING
GENERAL
Ident.: DSC-22_20-20-30-00010478.0001001 / 17 AUG 10
Applicable to: ALL
Radio navaids are tuned for two different purposes: Display and computation.
It is possible to perform tuning for display in three different ways:
‐ Automatic tuning via FMGC software
‐ Manual tuning via the MCDU RAD NAV page
‐ Manual tuning via the Radio Management Panel (RMP ) if both FMGC s or both MCDUs fail.
The FMGS automatically tunes the radio navaids for computation of the radio position.
Note:
The manual selection of a VOR or VOR /DME may prevent the FMGS from automatically
tuning a VOR /DME to compute position. In this case, the related MCDU displays “TUNE
BBB FFF.FF” (BBB = ident, FFF.FF = frequency).
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05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
NAVIGATION - RADIO NAVIGATION TUNING
FLIGHT CREW
OPERATING MANUAL
ARCHITECTURE
Ident.: DSC-22_20-20-30-00010479.0001001 / 31 AUG 17
Applicable to: ALL
‐ In dual mode and independent mode, each FMGC simultaneously tunes the navaids on its own
side (one VOR , one DME , one ILS , one GLS , one MLS and one ADF ). In these
modes, the flight crew can also manually tune the VOR (and associated DME ), ILS, GLS ,
MLS and ADF .
‐ In single mode, the valid FMGC tunes navaids on both sides. The flight crew can also use the
RAD NAV page to manually tune both VOR s, both ADFs , and the ILS / GLS / MLS .
Manual tuning has priority over automatic tuning.
Note:
If one receiver fails, both FMGCs use the operative radio receiver to compute the position
of the aircraft.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - RADIO NAVIGATION TUNING
VOR
Ident.: DSC-22_20-20-30-00010480.0001001 / 17 AUG 10
Applicable to: ALL
Each FMGC may tune only one VOR (manually or automatically).
Automatic tuning complies with the following priorities for tuning the VOR:
1. The specified navaid for the approach
2. The navaid that the flight crew should use to compute the current radio position
3. For display purposes:
‐ A navaid specified for the active flight leg
‐ The “TO” waypoint (TO WPT), if it is a navaid
‐ The “FROM” waypoint (FROM WPT), if it is a navaid
‐ A waypoint farther along the flight path, if it is a navaid
‐ The navaid closest to the current position of the aircraft.
The scratchpad displays “SPECIFIC VOR-D UNAVAIL”, if the VOR or the VOR /DME that the flight
crew requires for tuning is deselected.
DME
Ident.: DSC-22_20-20-30-00010481.0002001 / 17 AUG 10
Applicable to: ALL
Each FMGC automatically uses its four DME frequencies as follows:
‐ One DME frequency for display. It is possible to tune it manually or automatically. This DME
frequency is also used for VOR /DME position computation.
‐ Two DME frequencies in DME /DME mode for calculating the radio position of the aircraft. The
FMGC automatically tunes these as a function of their best accuracy. The flight crew does not
receive any indication that this process is happening.
‐ One DME frequency is connected to the ILS /DME.
ADF
Ident.: DSC-22_20-20-30-00010482.0001001 / 17 AUG 10
Applicable to: ALL
The FMGC automatically tunes one ADF , when the flight plan specifies a Non Directional Beacon
(NDB) approach and a fix in the approach is the “TO” waypoint.
The scratchpad displays “SPECIFIC NDB UNAVAIL”, if the NDB that the flight crew requires for
autotuning is deselected.
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05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - RADIO NAVIGATION TUNING
ILS
Ident.: DSC-22_20-20-30-00010483.0001001 / 17 AUG 10
Applicable to: ALL
Each FMGC automatically tunes one ILS frequency:
‐ In the PREFLIGHT or TAKEOFF phase, when the takeoff runway has an associated ILS.
‐ In the CLIMB, CRUISE, DESCENT, APPROACH, or GO-AROUND phase, when the type of
approach in the flight plan is ILS.
The scratchpad displays “RWY /ILS MISMATCH” when the flight crew manually tunes the ILS and
the entered frequency does not agree with the ILS or the LOC IDENT /FREQ that the flight crew
requests for automatic tuning. The FMGS logic does not enable the flight crew to modify the course
of an ILS when its frequency is identical to the ILS selected in the F-PLN.
SELECTION OF NAVAIDS ON MCDU PAGES
Ident.: DSC-22_20-20-30-00010485.0032001 / 31 AUG 17
Applicable to: ALL
The MCDU displays the navaids tuned by the FMGC on two pages:
‐ RADIO NAV Page
‐ SELECTED NAVAIDS Page.
RADIO NAV PAGE
This page shows which navaids have been tuned automatically or manually for display purposes.
SELECTED NAVAIDS PAGE
This page lists the navaids tuned by the onside FMGC. No navaids can be modified on this page.
The flight crew may deselect navaids and or GPS for the whole flight.
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05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
NAVIGATION - RADIO NAVIGATION TUNING
FLIGHT CREW
OPERATING MANUAL
MANUAL TUNING
Ident.: DSC-22_20-20-30-00010486.0002001 / 01 MAR 17
Applicable to: ALL
INSERT the identifier on the RADIO NAV page.
Preferably use the identifier.
Note:
The RAD NAV page may differ according to option installed (ADF 1, ADF2, xLS).
If the MCDU displays “NOT IN DATA BASE”:
INSERT the frequency.
DISREGARD the ident that appears in small font on the MCDU.
When a frequency is entered in the VOR field, the FMGC automatically associates to the tuned
frequency the closest navaid identifier with the same frequency, and displays it on the RAD NAV
page. This identifier may not correspond to the tuned navaid.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
NAVIGATION - RADIO NAVIGATION TUNING
FLIGHT CREW
OPERATING MANUAL
If the closest navaid, found in the database, is of a different type (e.g. VOR instead of VOR /DME
), the flight crew will obtain a partial tuning (e.g. VOR indication instead of VOR /DME indication).
ENTER the course.
If the flight crew intends to manually tune an ILS that is not in the Navigation Database or to
manually tune an ILS by its frequency (ident not entered), and if they do not enter the course, the
flight crew will not be able to arm approach modes.
NAVAID IDENTIFICATION
Ident.: DSC-22_20-20-30-00010487.0001001 / 31 AUG 17
Applicable to: ALL
CHECK the xLS (ILS or GLS or MLS ) identifier decoded on the PFD , and the VOR or ADF
on the ND.
When the navaid identifier is decoded in agreement with that published, no audio check is necessary.
When the decoding is different from the published one, check the audio. Due to morse coding
inaccuracy, wrong decoding may sometimes occur.
For GLS , the audio signal may be inaudible. However, the GLS identifier displayed on ND
and PFD is raw data. Consequently, for GLS , no audio check is necessary.
Note:
When a DME or a TACAN only is selected using either its identifier or its frequency, the
NDs do not display the decoded indication.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - ALIGNMENT OF INERTIAL REFERENCE SYSTEM
ALIGNMENT OF INERTIAL REFERENCE SYSTEM
Ident.: DSC-22_20-20-40-00010143.0013001 / 01 OCT 12
Applicable to: ALL
The FMGS uses the reference point coordinates of the departure airport to align the IRS.
It calls these up from the database automatically after the flight crew has entered a company route
or an origin-destination city pair and pressed the ALIGN IRS key on the MCDU. The flight crew can
adjust these coordinates manually to the gate position. A normal alignment takes 10 min, a fast
alignment 30 s.
Fast alignment is used to refine a position when time is limited.
Note:
If the “IRS IN ALIGN” memo flashes on the E/WD during the alignment process, it indicates
one of the following:
‐ It has detected excessive motion. (It automatically restarts the alignment)
‐ It has detected a disagreement between the position the MCDU has sent to the IRS ,
and the last memorized IRS position. The flight crew must enter new coordinates in the
MCDU , and realign the IRS
‐ It has detected a disagreement between the latitude the MCDU has sent to the IRS , and
the latitude the IRS has computed during the alignment
‐ The IRS has not received a position from the MCDU .
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - ALIGNMENT OF INERTIAL REFERENCE SYSTEM
Intentionally left blank
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAVIGATION - NAVIGATION DATABASE
GENERAL
Ident.: DSC-22_20-20-50-00010410.0001001 / 09 MAR 15
Applicable to: ALL
Overall navigation performance is mainly based on two elements:
‐ The accuracy of the aircraft position calculation
‐ The validity of the flight path definition, as extracted from the navigation database.
The level of validation depends on the type of operations. For example, JAA TGL 10 requires that, for
Precision RNAV in terminal area, providers and operators implement a quality assurance program for
the navigation database, which may include a navigation database validation process. The highest
level of validation is required for RNAV approach, with lateral and vertical navigation.
The navigation databases are revised every 28 days (AIRAC cycle). Flights should be conducted
with a navigation database that is within its cycle. This should be checked on the AIRCRAFT
STATUS MCDU page.
OPERATIONS WITH AN OUTDATED NAVIGATION DATABASE
Ident.: DSC-22_20-20-50-00010411.0001001 / 13 DEC 12
Applicable to: ALL
Airbus recommends flying with an updated navigation database. However, in exceptional
circumstances, and for a limited period of time, an aircraft can continue to operate beyond the end
date of the database cycle, provided it is approved by the national authorities.
The following precautions need to be considered:
‐ Prior to flight, identify recent changes on the intended route, with the navigation charts and
manuals. Some “strategic” new waypoints, not in the navigation database, may be worth entering
as DEFINED WAYPOINT on MCDU.
Note:
Flying with an outdated database, in an airspace that was recently restructured with
numerous new waypoints, should be avoided.
‐ Check SID , STAR, and approach procedures of departure, destination and required alternates for
recent changes.
Do not attempt to modify or manually construct terminal instrument procedures or approaches.
‐ Fly terminal instrument procedures and approaches with managed guidance, that are in the
navigation database and that have been checked for accuracy. Otherwise, fly the procedure, or
the approach, in selected guidance with conventional radio navaid raw data.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
NAVIGATION - NAVIGATION DATABASE
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT PLANNING - GENERAL
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING
Ident.: DSC-22_20-30-05-00010492.0002001 / 17 AUG 10
Applicable to: ALL
The flight crew uses the MCDU to insert flight plans into the FMGS:
‐ A lateral flight plan that defines the intended horizontal flight path
‐ A vertical flight plan that defines the intended speed and altitude profile for the aircraft to follow
while flying the lateral flight plan.
Note:
The flight planning function is available for both the primary and secondary flight plans.
The FMGS can contain two different flight plans:
‐ The ACTIVE flight plan, which is the basis for:
• Lateral and vertical guidance
• MCDU and ND display
• Radio navigation autotuning
• Performance predictions
• Fuel planning.
‐ The SECONDARY flight plan which the flight crew may use:
• When an alternate takeoff runway is probable
• To plan a diversion
• To prepare the next flight
• To compare predictions or evaluations.
Each flight plan is composed of the same elements:
‐ The primary flight plan, from origin to destination and missed approach
‐ The alternate flight plan, from destination to alternate destination.
The flight crew enters the flight plan in either of two ways:
‐ Automatically by selecting a company route. Such a selection will call all the elements of the route
out of the database.
‐ Manually by selecting an ORIGIN/DEST pair, and then selecting all successive waypoints,
procedures, and vertical constraints on the MCDU.
The flight crew may then modify the flight plan on the ground or in flight, by making lateral and
vertical revisions.
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A318/A319/A320/A321
FLIGHT PLANNING - GENERAL
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
General
GENERAL
Ident.: DSC-22_20-30-10-05-00011075.0002001 / 23 JUN 15
Applicable to: ALL
To insert the lateral flight plan, the flight crew can use either a company route number or an ICAO
four-letter city pair.
The lateral flight plan includes the following elements:
‐ Departure
• Takeoff runway
• SID
• En route transition.
‐ En route
• En route waypoints and airways.
‐ Arrival
• En route transition
• STARs/VIAs
• Landing runway with selected approach
• Missed approach.
‐ Alternate flight plan.
These elements are defined by waypoints and legs between the waypoints.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
The FMGC automatically strings the legs in sequence.
The flight plan has a discontinuity if any two waypoints do not have a leg defined between them.
The computer assumes that the aircraft will fly a direct leg between the two waypoints that define the
discontinuity.
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
FLIGHT PLANNING - LATERAL FUNCTIONS
1. When the aircraft overflies a flight plan discontinuity, the NAV mode automatically reverts
to the HDG (TRK) mode.
2. In HDG /TRK mode, a waypoint is sequenced when it passes behind the aircraft, and the
aircraft is less than 7 NM from it, and also when the difference between the track of the
aircraft and the track of the leg is less than 90 °.
If the aircraft is flying a discontinuity towards a waypoint, this waypoint is sequenced
when the aircraft is less than 5 NM from it.
The same conditions apply in NAV mode, except that no distance to the waypoint is
taken into account.
The FMGS automatically strings additional types of legs, when departure or arrival procedures (SID STAR - TRANS) are defined.
Those strings correspond to specific patterns that are heading or track referenced and are defined in
the database, such as:
‐ DME arc leg
‐ Holding pattern to a fix, or reverse turn
‐ Course-to-fix leg
‐ Radius-to-fix leg
‐ Heading leg
‐ MANUAL leg.
The flight crew cannot create these types of legs: They are part of the stored departure/arrival
procedures they have selected.
The flight crew can only create direct legs between manually defined geographic points (navaids,
airports, waypoints).
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
Note:
The departure and arrival procedures are defined in the database to minimize the amount
of memory required.
They are divided, as follows:
‐ DEPARTURE = SID + EN ROUTE TRANSITION
‐ ARRIVAL = APPR VIA + STAR + EN ROUTE TRANSITION
The SID is the central common part of the departure procedure, as the STAR is of the
arrival procedure. Enroute transitions (TRANS ) are the various possible trajectories defined
between the last SID point and the first enroute waypoints, and between the last enroute
waypoint and the first fix of the STAR . ”APPR VIAs” are the possible trajectories, defined
between the last STAR point and the first point of the approach.
MANUAL LEGS
Ident.: DSC-22_20-30-10-05-00010629.0001001 / 17 AUG 10
Applicable to: ALL
A MANUAL leg stays on a constant TRK or HDG and has no termination point. The flight crew
cannot insert it into a flight plan manually: it is part of a given procedure such as a SID or a STAR.
When the aircraft is flying a MANUAL leg, the NAV mode remains engaged and predictions assume
that the aircraft will fly a direct leg from its present position to the next waypoint (DIR TO ). When the
aircraft is cleared to fly to the next waypoint of the flight plan, the flight crew performs a DIR TO.
Note:
1. In NAV mode, a MANUAL leg is sequenced only by performing a DIR TO.
2. The use of the descent mode (DES) on a MANUAL leg is not recommended.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLAN CONSTRUCTION
Ident.: DSC-22_20-30-10-05-00011076.0032001 / 01 OCT 12
Applicable to: ALL
There are three ways of defining the route:
1. A company route, that is in the database, and is known by the flight crew.
The flight crew enters the name of the CO RTE into the [1L] field of the INIT A page. This action
enters all the elements of the flight plan. The database usually includes an alternate route
associated with the destination.
2. A company route, that is in the database, but the flight crew does not know it is there.
The flight crew enters a city pair in the [1R] field. The ROUTE SELECTION page automatically
appears and enables the flight crew to review all stored routes between the two cities before
selecting one of them.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
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FLIGHT CREW
OPERATING MANUAL
3. There is no company route between the two cities.
The flight crew enters the city pair in the [1R] field. The ROUTE SELECTION page appears and
displays “NONE”.
The flight crew has to manually construct the entire flight plan.
For procedure, Refer to PRO-NOR-SRP-01-10 Flight Plan Initialization - General.
FLIGHT PLAN CAPACITY
Ident.: DSC-22_20-30-10-05-00010631.0002001 / 17 AUG 10
Applicable to: ALL
In terms of flight plan capacity, the FMS takes into account 3 flight plans:
‐ The active flight plan
‐ The secondary flight plan
‐ The temporary flight plan.
Each flight plan can contain up to 200 legs. If a flight plan contains 200 legs, and if the flight crew
attempts to perform a lateral revision that increases the number of legs of this flight plan, the
FMS rejects the revision and the MCDU displays the “F-PLN FULL” message. For the active and
GLG A318/A319/A320/A321 For A/C: HC-CRU
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← C to D →
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secondary flight plans, the primary parts must contain less than 135 legs, and the alternate parts
must contain lesgs than 65 legs.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←D
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AIRCRAFT SYSTEMS
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FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
LATERAL REVISIONS
Ident.: DSC-22_20-30-10-05-00010632.0002001 / 07 APR 17
Applicable to: ALL
The flight crew can revise the lateral flight plan following two types of revisions:
1. Lateral revisions that have an immediate effect on the active flight plan:
‐ The flight crew inserts a new waypoint directly on the F-PLN page, deletes, or changes a
waypoint from it:
When the flight crew enters a new waypoint, which does not exist in the flight plan, the following
waypoint moves down the flight plan, with a discontinuity shown after the new waypoint.
‐ The flight crew adds a direct leg (DIR TO) from his present position to a selected waypoint:
The flight crew can change the “TO” waypoint of the active leg. The DIR TO function gives
access to DIR TO , DIR TO ABEAM, or DIR TO/INTERCEPT. The active leg then goes from the
present position (T/P) to the waypoint selected or inserted as the new “TO” waypoint.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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FLIGHT PLANNING - LATERAL FUNCTIONS
2. Lateral revisions that lead to a temporary flight plan (TMPY) before they take effect:
The flight crew creates a temporary flight plan, then inserts it as a revision to the active flight plan.
The flight crew does this when selecting, deleting, or modifying several waypoints of an airway or
procedure at once (SID , STAR , HOLD, TAKEOFF or LANDING RWY ). This modification is made
on specific “LAT REV” pages from the flight plan page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←E→
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
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FLIGHT PLANNING - LATERAL FUNCTIONS
Possible revisions are:
‐ Insert or modify the departure procedure
‐ Insert or modify the arrival procedure
‐ Insert a waypoint
‐ Change the destination
‐ Insert an airway
‐ Insert an offset
‐ Insert a holding pattern
‐ Select or enable an alternate flight plan
‐ Fix information.
The purpose of the temporary flight plan is to allow the flight crew to check a revision on the
MCDU and on the ND before inserting the changes into the active flight plan. It is a copy of the
active flight plan that has been changed according to the flight crew revision. While it is displayed,
the aircraft will continue to follow the original active flight plan.
No predictions are computed or displayed on the pages of the temporary flight plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←E→
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12 APR 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
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OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
A temporary flight plan is displayed for a check and/or new modification. Inserting the temporary
revision will modify the active flight plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
DSC-22_20-30-10-05 P 11/12
12 APR 17
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OPERATING MANUAL
Intentionally left blank
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DSC-22_20-30-10-05 P 12/12
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AIRCRAFT SYSTEMS
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OPERATING MANUAL
FMS2 HONEYWELL
GENERAL
Ident.: DSC-22_20-30-10-15-00005067.0001001 / 09 FEB 11
Applicable to: ALL
The lateral revision function allows the pilot to create or modify the following parts of the flight plan:
‐ Airway
‐ Waypoint
‐ New destination
‐ Holding pattern
‐ Offset
‐ Alternate
‐ Fix information
Each time the pilot activates one of the above-listed revisions, he accesses a temporary flight plan
that enables the modification to be checked before inserting it in the active flight plan. The crew
selects these functions by pressing the left keys on F-PLN A or B.
‐ Direct to and overfly functions are accessed via the MCDU keys. No temporary flight plan is
created with these functions.
‐ “Update at” capability is a specific function that manually updates the FM position. It does not .use
a temporary flight plan, but the pilot must confirm its insertion before it is activated.
TEMPORARY F-PLN (TMPY)
Ident.: DSC-22_20-30-10-15-00000460.0001001 / 01 OCT 12
Applicable to: ALL
When a pilot makes a lateral revision to the F-PLN , the FMGS creates a temporary flight plan. This
is a copy of the active F-PLN, but is corrected by the lateral revision in progress.
The aircraft continues to follow the active F-PLN, until the temporary revision is inserted.
The revision appears in yellow font on both MCDU s and NDs.
‐
‐
‐
‐
‐
‐
Lateral and vertical revisions cannot be made to a temporary F-PLN.
Only one temporary F-PLN may be accessed at a time.
The “DIRECT TO” function, when used, erases a temporary F-PLN.
When a DIR TO is in process, a temporary revision cannot be displayed on the other MCDU.
A TMPY F-PLN changes the title of the flight plan pages. (TMPY appears in all titles).
No predictions are computed for a temporary flight plan (dashes are displayed).
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A to B →
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FLIGHT PLANNING - LATERAL FUNCTIONS
Temporary data is displayed in yellow (ND and MCDU). Once inserted, it becomes active and is
displayed in green.
INSERTING AN AIRWAY WITH "VIA"
Applicable to: ALL
Ident.: DSC-22_20-30-10-15-E-00012828.0001001 / 14 MAY 12
GENERAL
In the active flight plan, the pilot can insert up to 5 successive airway segments, going from a
revised waypoint or ending at a given waypoint of the flight plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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← B to C →
DSC-22_20-30-10-15 P 2/56
24 JAN 17
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FLIGHT PLANNING - LATERAL FUNCTIONS
SELECT the revised waypoint (here CDN).
PRESS [ 5R ] to select the airways function.
Ident.: DSC-22_20-30-10-15-E-00012829.0001001 / 14 MAY 12
THE PILOT WISHES TO INSERT SUCCESSIVE AIRWAY SEGMENTS FROM A WAYPOINT
e.g. from CDN - Airways UB19 – Airways UB25 – Ending point AAA.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←C→
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24 JAN 17
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FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the first airway in the scratchpad (here UB19).
PRESS [ 1L ] to insert it into the VIA field.
WRITE the second airway in the scratchpad (here UB25).
PRESS [ 2L ] to insert it into the VIA field.
The system automatically determines the first downpath intersection point between the 2 airways.
‐ If the airways have a common waypoint, the system selects it as the ending point of the first
VIA.
‐ If they have no common waypoint, but have a single intersection, the system creates this
intersection as an FM -computed point and displays X followed by the airway IDENT (here
XUB25).
‐ If they have no common waypoint or intersection, the system displays NO INTERSECTION
FOUND in the scratchpad.
Once the pilot has entered the required airways (up to 5), he must enter the ending point of the
last selected airways:
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←C→
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24 JAN 17
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FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the ending waypoint in the scratchpad (here AAA).
PRESS [ 2R ] to insert the ending waypoint into the TO field.
Note:
If two waypoints with the same IDENT belong to the same airway, the DUPLICATE
NAMES page will not be called up, and the system selects the first one in the database.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←C→
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24 JAN 17
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FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-E-00012830.0001001 / 01 OCT 12
THE PILOT WISHES TO INSERT ONE AIRWAY SEGMENT TO AN ENDING WAYPOINT
WRITE the airway IDENT in the scratchpad (here UB19).
PRESS [ 1L ] to insert it into the VIA field.
WRITE the ending waypoint in the scratchpad (here PON).
PRESS [ 1R ] to insert it into the TO field.
Note:
‐ If the revise waypoint, or the ending waypoint, does not belong to the entered airway,
the system displays AWY /WPT MISMATCH in the scratchpad.
‐ If two waypoints with the same IDENT belong to the same airway, the DUPLICATE
NAMES page will not be called up and the system selects the first one in the database.
Ident.: DSC-22_20-30-10-15-E-00012831.0001001 / 09 FEB 11
FLIGHT PLAN INSERTION
The flight crew either inserts the flight plan directly from the AIRWAYS page, or from the TMPY
F-PLN page. In both cases:
PRESS [ 6R ] to insert the temporary flight plan. Clear flight plan discontinuity, as needed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←C
DSC-22_20-30-10-15 P 6/56
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
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FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
INSERTING A WAYPOINT
Applicable to: ALL
Ident.: DSC-22_20-30-10-15-F-00012832.0001001 / 09 FEB 11
GENERAL
Waypoints can be inserted in two ways:
‐ Directly into the flight plan. All modifications go directly into the active flight plan. No temporary
flight plan is created.
‐ By means of a lateral revision at the “NEXT WAYPOINT”, a process that creates a temporary
flight plan.
The second method enables the temporary flight plan to be checked before it is inserted.
Ident.: DSC-22_20-30-10-15-F-00012833.0001001 / 09 FEB 11
WAYPOINT IDENTIFICATION
The pilot can identify a waypoint by:
‐ Its identifier (if it is in the navigation database).
‐ A Latitude/Longitude (LL).
‐ A Place/Bearing/Distance (PBD). The waypoint is defined by its bearing and distance from a
place.
‐ A Place-Bearing/Place-Bearing (PBX). The waypoint is defined by the interception of 2 radials
from 2 places.
‐ A Place/Distance (PD). The waypoint is defined by a distance from a place, along the F-PLN.
Note:
If a slash or a dash is not entered properly, the MCDU displays a “FORMAT ERROR”
message.
When the Flight Management Guidance System receives a waypoint that is not in the database,
it identifies it as LLxx or PBD xx or PBX xx or PD xx (xx is a two-digit number between 01 and 20)
and stores it in the stored waypoints file of the database.
Note:
When NAV mode is engaged, the crew cannot modify the “TO ” waypoint (active leg)
using the waypoint insertion function. If the crew wants to modify it, the DIR TO function
will be used.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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24 JAN 17
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FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-F-00012834.0001001 / 14 MAY 12
WAYPOINT INSERTED DIRECTLY IN THE FLIGHT PLAN
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←D→
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A318/A319/A320/A321
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FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the waypoint identifier or LAT /LONG, Place/Bearing/Distance or
Place-Bearing/Place-Bearing into the scratchpad. (Example: Place: LMG, Bearing: 330 °,
Distance: 135 NM).
PRESS the appropriate key to enter the waypoint into the flight plan. The rule is that the new
waypoint appears next to the pressed key, and the previous waypoint moves down the flight plan
path.
This operation creates a discontinuity between the new waypoint and the previous one.
The new flight plan will have to be cleared of the discontinuity and some waypoints erased.
Ident.: DSC-22_20-30-10-15-F-00012835.0001001 / 01 OCT 12
ALONG TRACK WAYPOINT INSERTION
On the F-PLN or STEP ALTS page, the pilot can enter an along track waypoint, defined as a
place/distance waypoint.
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←D→
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the waypoint identifier and distance from this place.
According to the sign of the distance, the crew may define an along track waypoint before or after
the revised place. (Example: AMB/-040).
PRESS the appropriate key adjacent to the place identifier. The system automatically positions the
waypoint in the flight plan.
This operation does not create any discontinuity.
The system does not accept an along track waypoint entered at the FROM waypoint.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←D→
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24 JAN 17
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FLIGHT CREW
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FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-F-00012836.0001001 / 01 OCT 12
WAYPOINT INSERTED THROUGH THE USE OF “NEXT WAYPOINT”
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
SELECT the lateral revision (LAT REV) function at an appropriate waypoint.
WRITE the waypoint identifier, or LAT /LONG, or Place/Bearing/Distance, or Place-Bearing /
Place-Bearing into the scratchpad.
ENTER it in the brackets under NEXT WPT (next waypoint).
INSERT the temporary flight plan by pressing the [ 6R ] key.
CLEAR the F-PLN discontinuity, as appropriate.
Ident.: DSC-22_20-30-10-15-F-00012837.0001001 / 14 MAY 12
LATITUDE/LONGITUDE CROSSING WAYPOINT INSERTION
This function allows the insertion of one or several points along the flight-plan beyond the revised
waypoint, at fixed latitude or longitude intervals (INCR) from a specified latitude or longitude.
These waypoints are not considered as part of the pilot-defined elements. The system deletes
them when sequenced.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←D→
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AIRCRAFT SYSTEMS
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OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the latitude (NXX, XXN, SXX or XXS), the required increment in degrees between the
successive waypoints, and the number of required waypoints.
(Example: The pilot wants to obtain 3 points, every degree from latitude N46: He enters N46/1/3).
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←D→
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FLIGHT CREW
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FLIGHT PLANNING - LATERAL FUNCTIONS
PRESS [ 2R ] to insert it into the LL XING/INCR/NO field.
PRESS [ 6R ] to insert the new waypoints in the flight plan without discontinuity.
The system does not store these waypoints in the database.
FIX INFO
Applicable to: ALL
Ident.: DSC-22_20-30-10-15-G-00012838.0008001 / 09 FEB 11
GENERAL
When using the FIX INFO function, the flight crew defines waypoint intersections of the flight plan
with radials, circle or abeam associated to a fix.
When the flight crew inserts the intersection points, the system automatically identifies these
points, but does not store them in the navigation database.
Ident.: DSC-22_20-30-10-15-G-00012839.0008001 / 01 OCT 12
INSERTING A RADIAL INTERCEPT WAYPOINT
The flight crew accesses the radial intercept function from the lateral revision page at the origin or
“from” waypoint.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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← D to E →
DSC-22_20-30-10-15 P 14/56
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GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
FLIGHT PLANNING - LATERAL FUNCTIONS
←E→
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OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
WRITE the reference fix identifier into the scratchpad (here POI), and ENTER it [1L].
It may be any database or pilot-defined fix.
WRITE the radial into the scratchpad (here 120 °) and ENTER it [ 2L ].
The defined radial appears as a blue dashed line on the ND.
If the radial line intersects the active flight plan, the system computes the time, distance to go, and
the altitude at the intersection point.
Up to two radials can be entered.
SELECT the required radial to insert the associated waypoint into the flight plan (if needed):
The system automatically assigns its IDENT as the three first characters of the reference fix
IDENT , followed by the radial. (Example: ABC 140). The blue dashed line disappears from the
ND.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←E→
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24 JAN 17
AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-G-00012840.0001001 / 01 OCT 12
INSERTING A CIRCLE INTERCEPT WAYPOINT
WRITE the reference fix identifier into the scratchpad (here POI), and ENTER it [1L].
WRITE the circle radius in the scratchpad (here 20 NM), and ENTER it [ 4L ]:
The defined circle appears as a blue dashed circle on the ND. If the circle intersects the active
flight plan, the system computes the time, along path distance to go and altitude at the first
intersection point from the current aircraft position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←E→
DSC-22_20-30-10-15 P 17/56
24 JAN 17
AIRCRAFT SYSTEMS
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FLIGHT PLANNING - LATERAL FUNCTIONS
SELECT the required radius to insert the associated waypoint into the flight plan (if needed).
The system automatically assigns its IDENT as a D, followed by the radius, and followed by the
three first characters of the reference fix IDENT (example D020 POI). The blue dashed circle
disappears from the ND.
Ident.: DSC-22_20-30-10-15-G-00012841.0008001 / 01 OCT 12
INSERTING AN ABEAM INTERCEPT WAYPOINT
WRITE the reference fix identifier into the scratchpad (here POI), and ENTER it [1L]
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←E→
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
SELECT the ABEAM prompt [ 5L ]:
A blue dashed line from the reference fix and perpendicular to the flight plan appears on the
ND. The system computes the radial, time, distance to go, altitude and predictions related to the
waypoint abeam the reference fix.
SELECT [ 5L ] to insert the abeam intercept waypoint into the flight plan (if needed):
The system automatically assigns its identifier as AB, followed by the first five characters of the
reference fix identifier (Example ABXYZ). The blue dashed line disappears from the ND.
INSERTING A NEW DESTINATION
Ident.: DSC-22_20-30-10-15-00000471.0001001 / 14 MAY 12
Applicable to: ALL
The pilot may define a new destination and insert it via the lateral revision page. The pilot may then
call up the new destination from any waypoint along the flight plan, except the FROM waypoint, the
destination, and the missed-approach waypoint. When the new destination has been inserted, a flight
plan discontinuity appears between the revision waypoint and the new destination. All waypoints
beyond the revision waypoint (including the previous destination and associated missed approach)
are deleted.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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← E to F →
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
SELECT the lateral revision function at an appropriate waypoint.
WRITE the new destination in the scratchpad.
Enter it in the brackets under “NEW DEST”.
INSERT the temporary flight plan ([ 6R ] key), and complete the flight plan to the new destination.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←F
DSC-22_20-30-10-15 P 20/56
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
HOLDING PATTERN
Applicable to: ALL
Ident.: DSC-22_20-30-10-15-A-00007222.0001001 / 09 FEB 11
GENERAL
This section describes holding patterns, associated guidance and flight crew procedures.
The Flight Management and Guidance Computer (FMGC) has three types of holding patterns that
the pilot can use in a flight plan.
Ident.: DSC-22_20-30-10-15-A-00007163.0001001 / 01 OCT 12
HOLD TO FIX (HF)
The holding pattern is always part of an arrival or departure procedure. The aircraft flies it once
and then automatically exits the holding pattern at the fix. The predicted speed in the holding
pattern is the lowest of the ICAO speed limit, max endurance speed, or any speed constraint.
Guidance to the fix in the holding pattern is similar to that on any leg of a flight plan. The HF
patterns are part of the navigation database and cannot be created by the crew.
Ident.: DSC-22_20-30-10-15-A-00007182.0001001 / 01 OCT 12
HOLD TO ALTITUDE (HA)
The aircraft flies the hold until it reaches the specified altitude. Then, it automatically exits the hold
at the fix.
The predicted speed for the holding pattern is the lowest of the ICAO speed limits, the max
endurance speed, or any speed constraint.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
The size of the holding pattern is a function of the predicted speed.
Guidance in a hold to altitude (HA) is similar to that for any leg of a flight plan.
The HAs are in the navigation database, as part of the arrival or departure procedures, and cannot
be created by the crew.
Ident.: DSC-22_20-30-10-15-A-00007206.0013001 / 01 OCT 12
HOLD WITH MANUAL TERMINATION (HM)
This type of holding pattern may be part of an arrival procedure, or the pilot may enter it at the
present position or at any flight plan waypoint.
The pilot will use this type of holding pattern to comply with a defined procedure or a clearance
limit, or to meet an operational need (such as losing altitude, holding for weather improvement, or
absorbing an ATC delay).
This type of holding pattern is exited according to the pilot's decision, not automatically.
There are 3 types of HM.
All are modifiable.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
DATABASE HOLD
If the holding pattern is part of the database, it is named DATABASE HOLD and all its
associated data (inbound course, turn direction, time/distance) are defined in the database. The
flight crew can modify this data.
COMPUTED HOLD AT...
If the holding pattern is not in the database, the FMGC designs a holding pattern and proposes
it to the pilot. The associated data consists of default values that the pilot can modify.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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24 JAN 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
HOLD AT...
If the pilot inserts into the active flight plan a holding pattern that is manually-corrected from
a hold defined by the FMGS, the screen displays a “HOLD AT...” page. The 2R field displays
REVERT TO DATABASE or REVERT TO COMPUTED to restore the database data, if
necessary.
PREDICTIONS AND GUIDANCE ASSOCIATED WITH A HM HOLDING PATTERN (HOLD WITH
MANUAL TERMINATION)
Before deceleration
If an altitude constraint is defined at the hold entry fix, then the FMS duplicates this constraint
on the hold exit.
However, different constraints may be inserted at entry and exit fixes.
Although the hold is inserted into the flight plan, the FMGS does not take it into account for
predictions until the aircraft enters the hold.
However, if the hold is not deleted by the crew, the FMGS schedules a deceleration point and
displays it on the ND.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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24 JAN 17
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FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
The FMGS predicts the estimated time and amount of fuel remaining at which the aircraft
must exit holding, so as to comply with the fuel policy specified on the fuel prediction page.
When the aircraft enters the holding pattern, the FMGS revises all predictions and assumes
the aircraft will fly one turn of the holding pattern.
All predictions are revised for one more holding circuit at holding fix overfly.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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24 JAN 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Upon reaching the speed change pseudo waypoint
The FMGS either causes the aircraft to decelerate to the hold speed (if managed speed
is active and NAV mode engaged), or displays “SET HOLD SPD” (set hold speed) on the
MCDU and primary flight display, if the flight crew had selected a speed target.
The default hold speed is the lowest of the:
‐ Maximum endurance speed
‐ ICAO limit holding speed
‐ Speed constraint (if any).
When no specific speed limit applies, the default hold speed is approximately equal to:
‐ Green Dot speed on the A318, A319, A320 (CFM) and A321
‐ Green Dot + 20 kt for altitude lower than 20 000 ft, on the A320 (IAE).
‐ Green Dot + 5 kt for altitude bigger than 20 000 ft, on the A320 (IAE).
The flight plan predictions for time and fuel do not yet consider that the hold will be flown,
however, the navigation display shows the hold entry and holding pattern trajectory.
Deceleration receives priority, so that when the aircraft is in descent with the descent mode
engaged, it will deviate above the descent path to decelerate. (VDEV becomes positive on
the progress page).
The flight plan page displays an immediate exit prompt.
If the flight crew presses the key next to “IMM EXIT” before arriving at the holding fix, the
aircraft will not enter the holding pattern, but will resume its phase-related managed-speed
profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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24 JAN 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
After reaching the hold entry fix
The aircraft enters the hold. The MCDU HOLD page displays the associated holding data:
‐ The inbound course (INB CRS)
‐ The TURN direction (L or R)
‐ The TIME/DIST
‐ The LAST EXIT time and the associated fuel to reach the alternate airport with no extra
fuel.
The FMS assumes that the aircraft will fly one turn of the holding pattern, and revises the
predictions accordingly.
When the holding pattern is defined by a leg time (and not a leg distance), the system revises
the size of the hold as a function of the target speed.
‐ If managed speed is active, the system uses the predicted holding speed to calculate the
size of the holding pattern.
‐ If the selected speed is active, the system uses the target speed selected by the flight crew
at the entry fix sequencing to calculate the size of the holding pattern.
‐ The VDEV displayed on the primary flight display and the PROG page when the aircraft
is flying in the HM (hold pattern with manual termination) is the difference between the
aircraft's current altitude and the altitude at which it should be when it reaches the hold exit
fix in order to be correctly positioned on the descent path.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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24 JAN 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
With IMM EXIT pressed (aircraft in the holding pattern)
The predictions and guidance assume that the aircraft is immediately returning to the hold fix.
Sequencing the hold fix, the aircraft exits the holding pattern and resumes its navigation.
The flight plan page displays “RESUME HOLD*” instead of “IMM EXIT*”.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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24 JAN 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
HOLD EXIT PROCEDURE
Position (1) If “IMM EXIT” pressed, the aircraft will exit at the next fix overfly.
Position (2) If “IMM EXIT” pressed, the aircraft will make an immediate turn to the fix where the
hold will be exited.
If managed speed is active:
The computer sets the target speed to the applicable speed of the current phase (for
example, speed constraint, ECON speed, or speed limit).
The computer then bases its predictions on the assumption that the flight will continue on
the descent path, if the aircraft is in descent.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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24 JAN 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
If DES mode is engaged:
The following applies:
‐ The holding pattern is never included in the descent path computation.
‐ The flight crew cannot enter altitude and speed constraints at the hold exit fix. (This is
only allowed at the hold entry fix).
‐ The vertical guidance in the HM , during the descent phase, calls for a constant
-1 000 ft/min. But the computer considers altitude constraints that will take effect farther
down the flight path as it calculates vertical guidance and predictions. The system will not
allow the aircraft to descend below the next altitude constraint, neither the FCU selected
altitude. If the aircraft reaches the next altitude constraint, it will level off and the altitude
constraint mode will engage.
With RESUME HOLD pressed
If the flight crew presses the key next to “RESUME HOLD”, the aircraft remains in the holding
pattern, and “IMM EXIT” is displayed again.
After that, each time the aircraft flies over the holding fix, the system updates the predictions
for one more holding circuit.
HOLDING PATTERN ENTRIES
The FMGS offers three types of entry into holding patterns:
1. Direct entry
2. Teardrop entry
3. Parallel entry
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
DSC-22_20-30-10-15 P 30/56
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
1. The direct entry
2. The teardrop entry
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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24 JAN 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
3. The parallel entry
Note:
If the leg the aircraft is flying toward the holding fix is on a “limit” between a teardrop
entry and a parallel entry, the FMGC may compute and display either of the two
entries. The pilot should keep this in mind and should not assume that the FMGC is
malfunctioning.
If the flight plan leg toward the hold entry fix is on a course that is the reciprocal of
the inbound course of the holding pattern, the aircraft will fly a parallel entry.
Ident.: DSC-22_20-30-10-15-A-00007220.0001001 / 09 FEB 11
PROCEDURE TO INSERT A HOLD (HOLD WITH MANUAL TERMINATION)
The HOLD prompt allows the flight crew to enter a hold with manual termination (HM), at the
revised waypoint or at the present position.
The flight crew accesses the HOLD page from a lateral revision at the present position (PPOS) or
at a waypoint.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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24 JAN 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
SELECT lateral revision at present position (PPOS), or an applicable waypoint.
PRESS the HOLD prompt [3L].
A TMPY F-PLN is created and if applicable, the database hold is proposed.
If no database hold is available, the computed hold is proposed.
CHECK and (if necessary) MODIFY the HOLD data.
CHECK the temporary flight plan and INSERT it, if appropriate.
Ident.: DSC-22_20-30-10-15-A-00007219.0001001 / 09 FEB 11
PROCEDURE TO DELETE A HOLD (HOLD WITH MANUAL TERMINATION)
CLEAR the HOLD directly in the flight plan, as can be done for a normal waypoint.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
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A318/A319/A320/A321
FLIGHT CREW
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FLIGHT PLANNING - LATERAL FUNCTIONS
OFFSET
Applicable to: ALL
Ident.: DSC-22_20-30-10-15-B-00007230.0009001 / 14 MAY 12
GENERAL
Offset allows the flight crew to define on offset of the active flight plan. The offset can be
immediate or deferred to start on a downstream leg. The offset will end by default or at a
pre-planned end waypoint. Additionally, the flight crew can specify the intercept angle used for the
transitions to and from the offset path.
In most cases, the pilot will use it enroute because of an ATC clearance, or to avoid bad weather
expected along the flight plan route.
This page is accessed from LAT REV page at the FROM waypoint or at any waypoint downpath
the flight plan, except the destination airport.
After inserting the offset in the flight plan, the flight plan page shows OFST in its title, left or right
arrows are displayed on every label line between the start and end waypoints of the offset, and the
navigation display shows the offset flight plan with a solid green line and the original flight plan with
a dashed green line.
The offset is cleared:
‐ Automatically (holding pattern, approach), or
‐ Manually with the clear (CLR) key, or by entering “o” in the offset value field [ 1L ] or by using
the delete prompt in the OFFSET page.
Note:
If the pilot enters an OFFSET when the aircraft is too close to the TO waypoint, the
FMGS may refuse to accept it, in which case the MCDU displays the “ENTRY OUT OF
RANGE” message.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H→
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-B-00007207.0010001 / 01 OCT 12
INSERTING AN OFFSET
SELECT LAT REV page at a waypoint.
SELECT OFFSET function by pressing [ 2L ].
WRITE the required offset value and direction (for example, L5 or 5L), and enter it into [ 1L ] field.
CHECK or INSERT the START WPT from the list in [ 3L ] - [ 5L ] fields or manually enter it.
CHECK or ENTER the INTCP ANGLE in [ 1R ] field.
CHECK OR INSERT the END WPT from the list in [ 3R ] - [ 5R ] fields or manually enter it.
PRESS INSERT in [ 6R ] field to activate the OFFSET.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H→
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-B-00007218.0009001 / 14 MAY 12
MANUAL CANCELLATION OF AN OFFSET
There are two standard methods for cancelling an offset:
1. SELECT DIR TO a waypoint (the next waypoint, for example).
2. SELECT a Lateral Revision (LAT REV ) at FROM WPT.
CLEAR the OFFSET field or enter “0” in the OFFSET value field [1L], and press INSERT* in [6R]
to activate the temporary flight plan (cancelling OFFSET), or
PRESS the OFFSET DELETE prompt [6R] to activate the temporary flight plan (cancelling
OFFSET).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H→
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
ALTERNATE FUNCTION
Applicable to: ALL
Ident.: DSC-22_20-30-10-15-C-00007240.0001001 / 09 FEB 11
GENERAL
The ALTERNATE FUNCTION performs two actions:
‐ It reviews and defines alternate airports and inserts them into the flight plan.
‐ It allows a diversion to be activated through the ENABLE ALTN command.
Ident.: DSC-22_20-30-10-15-C-00007217.0009001 / 23 JUN 15
REVIEW AND SELECTION OF ALTERNATE AIRPORT
Several alternate airfields may be stored in the database and assigned to a destination. When
the pilot selects a company route (CO RTE) (or a city pair), the computer strings the preferred
alternate into the active flight plan.
The pilot may review the alternate airports on the ALTN page and, if the one selected is not
suitable because of weather or fuel considerations, another alternate may be strung into the active
flight plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← H to I →
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24 JAN 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
The pilot may define an additional alternate airport into the list, if necessary.
The ALTERNATE page shows the track and distance (airway or direct) between destination and
alternate, as well as fuel management data (EXTRA fuel, assuming the associated airfield is the
alternate airport). This data will help the pilot change the preferred alternate, if necessary.
Access the ALTERNATE page through the ALTN prompt on the LAT REV page at destination.
Alternate airfields are attached to the destination.
ENTERING NEW ALTERNATE INTO THE F-PLN
If the preferred alternate is unsuitable, proceed as follows:
SELECT F-PLN key on MCDU.
SELECT LAT REV at destination.
SELECT ALTN [5L].
SELECT an AIRFIELD IDENTIFIER.
INSERT the temporary flight plan.
Note:
If weather and destination airfield conditions permit, you may select “NO ALTN”.
Fuel predictions will be computed without alternate fuel.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←I→
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
SELECTION OF ANOTHER ALTERNATE
Fuel management information for flight to another alternate airfield may be obtained by selecting
the OTHER ALTN field.
SELECT LAT REV at DESTINATION.
SELECT ALTN [5L].
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←I→
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24 JAN 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
ENTER the airfield identifier in the brackets.
‐ If the airfield is not in the database, the NEW RUNWAY page automatically appears.
‐ If the airfield is in the database and there is a company route (CO RTE) to it, the ROUTE
SELECTION page automatically appears.
SELECT the route, as appropriate, or RETURN to the ALTN page.
ENTER the distance in the brackets (if required). XTRA fuel and track (TRK) will appear.
SELECT the other alternate (OTHER ALTN ) as a primary alternate if convenient. (EXTRA fuel
and DIST revert to AIRWAY distance).
INSERT it, if you want to have it as a primary alternate.
Note:
‐ The pilot can always overwrite the “OTHER ALTN ”. The new “OTHER ALTN” then
replaces the previous one, which is lost.
‐ The pilot can select OTHER ALTN as a primary alternate (active flight plan), to
replace any alternate on the initial list.
‐ If the pilot selects the other alternate as a primary alternate, and overwrites the
OTHER ALTN field by entering a new airport, the first one will remain a primary
alternate and the system will memorize a second OTHER ALTN.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←I→
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24 JAN 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
The pilot may enter a distance in the OTHER ALTN field. The system will compute the extra fuel
and the track for this distance.
PREDICTED DATA FOR ALTERNATE
Data predictions are based on:
‐ Aircraft weight being equal to landing weight at primary destination.
‐ Flight at FL 100 if the alternate F-PLN length is less than 100 NM , at FL 220 if the alternate
F-PLN length is comprised between 100 and 200 NM , or else at FL 310.
‐ Cost index 0.
‐ Constant wind (as entered in the alternate field of the DES WIND page).
‐ Constant delta ISA (equal to delta ISA at primary destination).
‐ The along flight path distance from the destination to the alternate airport. If the flight crew
enters an ALTN fuel value, this value is the one taken into account.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←I
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
ENABLE ALTN
Ident.: DSC-22_20-30-10-15-00000467.0009001 / 01 OCT 12
Applicable to: ALL
This enables the pilot to initiate a diversion by entering the alternate flight plan just after the revision
waypoint (with a discontinuity).
The pilot may have to adjust the resulting flight plan (use “direct to”, or add or suppress waypoints),
depending on the circumstances.
TO ACTIVATE THE PRIMARY ALTN:
SELECT a LAT REV at the “TO” waypoint (or at another suitable waypoint).
PRESS the ENABLE ALTN key.
INSERT the temporary flight plan.
ENTER an appropriate waypoint in DIRECT TO and adjust the flight plan.
ADJUST the cost index on the PERF page and the defaulted cruise flight level (CRZ FL ) on the
PROG page, as required.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J→
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
When ENABLE ALT is pressed at ABE, a flight plan discontinuity is created from ABE down to
destination and the alternate route is linked to the active flight plan.
DIR KEY (DIRECT-TO-FUNCTION)
Applicable to: ALL
Ident.: DSC-22_20-30-10-15-D-00007243.0001001 / 09 FEB 11
GENERAL
The pilot uses the “Direct To” function to define a direct leg from the present position to any
waypoint on the active flight plan or to any waypoint.
The designated waypoint may be entered by its identifier (if it is stored in the database) or by a
latitude/longitude, place/bearing/distance, or a place-bearing/place-bearing.
Note:
If the autopilot or flight director is in the heading/track or localizer mode, the “DIR TO ”
function engages the NAV mode.
Three functions are available through the DIR TO key:
‐ The DIR TO defines a direct leg from the present position to a specified waypoint.
NAV mode engages simultaneously to the DIR TO selection.
When the pilot uses DIR TO , the present position (PPOS ) becomes the “FROM” waypoint and
the active flight plan shows it as the T-P (turn point).
‐ The DIR TO /ABEAM function, defines the abeam waypoints along the direct leg. These
waypoints are the projection on the direct leg of the initial F-PLN waypoints located between the
aircraft position and the specified waypoint.
NAV mode engages simultaneously to the DIR TO/ABEAM selection.
‐ The DIR TO /INTCPT function allows the definition of a specified RADIAL INBOUND or
OUTBOUND at an inserted waypoint. The current aircraft track is used to compute the INTCPT
point with the specified radial.
NAV mode is armed simultaneously to the DIR TO /INTCPT selection.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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← J to K →
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A318/A319/A320/A321
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FLIGHT PLANNING - LATERAL FUNCTIONS
The ND displays the DIR TO leg as a temporary flight plan leg between current aircraft position
and specified waypoint. In case of a DIR TO /INTCPT, the leg is not displayed when the angle
between the current aircraft track and the intercept radial exceeds 160 °.
Ident.: DSC-22_20-30-10-15-D-00007216.0001001 / 14 MAY 12
PROCEDURE FOR DIR TO WAYPOINT
CASE 1. THE “TO” WAYPOINT IS IN THE FLIGHT PLAN
Example : DIR TO FRZ
PRESS the DIR key on the MCDU.
PRESS the line select key next to “FRZ”.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←K→
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A318/A319/A320/A321
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FLIGHT PLANNING - LATERAL FUNCTIONS
CASE 2. THE “TO” WAYPOINT DOES NOT BELONG TO THE FLIGHT PLAN
Example : Direct to ABC (ABC being an ident, LL or PBD or PBX (Place/Bearing-Place/Bearing)
PRESS the DIR key.
WRITE the waypoint identifier (e.g. ABC) into the scratchpad.
PRESS [1 L] to enter “ABC” in the “DIR TO” field.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←K→
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Clear the discontinuity and the waypoints that are not included in the new flight plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←K→
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-D-00007215.0001001 / 09 FEB 11
PARTICULAR CASES FOR USE OF DIR TO
‐ If the pilot is flying a manual leg (part of a SID or STAR ), the flight plan page displays “F-PLN
DISCONTINUITY”, preceded by “MANUAL” (see below).
These legs are specific heading or track legs flown with no defined end waypoint.
‐ When the pilot encounters a flight plan discontinuity, or if a major reset occurs, the flight plan
page displays “PPOS - F-PLAN DISCONTINUITY”, and the pilot looses managed guidance in
both the lateral and vertical plans.
The autopilot or flight director reverts to the basic HDG V/S (or TRK FPA) modes. Predictions
remain available and are based on the assumption that the aircraft will fly a direct leg from its
present position to the next waypoint.
‐ In both of these cases, the only way to get back to a standard flight plan is to perform a “
DIR TO ” to a designated waypoint.
‐ Following a DIR TO , the message “MAP PARTLY DISPLAYED” may appear on the NDs, if the
new flight plan includes a very long leg (Refer to DSC-31-45 Flags and Messages Displayed on
ND). When this message comes up, enter an intermediate waypoint to shorten the leg.
Note:
During cruise, the DIR TO function is not available as long as uplink wind data, received
through ACARS , is not inserted or cancelled on the CRUISE WIND page.
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
Ident.: DSC-22_20-30-10-15-D-00007208.0009001 / 22 OCT 13
PROCEDURE FOR DIR TO/ABEAM
Example : DIR TO/ABEAM BEROK
PRESS the DIR on the MCDU.
WRITE the waypoint identifier into the scratchpad (Example : BEROK).
PRESS [1 L] to enter the waypoint in the DIR TO field.
SELECT the ABEAM PTS function.
The display reverts to F-PLN A page.
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AIRCRAFT SYSTEMS
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OPERATING MANUAL
Note:
FLIGHT PLANNING - LATERAL FUNCTIONS
1. If, between two waypoints projected on the direct leg, there was a discontinuity in the
original flight plan, this discontinuity disappears between the corresponding abeam
points on the direct leg.
2. . Abeam waypoints computed from latitude/longitude-type waypoints are renamed by
the system as “AB XXXXX”, where “xxxxx” is an abbreviation in 5 characters, of the
latitude and longitude of the initial waypoints.
Ident.: DSC-22_20-30-10-15-D-00007221.0001001 / 14 MAY 12
PROCEDURE FOR DIR TO/INTERCEPT
PRESS the DIR key.
WRITE the waypoint identifier into the scratchpad.
PRESS [1L] to enter the waypoint in the DIR TO field.
In the [1R] and [2R] fields, the MCDU displays the functions radial inbound and radial outbound
from the waypoint.
If the waypoint belongs to the flight plan, the system displays the flight plan track as the default
inbound radial. The crew can modify it.
WRITE the required in or out radial into the scratchpad.
PRESS [1R] or [2R] to enter the radial in the required field.
The ND displays the entered radial as an amber dotted line : The pilot can still modify it.
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FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
PRESS [1R] or [2R] to confirm the DIR TO/INTERCEPT selection.
The display reverts to the F-PLN A page, the system arms the NAV mode, and engages the
HDG mode. The FROM waypoint is the aircraft position at the time of the DIR TO /INTERCEPT
selection. The MCDU indicates it as INBND or OUTBND.
Note:
1. If the waypoint does not belong to the flight plan, the system strings the
DIR TO/INTERCEPT leg to this waypoint, and inserts a discontinuity following the
waypoint.
2. A DIR TO/INTERCEPT cancels any active offset.
3. If the current AP /FD lateral mode is HDG or TRK , NAV becomes armed.
If the NAV mode was engaged, NAV becomes armed. FCU HDG or TRK must be
used to guide the aircraft.
The ND displays an intercept point, if the intercept angle is less than 120 °. The
system constantly updates it to reflect the current aircraft track and position with
respect to the intercept radial. The NAV mode engages when reaching the intercept
point.
EXAMPLE: RADIAL INBND
DIR TO AMB - RADIAL 200 ° INBOUND
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AIRCRAFT SYSTEMS
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OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
EXAMPLE: RADIAL OUTBND
DIR TO AMB - RADIAL 200 ° OUTBOUND
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FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
OVFY (OVERFLY) KEY
Ident.: DSC-22_20-30-10-15-00000469.0001001 / 01 OCT 12
Applicable to: ALL
The overfly key programs the Flight Management Guidance Computer to fly over a specific waypoint
or NAVAID. To use it:
PRESS the “OVFY” key.
A “Δ” appears in the scratchpad.
INSERT it by pressing the key adjacent to the waypoint to be overflown. [3L] in this example.
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FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - LATERAL FUNCTIONS
The pilot cannot cancel the overfly program. If you do not want to fly over the point you have entered,
use DIR TO (direct to) the next waypoint or engage the heading mode, whichever is more suitable.
The overfly function allows you to fly over a specific waypoint, and return the aircraft to the great
circle track.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←L
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A318/A319/A320/A321
FLIGHT PLANNING - LATERAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
"UPDATE AT"
Ident.: DSC-22_20-30-10-15-00000470.0001001 / 01 OCT 12
Applicable to: ALL
To manually change the position computed by the FMGC (FM position and bias), the pilot uses
“UPDATE AT” on the progress page.
Use this facility with extreme caution: It is apt to be inaccurate, because it relies on the pilot's
estimation of when a designated position has been reached.
WRITE the ident for the NAVAID (or waypoint or airport), or the coordinates, or the PBD or PBX
(Place/Bearing-Place/Bearing) at which the update is intended.
PRESS [3L] to enter the ident in the “UPDATE AT” field. The coordinates of the point, along with its
identifier (or “ENTRY”, if the identifier is not in the database), appear in that field.
PRESS [3R] to activate the update, when you estimate that you are at the position.
Note:
The system reinitializes the Estimated Position Error computation when a position update
is performed. This may lead to the appearance of a “NAV ACCUR DOWNGRAD” or “NAV
ACCUR UPGRAD” message.
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FLIGHT PLANNING - LATERAL FUNCTIONS
If the “UPDATE AT” does not properly take effect, it corrupts the FM position.
‐ In an area with good radio NAVAID coverage:
• If the update error is small, subsequent radio position updating will correct the FM position.
• If the update error is large, the system will reject any radio updating because its internal
“reasonableness test” will reject the various NAVAID s. Thus, the FM position will only be the
MIX IRS position corrected by the position bias, determined at the time of the update, and the
error will be maintained.
‐ In an area without proper NAVAID coverage, radio position updating will not be available and the
FM position, if incorrect, will remain incorrect until a new manual update is performed.
‐ Therefore, the pilot should only use “UPDATE AT” in case of a major position problem, such as:
• On the ground, no flight plan appears on the navigation display and ARC/ROSE NAV mode is
selected.
• A “CHECK IRS /FM POSITION” message appears on the MCDU.
• A “FM /IR POSITION DISAGREE” message appears on the ECAM.
When GPS PRIMARY is operative, the FM position will always converge towards the GPS position at
a rate depending on the aircraft altitude. Therefore, when GPS PRIMARY is operative, an inaccurate
“update at” will have a temporary effect on the FM position.
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←M
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FLIGHT PLANNING - VERTICAL FUNCTIONS
General
GENERAL
Ident.: DSC-22_20-30-20-05-00010939.0001001 / 01 OCT 12
Applicable to: ALL
The vertical flight plan is divided into the following flight phases:
Preflight - Takeoff - Climb - Cruise - Descent - Approach - Go-Around - Done.
All but “Preflight” and “Done” phases are associated with speed and altitude profiles.
Each phase has an assigned profile of target speeds. For each phase the FMGS computes an
optimum (ECON ) speed as a function of the strategic parameters (CI , CRZ FL , ZFW , ZFWCG,
block FUEL) and performance criteria.
ECON speed is the basis of the managed speed profile.
The ECON speed can be modified by:
‐ Presetting a speed or Mach number on the MCDU (PERF page) for the next phase
‐ Selecting on the FCU a speed or a Mach number for the active phase
‐ Inserting speed constraints or speed limits on the MCDU vertical revision (VERT REV) page.
The vertical flight plan includes vertical constraints (altitude, speed, time) that may be stored in the
data base or entered manually by the flight crew through vertical revision pages.
The flight crew may also define step climbs or step descents for cruise purposes. If the flight crew
plans to climb to a higher flight level or descend to a lower level, they can use a vertical revision at
any waypoint to insert the new level.
When all the vertical data has been defined, the FMGC computes the vertical profile and the
managed speed/Mach profile from takeoff to landing.
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A
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FLIGHT PLANNING - VERTICAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
VERTICAL FLIGHT PLANNING
Ident.: DSC-22_20-30-20-05-00011065.0002001 / 17 AUG 10
Applicable to: ALL
DATA ENTRY
The vertical flight plan provides the FMGS with all the data required to calculate performance and
predictions. This data is either entered by the flight crew or calculated by the FMS.
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OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
There are three categories of data:
‐ Strategic data, that applies to the overall flight profile:
• Cost Index (CI)
• Cruise Flight Level (CRZ FL) and STEP ALTS if any
• Zero-Fuel Weight (ZFW)
• Zero-Fuel Weight Center of Gravity (ZFWCG)
• Block Fuel.
‐ Weather data:
• Winds (for climb, cruise, descent, approach)
• Sea level atmospheric pressure (QNH) at destination
• Surface temperature (TEMP) at destination
• Temperature in cruise phase
• The Tropopause altitude (TROPO).
‐ Tactical data for the flight phases:
• Phase switching conditions:
▪ Setting of the thrust levers to TOGA or FLEX positions
▪ Reaching acceleration altitude (ACCEL ALT)
▪ Entering cruise (T/C)
▪ Initiation of descent (T/D)
▪ Passing a deceleration pseudo waypoint (DECEL PSEUDO WPT)
▪ Touchdown.
• Speed profile:
▪ V2
▪ Economy climb speed or Mach (ECON CLB SPD/MACH)
▪ Preselected speed or Mach (SPD/MACH PRESELECTION)
▪ Economy cruise Mach (ECON CRZ MACH)
▪ Constant Mach
▪ Economy descent Mach or speed (ECON DES MACH/SPD)
▪ Approach speed (VAPP).
• Vertical limitations:
▪ Speed limits (SPD LIMIT)
▪ Speed and altitude constraints (SPD AND ALT CSTR)
▪ Time constraints or Required Time of Arrival (RTA).
In addition to the data entered by the flight crew, the FMS uses some real flight data parameters
(CRZ SAT, actual wind) to improve the accuracy of the computed predictions.
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FLIGHT PLANNING - VERTICAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
FLIGHT PHASES
Ident.: DSC-22_20-30-20-05-00011024.0007001 / 22 MAR 16
Applicable to: ALL
The vertical flight plan is divided into flight phases. For each phase, the FMGS computes the
optimum speed or Mach Profile. These flight phases are:
Preflight - Takeoff - Climb - Cruise - Descent - Approach - Go-Around - Done.
FLIGHT PHASES
OPTIMUM SPEED PROFILE
PREFLIGHT
TAKEOFF
/
CLIMB
CRUISE
V2
(V2 + 10)
ECON CLB SPD / MACH
ECON CRZ MACH
DESCENT
ECON DES MACH / SPD
APPROACH
VAPP
(GS Min)
GO-AROUND
VAPP or current SPD,
whichever is greater.
Green Dot at ACC ALT
DONE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
/
SWITCHING CONDITIONS
TO NEXT PHASE
SRS takeoff mode engaged and N1 >
85 %(EPR ≥ 1.25) or Ground Speed >90 kt
At acceleration altitude or by engagement of
another vertical mode.
Reaching cruise FL
No step descent, and distance to destination
< 200 NM, or all engines operative and
selected altitude below Max [FL 200,
highest DES ALT CSTR]
‐ Overflying (DECEL ) pseudo waypoint
with NAV (or LOC */LOC ) mode
engaged and altitude <9 500 ft AGL
‐ Manual activation of the approach phase.
1. To Go-Around: When thrust levers at
TOGA detent, or
2. To Done: 30 s after landing, or
3. To Climb: When inserting a new CRZ FL.
1. To Approach: Manual activation of the
approach phase, or
2. To Climb: Above acceleration altitude,
modification of the destination airport by:
‐ Selection of the ALTN, or
‐ Insertion of a NEW DEST, or
‐ Insertion of a SEC F-PLN with a
destination airport different from the
destination airport of the active F-PLN.
To preflight: When INIT or PERF key
depressed.
C→
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FLIGHT CREW
OPERATING MANUAL
Note:
During the preflight phase, the flight crew inserts the flight plan, which includes all data
needed for the flight.
During the Done phase, the FMGC erases the data entered for the flight. If the descent
or the approach phase is inadvertently activated (manual approach phase activation, for
example), the flight crew may reselect a CRZ FL on the PROG page to reactivate the CRZ
phase.
VERTICAL REVISION
Ident.: DSC-22_20-30-20-05-00011025.0002001 / 17 AUG 10
Applicable to: ALL
The flight crew uses vertical revisions to enter or modify:
‐ The speed limit in the climb and descent phases
‐ An altitude or speed constraint at the revised waypoint
‐ A step climb or a step descent
‐ New wind data
‐ A time constraint.
The vertical revision page is accessed by pressing a right hand select key of the flight plan page.
VERTICAL CONSTRAINTS (SPEED, ALTITUDE, TIME)
Ident.: DSC-22_20-30-20-05-00012689.0005001 / 18 FEB 15
Applicable to: ALL
The flight crew enters speed, altitude and time constraint, either to comply with ATC requests and
specified procedures, or at the discretion of the flight crew, in response to operational variables.
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FLIGHT PLANNING - VERTICAL FUNCTIONS
SPEED LIMIT
A speed limit is associated with altitude as a maximum speed below a specified altitude (only one
in climb and one in descent).
ALTITUDE CONSTRAINT
Altitude constraints may be attached to specific waypoints in the climb, descent, or approach
phases.
To meet the altitude constraint, the aircraft must fly over the waypoint at an altitude equal, above
or below the altitude constraint as specified by the flight crew or the database.
Note:
The database may contain an altitude constraint window (two altitudes between which
the aircraft must fly passing over a given waypoint), but the flight crew cannot enter such
a constraint manually.
An altitude constraint is considered as missed if the system predicts more than 250 ft of difference
between the constraint value and the predicted aircraft altitude.
Altitude constraints are observed in CLB or DES or APP NAV-FINAL modes.
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FLIGHT PLANNING - VERTICAL FUNCTIONS
The FMS automatically deletes from the F-PLN:
‐ The altitude constraints ("AT", "AT OR ABOVE", or "AT OR BELOW") with values greater than
the CRZ FL
‐ The altitude constraint windows with the upper constraint greater than the CRZ FL.
The MCDU and the ND no longer display the deleted altitude constraints. These altitude
constraints are no longer used for the computation of the FMS climb and descent profile.
In that case, the scratchpad of the MCDU displays the "CSTR DEL ABOVE CRZ FL" message.
The FMS does not delete the altitude constraints at the CRZ FL . The FMS computes the T/D ,
in order to respect these altitude constraints. However these altitude constraints are not used for
guidance. If the flight crew initiates the descent before reaching the T/D , the aircraft descents
below the altitude constraints, and the altitude constraints are missed (amber on the MCDU and
on the ND).
SPEED CONSTRAINT
Speed constraints may be attached to specific waypoints in the climb, descent or approach
phases. To meet the speed constraint, the aircraft must fly over the waypoint with a speed equal or
less than the speed constraint.
A speed constraint is considered as missed if the system predicts an aircraft speed 10 kt greater
than the speed constraint.
Speed constraints are observed when NAV mode is engaged and speed target is managed.
Otherwise speed constraints are disregarded.
TIME CONSTRAINT
Time constraint may be attached to any waypoint except the "from" waypoint.
Note:
No constraint can be associated with go-around waypoints.
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OPERATING MANUAL
Intentionally left blank
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FLIGHT PLANNING - VERTICAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
FMS2 Honeywell
GENERAL
Ident.: DSC-22_20-30-20-25-00009323.0008001 / 14 MAY 12
Applicable to: ALL
The vertical revision function allows the pilot to modify the following parts of the flight plan:
‐ Speed limit
‐ Speed and altitude constraints
‐ Time constraints
‐ Wind
‐ Step climb or step descent
‐ Constant Mach Segment
The pilot selects these functions by pressing the right key on flight plan A or B.
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
FLIGHT PLANNING - VERTICAL FUNCTIONS
This vertical functions section only describes the following three functions: Wind and time
constraints, and Constant Mach Segment.
For other vertical revision functions: Refer to the Systems Related Procedures section.
REQUIRED TIME OF ARRIVAL (RTA)
Applicable to: ALL
Ident.: DSC-22_20-30-20-25-A-00009324.0001001 / 24 JAN 11
GENERAL
A Required Time of Arrival (RTA) is a time requirement to be met over a specified waypoint of the
lateral flight plan, including destination but excluding the origin and FROM waypoints. When the
predictions are available, the time constraint value is replaced by the predicted time at the related
waypoint, highlighted by a star (*):
‐ If the RTA is predicted as matched, the star (*) is in magenta.
‐ If the RTA is predicted as missed, the star (*) is in amber.
No specific symbol is provided on the ND.
A time constraint is cleared in the same way as any other constraints. If a time constraint is
automatically deleted. The MCDU displays an “RTA DELETED” message.
Ident.: DSC-22_20-30-20-25-A-00000489.0008001 / 14 MAY 12
ENTERING A REQUIRED TIME OF ARRIVAL
SELECT the F-PLN key on the MCDU.
SELECT a VERT REV at the revised waypoint.
SELECT the RTA prompt (2R).
CHECK, ENTER or MODIFY the identifier of the waypoint at which the time constraint is to be
defined in the [1L] field.
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A318/A319/A320/A321
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OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
WRITE the required time of arrival.
The format is +/- HHMMSS (entry of seconds is not mandatory).
ENTER it in the 1R field.
CHECK the 2R and 3R fields to determine whether the entered constraint can be met.
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FLIGHT PLANNING - VERTICAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
WIND - TEMPERATURE - QNH
Applicable to: ALL
Ident.: DSC-22_20-30-20-25-B-00000490.0001001 / 24 JAN 11
GENERAL
In order to receive the best predictions, the pilot must enter wind and temperature values for the
different phases and for the various waypoints of the cruise phase.
The system uses the temperature value at a given altitude, associated with the tropopause
entered on the INIT A page, to optimize the temperature profile.
Ident.: DSC-22_20-30-20-25-B-00009327.0001001 / 24 JAN 11
ENTERING THE TRIP WIND AND TEMPERATURE DURING F-PLN INITIALIZATION
The trip wind is a mean wind component for the entire flight from origin to destination. The pilot
can enter it on the INIT B page prior to engine start. It is usually defined by the airline's flight
operations on the computerized flight plan.
The FMGS does not consider the trip wind for alternate predictions.
The trip wind is used as long as no winds are entered in the CLB , CRZ , and DES WIND pages.
When the pilot enters a CLB , CRZ or DES WIND, the FMGS disregards the trip wind.
PRESS the INIT key.
INSERT the temperature at cruise FL.
On the INIT B page, INSERT the TRIP WIND.
The trip wind is defined as a headwind component (HDXX, XXHD or –XX), or as a tailwind (TLXX,
XXTL or +XX).
The FMGS uses the trip wind to compute preliminary performance, time and fuel predictions.
CHECK the predictions on the F-PLN B page.
Ident.: DSC-22_20-30-20-25-B-00009328.0008001 / 01 OCT 12
ENTERING THE WIND AND TEMPERATURE DURING F-PLN INITIALIZATION
When completing the INIT A page, and once the wind and cruise FL temperature forecasts are
available, the pilot may enter them, if significantly different, by pressing the wind prompt.
The pilot will access the different wind pages by using the NEXT PHASE and PREV PHASE
prompts. He will slew the CRZ WIND page to access the various cruise wind waypoints.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
The pilot will enter wind data as follows:
‐ For climb phase: By inserting either the HISTORY WIND data (as recorded during the last
descent), or by inserting winds (at up to 5 altitudes) on the CLIMB WIND page.
‐ For cruise phase: By inserting winds (at up to 4 FL ) at various CRZ waypoints on the CRZ
WIND pages. The 4 levels are the same for all the cruise waypoints. The pilot may enter the
temperature of each waypoint and at destination on this page.
‐ For descent phase: By inserting winds (at up to 5 FL /altitudes) on the DES WIND page.
‐ For the ALTN F-PLN , an average wind may be entered on the DES WIND page for alternate
cruise flight level.
Note:
Wind can be automatically received (and inserted) through the ACARS system (Refer to
DSC-22_20-70 Wind Data - Request for Wind Data).
Once a CLIMB, CRZ, or DESCENT WIND is entered, the system ignores the TRIP WIND.
Once temperature and winds are inserted, the FMGS computes the ISA profile, and the F-PLN B
page displays the forescast wind profile (by linear interpolation and propagation).
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FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
WIND ENTRY RULES
When a wind entry is performed from an empty field, direction/velocity/altitude (or flight level)
must be entered simultaneously. One entry in each bracket.
Overwriting a wind cancels the previous one.
Entered wind data can be cleared: The field reverts to brackets.
Propagated wind cannot be cleared.
Entering a new altitude, over an existing altitude, replaces that existing altitude at all cruise
waypoints. Any winds entered at the overwritten altitude are lost at all cruise waypoints.
ENTERING THE HISTORY WIND (F-PLN INITIALIZATION)
The pilot may insert the history wind, but cannot modify this page.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
If convenient, PRESS the (6R) prompt to insert. After insertion, the [6R] prompt is suppressed,
but the page still displays the wind values for information.
ENTERING THE CLIMB WIND (F-PLN INITIALIZATION)
If history winds are not convenient:
SELECT CLIMB WIND page from INIT A page or VERT REV page.
WRITE new winds into the scratchpad and ENTER.
Winds entered on the CLIMB, CRZ, and DESCENT WIND pages are always true north
referenced.
Tower wind, entered on PERF APPR page is magnetic-referenced.
The pilot can enter “GRND” in the altitude field for wind at destination.
CLIMB WIND cannot be modified when the climb phase is active.
At climb phase transition, wind data switches from blue to green, and any attempted
modification will trigger the “NOT ALLOWED” message.
The system extrapolates the highest wind entry to all higher levels.
The system interpolates winds between 2 entered levels.
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
Ident.: DSC-22_20-30-20-25-B-00009329.0001001 / 14 MAY 12
ENTERING THE CRUISE WINDS AND TEMPERATURES
At flight plan initialization, the CRZ WIND page displays all cruise waypoints with empty brackets.
In flight, only downpath waypoints are displayed.
SELECT VERT REV at WPT.
PRESS the WIND prompt.
SELECT NEXT PHASE.
SLEW until relevant waypoint is displayed.
WRITE and ENTER the new temperature into the scratchpad.
WRITE and ENTER the new wind data into the scratchpad.
WIND and temperature may be entered through the ACARS pages. (Refer to DSC-22_20-70 Wind
Data - Procedure to Insert Wind Data).
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
The crew will modify the entered winds and temperatures in flight, if a significant difference is
expected (greater than 30 kt or 30 ° for the wind data and greater than 5 °C for the temperature).
The system propagates the pilot’s (or ACARS) wind and temperature entries downpath, until a
waypoint for which a different temperature or wind has been entered (for the same flight level), or
until the last cruise waypoint.
The forecast winds at a waypoint are determined as follows:
‐ If the predicted altitude at the waypoint matches an altitude defined in the CRZ WIND page, the
forecast wind, is the corresponding entered or propagated wind, displayed at that waypoint on
the CRZ WIND page.
‐ If the predicted altitude lies between two altitudes entered on the CRZ WIND page, the wind
direction and velocity are linearly interpolated.
‐ If the predicted altitude is above or below the set of cruise altitudes, the forecast wind is a
constant value extrapolated from the entered or propagated wind at the highest (or lowest)
altitude displayed on the CRZ WIND page for that point.
Once in flight, the FMGS considers the actual measured wind up to 200 NM ahead of the
aircraft to permanently update the wind profile. This updated wind profile is used to compute the
predictions and the performance data, but is not displayed to the crew.
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FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
The CRZ WIND pages display the propagated values in small blue font, and the pilot (or ACARS)
entries in large blue font.
Note:
The CRZ WIND page displays ACARS or crew-entered or propagated data. It never
displays computed data (F-PLN B page only).
Example:
Ident.: DSC-22_20-30-20-25-B-00009330.0001001 / 24 JAN 11
EFFECT OF WIND ENTRIES ON OPTIMUM FLIGHT LEVEL
The OPT FL computation considers the wind entries made at different altitudes (normally at the
different CRZ FL).
When flying the subsequent CRZ FL , the OPT FL proposed by the PROG page may be affected
by the wind entries made at the previous CRZ FL; these winds are automatically propagated and
may be significantly different from the actual winds.
We recommend the following procedure: If the propagated winds at the lower altitudes are
significantly different from the actual winds, enter the wind at these altitudes, or if not available, the
wind measured at the current CRZ FL.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
Ident.: DSC-22_20-30-20-25-B-00009331.0016001 / 14 MAY 12
ENTERING THE DESCENT WINDS
The pilot will enter as many as one wind at 5 different FL or altitudes. This wind data will be used
for descent profile and prediction computation.
From the vertical revision page, or from the CRZ WIND page:
PRESS the WIND prompt.
SELECT the DESCENT WIND page.
ENTER up to 5 different “wind/altitude”.
A wind is written as true direction/velocity/flight level or altitude in feet.
If the crew enters “GRND” in the altitude field, the system uses the associated wind as wind at
destination.
The descent profile is corrected, as well as the tower wind entered in the PERF APPR page.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
When the winds have been entered, the F-PLN B page displays the forecasted wind profile at all
descent waypoints, using values it has interpolated from manual entries. Descent winds are not
modifiable when the descent, approach, or go-around phase is active. At descent phase transition,
wind data switches from blue to green, and any attempted modification will trigger the “NOT
ALLOWED” message.
Ident.: DSC-22_20-30-20-25-B-00009332.0001001 / 24 JAN 11
ENTERING THE ALTERNATE WIND
Alternate wind is entered on the DESCENT WIND page.
The alternate cruise (ALTN CRZ) level defaults to:
‐ FL 220 if the length of the ALTN F-PLN is less than 200 NM.
‐ FL 310 if the length of the ALTN F-PLN is greater than 200 NM.
If an alternate wind is not defined, the predictions are computed with a wind defaulted to zero.
Alternate wind can be modified at any time.
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING - VERTICAL FUNCTIONS
The alternate wind profile is as follows:
‐ ALTN CLB wind : Mean wind between ALTN CRZ wind (as entered on the DESCENT
WIND page), and the wind at primary DEST (as entered on the PERF
APPR page).
‐ ALTN CRZ wind : If no ALTN WIND has been entered on the DESCENT WIND page,
the WIND at primary DEST (as entered on the PERF APPR page) is
considered.
In case no entry is made, zero wind is assumed.
‐ ALTN DES wind : Mean wind between ALTN CRZ WIND and wind at FL 100.
Wind at FL 100 = Interpolation between wind at ALTN CRZ FL and zero
at ALTN DEST.
Ident.: DSC-22_20-30-20-25-B-00009333.0016001 / 14 MAY 12
ENTERING THE APPROACH WIND TEMPERATURE AND QNH
The wind at destination is entered in the 3L field of the PERF APPR page.
It is copied in true reference into the DESCENT WIND page at ground level (GRND ), and
F-PLN B page at destination. A ground entry on the DESCENT WIND page is, in the same way,
automatically copied to F-PLN B page and the PERF APPR page.
This wind is modifiable in descent, approach, and go-around phases.
SELECT the PERF key on the MCDU.
PRESS NEXT PHASE (6R).
WRITE QNH and temperature, and enter them.
WRITE the surface wind in the scratchpad, and enter it.
Note:
At each wind entry, the descent profile is recomputed. Therefore, it is recommended
to enter all winds, temperature, and QNH at the same time in order to minimize
recomputation time.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT PLANNING - VERTICAL FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
CONSTANT MACH SEGMENT
Applicable to: ALL
Ident.: DSC-22_20-30-20-25-C-00009334.0001001 / 14 MAY 12
GENERAL
The pilot can enter the start and end points of a constant Mach segment, and its associated Mach
number, from the VERT REV page.
Only one constant Mach segment may be defined in the active flight plan, and only one in the
secondary flight plan. No constant Mach segment can be defined in the alternate flight plan.
Ident.: DSC-22_20-30-20-25-C-00000491.0008001 / 01 OCT 12
ENTERING A CONSTANT MACH SEGMENT
SELECT the F-PLN key on the MCDU.
SELECT VERT REV at a waypoint.
(Except the destination and alternate flight plan waypoint).
WRITE the Mach/start waypoint pair.
It is possible to enter only the Mach or the waypoint. But, for the first entry, a Mach entry is
mandatory.
The waypoint must be located in front of the aircraft and must be part of the cruise.
ENTER it in the 4L field
The END WPT prompt appears in the 4R field.
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WRITE the end waypoint.
The end waypoint must be part of the cruise.
ENTER it in the 4R field.
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A318/A319/A320/A321
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OPERATING MANUAL
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A318/A319/A320/A321
PERFORMANCE - OPTIMIZATION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_20-40-10-00011077.0001001 / 17 AUG 10
Applicable to: ALL
The performance function:
‐ Optimizes a flight plan
‐ Computes predictions.
OPTIMIZATION
Ident.: DSC-22_20-40-10-00011084.0029001 / 23 JUN 15
Applicable to: ALL
The FMGC minimizes cost by optimizing the following items:
‐ Takeoff, approach, and go-around speeds (F , S , Green Dot, VAPP)
‐ Target speed for CLB , CRZ and DES phases (ECON SPD/MACH)
‐ Flight Level (for flight crew's information)
‐ Descent profile from CRZ FL down to the destination airport.
These items depend on the data the flight crew inserts during lateral and vertical flight planning and
revision procedures.
Most are displayed on the PERF pages associated with the appropriate flight phases.
WIND PROFILE
To obtain the best predictions, the flight crew must enter the wind for the various flight phases and
specifically for waypoints in cruise.
ON GROUND:
During flight planning initialization, enter the winds for the climb and cruise phases using the
HISTORY WIND and WIND pages. Enter, manually or with ACARS , different wind values in
the climb and cruise phases. The system will compute a wind for all waypoints of the F-PLN
using linear interpolation between manual/ACARS entries.
The wind profile will be displayed on the F-PLN B page, and is called forecast wind profile.
Flight crew or ACARS entries are displayed in large font, and system-computed winds in small
font.
IN FLIGHT:
The system updates the predictions and the current ECON speed, using the measured wind at
the present position. It combines actual wind and forecast winds to compute the wind ahead of
the aircraft, but this is totally transparent to the flight crew.
During cruise, the flight crew will enter the descent winds and the approach wind. The system
will update the final predictions, compute the optimum descent profile and compute the
optimum speed in descent and approach.
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OPERATING MANUAL
PERFORMANCE - OPTIMIZATION
The forecast wind profile will be used to compute fuel and time predictions, as well as ECON
speed/Mach targets.
OPTIMUM TAKEOFF, APPROACH AND GO-AROUND SPEEDS
The FMGC computes takeoff speeds (F , S, Green Dot) during the preflight and takeoff phases,
using the performance model in the database and the takeoff weight.
The flight crew has to insert V1 , VR , and V2 in the PERF TO page manually.
The FMGC uses the performance model and either the predicted landing weight or the current
gross weight at transition to the approach phase to compute approach speeds (VLS , VAPP , F ,
S, Green Dot).
On the PERF APPR page, the selected LDG CONF determines the applicable VLS and VAPP ,
the latter being updated by the WIND correction that the flight crew enters on the same page. The
FMGC uses the performance model and gross weight to compute go-around speeds (F , S, Green
Dot).
OPTIMUM TARGET SPEED FOR CLIMB, CRUISE AND DESCENT (ECON SPD/MACH)
The FMGS computes the optimum target speed (ECON SPD/MACH) as a function of:
‐ Cost index (CI)
‐ Cruise flight level (CRZ FL)
‐ Gross weight (GW)
‐ Wind and temperature models
‐ Performance factor.
The computer processes the ECON SPDs for the climb and descent phases before the initiation of
the flight phase, and freezes the values once the flight phase becomes active.
When there is no time or speed constraint/limit, ECON SPEED is the optimum speed for the
selected cost index. It refers to fuel and time cost and not directly to fuel saving.
The FM calculates ECON CLB , ECON DES and the associated top of climb and top of descent as
a function of cost index, cruise FL, and meteo data.
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OPERATING MANUAL
PERFORMANCE - OPTIMIZATION
The computer continually updates ECON CRUISE MACH (SPD), taking into account current
weather conditions and modifications to the flight plan.
Note:
If the cruise FL is below FL 250, ECON CRUISE SPEED is computed.
If the cruise FL is above FL 250, ECON CRUISE MACH is computed.
PRESET TARGET SPEED FOR CLB PHASE
The flight crew can preselect the climb speed before the CLB phase begins, by inserting a
speed in the PRESEL field:
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PERFORMANCE - OPTIMIZATION
The active mode field changes from MANAGED to SELECTED, and the FM will use the entered
speed for climb predictions computation.
The flight crew can revert to managed mode by pressing the 3L key.
PRESET TARGET SPEED/MACH FOR DES PHASE
The flight crew can change the speed and/or Mach displayed in the MANAGED field by inserting
a speed and/or Mach in the MANAGED field.
Although the entered speed is chosen by the flight crew, the FMGS uses it to compute the
descent flight path and top of descent. It is therefore part of the managed descent profile.
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PERFORMANCE - OPTIMIZATION
The flight crew can revert to the optimum speed/Mach by clearing the 3L field.
OPTIMUM FLIGHT LEVEL
The optimum flight level (OPT FL) indicates the most economic flight level for a given cost index,
weight, weather data. It is continuously updated in flight. It requires a 5 min minimum cruise time,
at a minimum cruise flight level of FL 100.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PERFORMANCE - OPTIMIZATION
The OPT FL is a compromise between fuel and time saving. As a result, the flight crew may
observe jumps in OPT FL due to GW , ISA , or wind changes. The computation of the OPT FL
considers the wind entries made at the different altitudes (normally at the different CRZ FL).
When flying the subsequent CRZ FL , the OPT FL proposed by the PROG page may be affected
by the wind entries made at the previous CRZ FL; these winds are automatically propagated and
may be significantly different from the actual winds.
Note:
For simplification purposes, the FCOM /QRH gives the OPT FL at a given Mach number.
It does not consider the cost index, therefore the FMGS and the FCOM /QRH values are
different.
FM displays OPT FL on the PROG page. The PROG page displays dashes for this quantity when
the system detects an engine-out condition.
OPTIMUM DESCENT PATH
The vertical flight path is computed to minimize fuel consumption, while satisfying the various
altitude constraints of the F-PLN and the descent speed profile, in order to reach VAPP at 1 000 ft.
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PERFORMANCE - OPTIMIZATION
The computer calculates the descent profile before the descent phase is initiated, taking into
account:
‐ All lateral and vertical flight plan data
‐ The descent and approach winds, as inserted into the DESCENT WIND page and PERF APPR
page, and the required maximum cabin rate of descent.
During descent, the descent profile is updated only if the flight plan is modified, or if data for the
APPR phase (WIND, VAPP , or LDG CONF) are changed.
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A318/A319/A320/A321
PERFORMANCE - OPTIMIZATION
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OPERATING MANUAL
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PERFORMANCE - COST INDEX
FLIGHT CREW
OPERATING MANUAL
COST INDEX (CI)
Ident.: DSC-22_20-40-20-00011041.0001001 / 17 AUG 10
Applicable to: ALL
The cost index is a fundamental input for the ECON SPEED or ECON MACH computation. ECON
SPEED and ECON MACH reduce the total flight cost in terms of flight time and fuel consumption
(and not only in terms of fuel saving).
CI is the ratio of flight time cost (CT ) to fuel cost (CF).
CI = CT /CF (kg/min or 100 lb/h).
CI = 0 corresponds to minimum fuel consumption (Max Range).
CI = 999 corresponds to minimum time.
CI = Long Range Cruise (Refer to PRO-NOR-SRP-01-50 Preparation for Descent and Approach Cost Index for Long-Range Cruise).
Note:
The airline's operations department usually defines the cost index, to optimize each
company route. The flight crew does not ordinarily modify the cost index during a flight.
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PERFORMANCE - COST INDEX
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OPERATING MANUAL
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_20-40-30-00011080.0002001 / 17 AUG 10
Applicable to: ALL
The FMGC computes predictions for the primary and secondary flight plans and displays them on
the Multipurpose Control and Display Units (MCDU s), and on the navigation display (ND ) of the
Electronic Flight Instrument System (EFIS).
The computations use the current state of the aircraft (GW , CG, position, altitude, speed, engaged
mode of the autopilot or flight director, time, wind, temperature) for the active flight plan.
The computations use data entered by the flight crew for the secondary flight plan when it is not a
copy of the active flight plan. When the secondary flight plan is a copy of the active flight plan, it uses
the same data.
PREDICTIONS FOR THE PRIMARY FLIGHT PLAN
Ident.: DSC-22_20-40-30-00011085.0001001 / 17 AUG 10
Applicable to: ALL
The predictions displayed on the MCDU assume that the FMGS will guide the aircraft along the
preplanned lateral and vertical flight plans.
The predictions displayed on the ND assume that the aircraft will continue to operate in the modes
(selected or managed) that are currently active.
As long as the aircraft is flying the flight plan under managed guidance, the predictions on the MCDU
will match those on the ND.
If the flight crew does not fly the flight plan, the MCDU predictions assume that:
‐ The flight crew will fly back towards the flight-planned route
‐ The flight crew will immediately resume flying the FMGC managed modes.
If the flight crew does not fly the managed speed profile, the MCDU predictions assume that they will
maintain the selected speed until they reach:
‐ In the climb or descent phase, the next speed limit or speed constraint if any, or next phase
‐ In cruise, the top of descent.
Then, the predictions assume that the flight crew will revert to managed speed.
COMPUTATION OF PREDICTIONS
Ident.: DSC-22_20-40-30-00011086.0001001 / 17 AUG 10
Applicable to: ALL
The system calculates various predictions for the active flight plan and updates them continually
during flight as functions of:
‐ Revisions to the lateral and vertical flight plans
‐ Cost index
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‐
‐
‐
‐
PERFORMANCE - PREDICTIONS
Current winds and temperature
Present position versus lateral and vertical flight plans
Current guidance modes
Speed control (managed/selected).
The MCDU and the ND show these predictions, each of which is based on specific assumptions.
Note:
During computation, prediction fields on the MCDU pages display dashes.
PREDICTIONS DISPLAYED ON THE NAVIGATION DISPLAY
Ident.: DSC-22_20-40-30-00011090.0002001 / 17 AUG 10
Applicable to: ALL
These predictions consist of symbols positioned along the lateral flight plan (NAV mode engaged)
or the track line (NAV mode not engaged). These symbols (named as pseudo waypoints) and their
meanings are:
Pseudo waypoint
Definition
Level symbol at the position (top of climb or level-off) where the aircraft will reach:
‐ The FCU selected altitude (blue) or
‐ The constrained altitude, if it is more restrictive than the FCU altitude and if appropriate modes
are engaged (magenta).
Top of descent or continue descent symbol:
‐ Top of descent (always white)
‐ Continue descent symbol (white if DES is not armed, blue if it is).
Start of CLIMB symbol:
‐ White if CLB is not armed
‐ Blue if CLB is armed.
•
Intercept point symbol:
The point where the aircraft is predicted to intercept the descent path, if there is any vertical
deviation when the aircraft is in DES mode (white if DES is not engaged, blue if it is).
Speed change symbol:
The point at which the aircraft will initiate an automatic ACCEL or DECEL from current speed to a
new computed speed if it encounters a SPD LIM , SPD CSTR , or HOLDING SPD (magenta).
Decelerate point symbol:
‐ Indicates the point at which the aircraft is predicted to decelerate for approach (and thus switch
to the approach phase)
‐ Magenta, if in managed speed and NAV or approach mode is engaged
‐ White, if in selected speed or HDG /TRK mode
‐ Automatic deceleration only occurs when displayed in magenta.
Continued on the following page
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Pseudo waypoint
PERFORMANCE - PREDICTIONS
Continued from the previous page
Definition
ALT CSTR symbol set around the constrained waypoint:
‐ Magenta, when the ALT CSTR is predicted to be met
‐ Amber, when the ALT CSTR is predicted to be missed
‐ White, when the ALT CSTR is not taken into account by the FMGS , and the NAV mode is
engaged.
(10 45)
(ETP)
Crosstrack error
XX.XR or XX.XL
(X is a number)
INTCPT
Time marker and equitime point symbols appear in green to indicate where the aircraft reaches
the time marker or equitime point.
Energy circle symbol (green arc) centered on the aircraft position and oriented to the current track
line. Represents the Required Distance to Land.
Only displayed if the lateral guidance mode is heading or track, and the current FMS flight phase
is in cruise, descent or approach, and the aircraft is within 180 NM of the destination.
The crosstrack error displays the lateral deviation between the aircraft position and the track of
the F-PLN active leg.
The value is limited to 99.9 NM left or right.
Intercept waypoint is displayed on the ND at the point at which the present track intercepts the
F-PLN.
The predicted time of arrival at the TO WPT is located in the upper right-hand corner of the ND . It
assumes direct distance from the aircraft position to the TO WPT and assumes current ground speed
will be constant.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-22_20-40-30 P 3/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
As a general rule, the ND indicates what the aircraft will fly, with the current active FG modes.
For example:
‐ The continuous green line on the ND represents the track the aircraft is currently flying:
• If HDG /TRK is engaged, the track line is green and the flight plan is dashed
• If NAV mode is engaged, the green line is the flight plan.
‐ If the speed target is manually selected, the speed-change symbol is no longer displayed because
it will not be taken into account.
‐ When the aircraft is not following the vertical flight plan (OP CLB , OP DES , V/S ) but the NAV
mode is engaged, the system disregards any altitude constraints and puts white circles around the
waypoints that have these constraints and positions level symbols accordingly.
‐ Pseudo waypoints are adjusted each time predictions are updated.
PREDICTIONS DISPLAYED ON THE MCDU
Ident.: DSC-22_20-40-30-00011093.0001001 / 14 MAY 12
Applicable to: ALL
The predictions displayed on the MCDU assume that AP (or FD order) is controlling the aircraft and
flying it along the preplanned lateral and vertical flight plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
DSC-22_20-40-30 P 4/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PERFORMANCE - PREDICTIONS
Therefore:
‐ If the aircraft is guided along the flight plan (managed guidance), the MCDU predictions
correspond exactly to what the aircraft is doing
‐ If the aircraft is not guided along the flight plan (selected guidance), the MCDU predictions assume
that it will return immediately to the flight plan, intercepting at a predetermined angle, and will then
proceed under managed guidance
‐ If the aircraft does not fly the managed speed profile (ECON , SPD CSTR ...), the MCDU
predictions assume that it will remain at the present selected speed/Mach until it reaches the next
SPD CSTR or SPD LIM or enters the next flight phase.
Note:
For secondary flight plan predictions, Refer to DSC-22_20-60-50 Secondary Flight Plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
DSC-22_20-40-30 P 5/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
TYPE OF PREDICTIONS
Ident.: DSC-22_20-40-30-00011113.0002001 / 18 MAR 11
Applicable to: ALL
Pseudo waypoints: T/C , T/D , S/C , S/D , I/P , SPD LIM , DECEL
TIME/SPD /ALT at each WPT and pseudo-WPT
ETA /DIST TO DEST along F-PLN /EFOB at destination
EFOB /T-WIND at each WPT and pseudo-WPT
Constraint symbol * at each constrained WPT (TIME/SPD /ALT)
Altitude error in case of missed ALT constraint
EFOB /EXTRA FUEL at each WPT
TIME/EFOB at destination
TIME/DIST to a selected altitude
Fuel prediction prior engine start
REC MAX FL
TIME/EFOB at Alternate
XTRA FUEL for various Alternates
VDEV vertical deviation from vertical flight path
MCDU PAGE
F-PLN A and B
F-PLN A
F-PLN A and B
F-PLN B
F-PLN A and B
VERT REV
VERT REV
FUEL PRED /PERF CLB /CRZ
/DES
PERF CLB or DES
INIT B
PROG
FUEL PRED
ALTN
PROG
EXAMPLES OF MCDU PREDICTIONS
Ident.: DSC-22_20-40-30-00011120.0001001 / 14 MAY 12
Applicable to: ALL
The following MCDU pages display some of the prediction types.
‐ Pseudo-waypoints:
Top of Climb (T/C ), Top-of-Descent (T/D ), Start of Climb (S/C ) or Start of Descent (S/D ) for Step
Climb/Descent, Speed Limit (SPD LIM ), deceleration to approach phase (DECEL)
‐ Time, speed, and altitude predictions:
TIME/SPD /ALT for all waypoints and pseudo-waypoints.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F to G →
DSC-22_20-40-30 P 6/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PERFORMANCE - PREDICTIONS
←G→
DSC-22_20-40-30 P 7/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
CONSTRAINT SYMBOLS (STAR)
Ident.: DSC-22_20-40-30-00011150.0001001 / 14 MAY 12
Applicable to: ALL
When a time speed or an altitude constraint is part of the vertical flight plan, it appears on the F-PLN
A page only at the time of insertion, or when predictions are not yet available.
Once available, the time speed and altitude predictions are displayed for all F-PLN waypoints: when
a speed or an altitude constraint is at a waypoint, a star symbol appears adjacent to the speed or
altitude prediction. If the star is magenta, the constraint is predicted to be matched. If the star is
amber, the constraint is predicted to be missed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← G to H →
DSC-22_20-40-30 P 8/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
Note:
If an altitude constraint is predicted as missed, the system tells you what will be the error at
the specific waypoint.
VERTICAL DEVIATION
Ident.: DSC-22_20-40-30-00011139.0001001 / 29 SEP 15
Applicable to: ALL
During descent, the system indicates to the flight crew the vertical deviation from the computed
descent profile (PFD and MCDU) and predicts where the flight crew can rejoin it.
VDEV on the PFD and PROG page, predictions on the MCDU F-PLN page, symbols on the ND,
enable assessment to the vertical position versus the computed flight profile.
OPERATION RULES CONCERNING PREDICTIONS
Ident.: DSC-22_20-40-30-00011140.0001001 / 17 AUG 10
Applicable to: ALL
The flight crew must properly update the flight plan data during the flight, in order to obtain accurate
and meaningful predictions.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← H to J →
DSC-22_20-40-30 P 9/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
The flight crew should rely on the ND for short-term predictions. It indicates what the aircraft will do
under the currently engaged modes (selected or managed).
The flight crew should rely on the MCDU for long-term predictions, when managed guidance is active
or about to be reengaged.
OTHER COMPUTATIONS
Applicable to: ALL
Ident.: DSC-22_20-40-30-A-00011141.0002001 / 17 AUG 10
ENGINE-OUT CASE
The FMGS computes an engine-out target speed for each flight phase. It computes an engine-out
maximum altitude at long-range cruise speed, and displays it on the PROG page.
The new speed target becomes Green Dot in climb, and EO CRZ SPD in cruise.
The system computes the flight plan predictions down to the primary destination. If the aircraft
is above EO MAX ALT , the predictions are computed, assuming that a drift down descent will
immediately be performed to reach EO MAX ALT.
Ident.: DSC-22_20-40-30-A-00011142.0001001 / 17 AUG 10
RECOMMENDED MAXIMUM ALTITUDE (REC MAX)
The recommended maximum altitude is the lowest of the maximum altitude that:
‐ The aircraft can reach with a 0.3 g buffet margin
‐ The aircraft can fly in level flight at MAX CRZ rating
‐ The aircraft can maintain a V/S of 300 ft/min at MAX CLB thrust
‐ The aircraft can fly at a speed higher than Green Dot and lower than VMO /MMO
‐ The aircraft is certified at.
The REC MAX altitude is displayed on the PROG page.
Anti-ice is not taken into account for this computation. Refer to QRH graphs if icing conditions are
expected.
A maximum altitude using a 0.2 g buffet margin is also computed. It is not displayed, but the
system uses it to limit CRZ ALT entry.
Ident.: DSC-22_20-40-30-A-00011250.0001001 / 17 AUG 10
PREDICTIONS FOR ALTERNATES
Predictions for alternates are displayed on the ALTERNATES page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← J to K →
DSC-22_20-40-30 P 10/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
They are based on:
‐ A default cruise FL equal to 220, if the airway distance is less than 200 NM. Otherwise, it is
FL 310
‐ Simplified wind/temperature models, based on flight crew entries:
• ALT CRZ wind, as entered on the FUEL PRED page
• CRZ temperature interpolated from the temperature model for the primary flight plan.
‐ Airway distance, or direct distance, as provided by the database (manual entry, if not in the
database)
‐ Cost index = 0 (minimum fuel)
‐ Initial aircraft weight equal to landing weight at primary destination.
Note:
1. No step can be inserted in an alternate flight plan
2. No predictions are displayed for the selected alternate on flight plan pages. However,
the flight crew can read ALTN trip fuel and time on the INIT B page before engine start,
and estimated time and estimated fuel on board at alternate on the FUEL PRED page
after engine start.
RETURN-TO-TRAJECTORY ASSUMPTIONS
Ident.: DSC-22_20-40-30-00011148.0001001 / 19 DEC 12
Applicable to: ALL
If the aircraft is not on the lateral flight plan, predictions assume an immediate return to the active
lateral leg with a 45 ° convergence angle, or that it will fly directly to the “TO” waypoint, when the
required convergence angle is greater than 45 °.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← K to L →
DSC-22_20-40-30 P 11/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
ENERGY CIRCLE
Ident.: DSC-22_20-40-30-00011144.0001001 / 17 AUG 10
Applicable to: ALL
The energy circle is a green arc, centered on the aircraft’s position and oriented towards the current
track line. It is displayed on the ND s during descent, when HDG or TRK mode is selected. It
represents the required distance to land from the aircraft’s position down to airport elevation at VAPP
speed, considering all speed constraints on the vertical profile.
INTRODUCTION TO PERF AND IDLE FACTORS
Ident.: DSC-22_20-40-30-00014856.0001001 / 31 JAN 13
Applicable to: ALL
The FMGS contains a performance database to compute the predictions and the performance
data. This performance database has a model of several aircraft configurations (aircraft type/engine
model) to tune the performance and the FMGS predictions. For some aircraft configurations, the
model can differ from the real aircraft performance. In these cases, the FMGS has to correct the
computation of the performance and the predictions. This is the aim of PERF and IDLE factors.
With time, the real aircraft drag and engine performance can deviate from the nominal model.
The airline Flight Operations should periodically revise the value of these factors to adapt FMGS
predictions to actual aircraft performance.
Note:
The IDLE factor is not available on aircraft with FMS1 Honeywell Legacy.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← L to N
DSC-22_20-40-30 P 12/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
PERF FACTOR
Applicable to: ALL
Ident.: DSC-22_20-40-30-B-00011145.0001001 / 30 JAN 13
GENERAL
The FMGS uses the PERF factor to correct the predicted fuel flow that is used for the computation
of the fuel predictions.
The PERF factor modifies the predicted fuel flow, according to the following formula:
FF pred is the FF used for prediction.
FF model is the FF from the aero-engine model.
This correction is applied throughout the entire flight, and modifies the performance predictions
and the ECON speed or Mach.
For example: Entering a PERF factor of +1.5 means that Flight Operations have evaluated the
aircraft fuel deviation as 1.5 %, compared to the basic performance model (0.0).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
O→
DSC-22_20-40-30 P 13/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_20-40-30-B-00011147.0002001 / 06 SEP 16
PERF FACTOR VALUES
The PERF factors to be used on FMS2, depending on engine type, are:
‐ For CFM 56-5B engines only:
Depending on the engine type: CFM 56–5B SAC (Single Annular Chamber) or DAC (Double
Annular Chambers), or non/P (without the new LP and HP blade compressor), a positive
performance factor has to be entered on the MCDU STATUS page to increase the FMGS’
predicted fuel consumption and match the actual fuel burnt.
SAC
NON/P
DAC
2
2
A321-111
CFM56-5B1
2
2
A321-112
CFM56-5B2
2
2
A321-211
CFM56-5B3
2
2
A321-212
CFM56-5B1
2
2
A321-213
CFM56-5B2
A321-214
CFM56-5B4
3
3
A320-214
CFM56-5B4
A320-215
CFM56-5B5
A320-216
CFM56-5B6
4.5
4.5
A319-111
CFM56-5B5
4.5
4.5
A319-112
CFM56-5B6
4.5
4.5
A319-115
CFM56-5B7
A318-111
CFM56-5B8
A318-112
CFM56-5B9
‐ For other engines:
• A318 “PW": 0.0 %
• A319/A320 “CFM” Family fitted with CFM 56-5A engines: 0.0 %
• A319/A320/A321 “IAE” Family: 0.0 %
• A320 “PW” Family: 0.0 %
• A320 “CFM LEAP” Family: 0.0 %
SAC
0
/P or /3
DAC
0
1
1
0
1
0
1
0
1
1
-
0
1
0
-
0
-
0
1
0
1
0
1
0
-
0
-
All these numbers assume that:
‐ The aircraft is brand-new
‐ Anti-ice is OFF
‐ The air conditioning is on NORMAL for “IAE” engines and on LOW for “CFM” engines
‐ The conservative Fuel Lower Heating Value (FLHV) is 18400 btu/lb.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←O→
DSC-22_20-40-30 P 14/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PERFORMANCE - PREDICTIONS
FLIGHT CREW
OPERATING MANUAL
When an aircraft ages, fuel consumption degradation will be measured to determine the so-called
“monitored fuel factor”. This factor corresponds to the deviation of the aircraft’s actual fuel
consumption from the nominal model. Generally, the FLHV that is used during fuel factor
monitoring is higher than the FMS value.
In order not to penalize FMS predictions, it is necessary to correct the “monitored fuel factor”.
For example, add -1 % to the “monitored fuel factor”, when an FLHV of 18590 btu/lb is used.
Once this factor is established by the airline, it should be arithmetically added to the above-noted
performance factor.
Note:
1. At delivery, ENTER the PERF factor (given in the table above) directly in the MCDU
(no correction factor is needed).
2. When replacing an FMS 1 Legacy by an FMS 2, on any given aircraft model, the
performance model that is stored in the FMS 2 may be different from the one that was
previously stored in the FMS1 Legacy.
As a result, DISREGARD the PERF factor previously entered in the MCDU.
ADD the “monitored fuel factor” (when available) to the PERF factor (given above),
and ENTER the resulting factor in the MCDU.
IDLE FACTOR
Applicable to: ALL
Ident.: DSC-22_20-40-30-D-00014861.0001001 / 29 SEP 15
GENERAL
The FMGS uses the IDLE factor to adjust the computation of the vertical profile during the descent
phase (IDLE segment).
The FMGS computes the vertical profile and the predictions from the Top of Descent (T/D) to the
first altitude constraint with the following assumptions:
‐ The aircraft has a given thrust
‐ The aircraft has a given speed (within the speed target range).
The IDLE Factor adjusts the value of the given thrust by an addition of a delta (DELTA) thrust to
IDLE thrust. With this additional thrust, the IDLE Factor gives flexibility to maintain the aircraft on
the computed vertical profile in case of external perturbations such as windy conditions (previously
entered by the flight crew in WIND pages).
Depending on the IDLE factor value, the FMGS modifies the position of the T/D and computes a
vertical profile in function of the given thrust (IDLE + DELTA).
Therefore, the IDLE factor has a direct impact on:
‐ The computation of vertical profile
‐ The capability of the aircraft to maintain the vertical profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← O to P →
DSC-22_20-40-30 P 15/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PERFORMANCE - PREDICTIONS
Ident.: DSC-22_20-40-30-D-00014862.0001001 / 23 JUN 15
IMPACT ON VERTICAL PROFILE
‐ If the IDLE factor is positive, the vertical profile is less steep than with IDLE factor 0. The
descent phase starts earlier.
‐ If the IDLE factor is negative, the descent path is steeper than with IDLE factor 0. The descent
phase start later.
The following graph provides an example (average values) of the IDLE factor's effect on descent
length:
Example: An IDLE factor of -3 decreases the computed descent length by 5 NM.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←P→
DSC-22_20-40-30 P 16/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PERFORMANCE - PREDICTIONS
Ident.: DSC-22_20-40-30-D-00014863.0001001 / 30 JAN 13
IMPACT ON GUIDANCE
In DES mode, the FMGS maintains the aircraft on the vertical profile and keeps the IAS within the
speed target range.
If the aircraft deviates above the profile, the IAS will increase to return to the vertical profile.
When the aircraft returns to the descent profile, the IAS will decrease to the target speed.
Ident.: DSC-22_20-40-30-D-00014864.0001001 / 30 JAN 13
IDLE FACTOR AT DELIVERY
The IDLE factor to be used at delivery is 0 %.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←P
DSC-22_20-40-30 P 17/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PERFORMANCE - PREDICTIONS
PROCEDURE TO MODIFY THE PERF AND IDLE FACTORS
Ident.: DSC-22_20-40-30-00014857.0001001 / 30 JAN 13
Applicable to: ALL
PROCEDURE TO MODIFY THE PERF AND IDLE FACTORS (ON GROUND ONLY)
‐ PRESS the MCDU DATA key and then the A/C STATUS prompt in order to access the A/C
STATUS page
‐ For aircraft with FMS2 Honeywell or Thales:
• ENTER the change code in the CHG CODE field.
The default value for this code is “ARM” but it is possible to modify it on airline request.
The applicable code is then coded in the Airline Modifiable Information (AMI).
When a valid change code is entered, the IDLE and PERF factors are displayed in blue.
• ENTER the new IDLE and PERF factors in the MCDU scratchpad separated by a "/".
For example: "-2/+1"
• PRESS the corresponding key to insert the new IDLE and PERF factors.
The new IDLE and PERF factors are displayed in large blue font.
Note:
Only authorized personnel should take the responsibility to update the IDLE and PERF
factor values.
‐ For aircraft with FMS1 Honeywell Legacy:
• ENTER the new PERF factor in the MCDU scratchpad.
• PRESS the corresponding key to insert the new PERF factor.
The new PERF factor is displayed in large blue font.
Note:
1. Only authorized personnel should take the responsibility to update the PERF factor
value.
2. The IDLE Factor is not available on aircraft with FMS1 Honeywell Legacy.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Q
DSC-22_20-40-30 P 18/18
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
FMS2 Honeywell
GENERAL
Ident.: DSC-22_20-50-10-25-00000556.0001001 / 01 OCT 12
Applicable to: ALL
The Flight Management and Guidance System (FMGS) displays information on various “pages”.
When a page cannot display all of the assigned information, it cues the pilot to call up additional
information. There are three types of pages, and each type has its particular way of cuing the pilot to
call up additional information.
FIRST TYPE
When this page cannot simultaneously display all the information on the screen (more information
than the six pairs of lines can hold), the pilot can scroll the page up or down.
In this case, the screen displays a ↑↓ symbol in the bottom righthand corner (F-PLN pages,
secondary F-PLN page, departure/arrival pages,...).
SECOND TYPE
When the information is on successive pages, the pilot presses the “NEXT PAGE” key to
sequentially call up these pages.
In this case, an arrow is displayed in the top righthand corner of the screen (INIT pages).
THIRD TYPE
When different types of information are on successive pages, the pilot calls up these pages by
pressing the key adjacent to the prompts >, < or *.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-22_20-50-10-25 P 1/144
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
MCDU MENU PAGE
Ident.: DSC-22_20-50-10-25-00000557.0010001 / 14 MAY 12
Applicable to: ALL
This page lists the various systems which the pilot can access via the MCDU.
The flight crew selects a system by pressing the key adjacent to the name of that system.
The name of the selected system is displayed in green, all others in white.
If the MCDU cannot establish communication with the selected system, it displays “OUT”.
When a system calls for the flight crew attention, the MCDU displays “REQ” next to the system’s
name, and the “MCDU MENU” annunciator lights up.
When the flight crew presses the key next to the name of the system requiring attention, the “MCDU
MENU” annunciator light goes out.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-22_20-50-10-25 P 2/144
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
SELECT
Pressing the [1R] key selects the NAV B/UP function and DESELECT
NAV B/UP NAV B/UP appears in the [1R] field.
If the NAV B/UP is inoperative, the field is blank.
RETURN This field is displayed when a function is active
When the MCDU communicated with a system other than the FMGC , the flight crew should use the
MCDU MENU page to revert to the FMGC system.
INIT A PAGE
Ident.: DSC-22_20-50-10-25-00000558.0009001 / 14 MAY 12
Applicable to: ALL
The flight crew uses the INIT A page to initialize the flight plan and align the inertial reference
system.
‐ The flight crew accesses to this page by pressing the INIT key on the MCDU . The INIT A page
can be accessed on ground or in flight.
‐ The flight crew may also call up this page by:
• Pressing the “NEXT PAGE” key on the MCDU console, while on the INIT B page, or
• Pressing the key next to “RETURN” or “INSERT” on the route selection page, or
• Pressing the key next to “INSERT” on the wind page.
‐ When in the done phase, the pilot may press the INIT key to switch to the next preflight phase.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_20-50-10-25 P 3/144
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[ 1L ] CO RTE
[ 2L ] ALTN/CO RTE
(blue)
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
If the flight crew enters a company route number, the screen displays all
data associated with that route (8 or 10 characters, depending on the pin
program).
Inserting the CO RTE into the RTE selection page also enters the CO RTE
number in this field.
This field is dashed, until a primary destination is entered in the 1R field.
If a preferred alternate is associated with the primary destination, it is
displayed in this field with the company route identification. The crew may
manually enter an alternate and company route.
If preferred alternate is not associated with the primary destination, NONE
is displayed in this field.
When the alternate route and the primary destination do not match, the
MCDU scratchpad displays “DEST /ALTN MISMATCH”.
If the primary destination is changed, this field is modified accordingly.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
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05 SEP 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 3L ] FLIGHT NUMBER The flight number automatically appears in this field, if it is stored with the
company route. The flight crew may modify it, or enter a new number here.
[ 5L ] COST INDEX
This is usually stored in the database along with the company route.
The flight crew may modify it, or enter a new value here. It defaults to the
last entered value, if a value is not stored in the database.
The cruise flight level is usually stored in the database along with the
[ 6L ] CRZ FL/TEMP
company route. If not, it has to be entered manually.
(cruise flight level and
If no cruise flight level is entered, the system will not furnish predictions,
temperature)
while the aircraft is on the ground.
The flight crew has to enter the temperature at cruise flight level in order to
refine the predictions. Otherwise, these are computed for ISA conditions.
(If no sign is entered, the system uses a plus).
[ 1R ] FROM/TO
This field allows the pilot to enter a city pair (ICAO codes for city of origin
and destination).
This entry automatically deletes any previously entered company route
and calls up the route selection page. If one airfield of the pair is not in the
database, the display changes to the NEW RWY page.
[ 2R ] INIT REQUEST
This prompt is displayed if the pilot did not enter an active flight plan
or entered a flight number or a company route that is not in the aircraft
database. Selecting this prompt sends the ground a request for active
flight plan initialization (downlink message). When the star is not
displayed, a downlink message cannot be sent.
The uplink flight plan is automatically inserted in the active flight plan, prior
to engine start, provided an active flight plan does not exist.
After engine start, the uplink flight plan is sent to the secondary flight plan
and manually inserted or rejected. (Refer to DSC-22_20-70 Flight Plan
Initialization Through ACARS).
[ 3R ] IRS INIT
The flight crew presses this key to access the IRS INIT page.
[ 5R ] WIND
The pilot presses this key in order to gain access to the climb wind page,
unless a temporary flight plan exists. In this case, the scratchpad displays
TEMPORARY F-PLN EXISTS.
[ 6R ] TROPO
The default tropopause altitude is 36 090 ft. The pilot can use this field to
modify it (60 000 ft maximum).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
ROUTE SELECTION PAGE
Ident.: DSC-22_20-50-10-25-00000559.0001001 / 17 MAR 11
Applicable to: ALL
This page displays all the company routes, stored in the database, that are associated with the
inserted city pair. They can be called up manually, or displayed automatically.
‐ Manually : The pilot presses the FROM/TO or ALTN key on the INIT A page when a city pair is
displayed.
‐ Automatically : The system displays it, when the pilot enters a city pair, or defines an alternate on
the INIT A page of the active or secondary flight plan.
TITLE
[ 1L ]
Line 2 to Line 5
[ 6L ] RETURN
[ 6R ] INSERT
Note:
Idents for the city pair inserted on the INIT A page.
(The numbers in the upper righthand corner are the total number of
company routes from this city pair stored in the database).
This field shows the name of the company route. NONE appears, if there is
no company route for this city pair.
These fields display the various elements of the company route:
Waypoints in large green font, and airways in small white font.
The pilot presses this key to return to the INIT A page.
The pilot presses this key to insert the displayed company route in the flight
plan, and return to the INIT A page.
The pilot can slew the display to show the rest of the route, if one page does not show it all,
or to display other company routes for this city pair.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
IRS INIT PAGE
Ident.: DSC-22_20-50-10-25-00013511.0051001 / 14 MAY 12
Applicable to: ALL
The flight crew uses the IRS INIT page to align the inertial reference system. The crew accesses this
page, by pressing the IRS INIT key on the INIT A page.
Line 1
LAT-REFERENCE-LONG
Line 2 LAT-GPS
POSITION-LONG
Line 3 to 5
[ 6L] RETURN
This line provides the latitude and longitude of the FM reference
position. This reference is extracted from the navigation database.
The flight crew can modify this reference. Only when the FM reference
position matches the origin airport position, the airport identifier is
displayed in green. Otherwise, there are dashes at the place of the
airport identifier. Latitude and longitude of the FM reference position are
displayed in blue. The flight crew can modify the latitude and longitude
values using the scroll keys.
This line displays the GPS position latitude and longitude.
These lines display the IRS 1-2-3 alignment state, source and
latitude/longitude.
The alignment status can be ALIGNING ON XXX, or ALIGNED ON
XXX or IN ATT . XXX is the alignment source and can be GPS or CDU
or REF. It is displayed in white font.
The latitude and longitude values are displayed in green.
This prompt enables the flight crew to return to the INIT A page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
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05 SEP 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[ 6R]
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
If a reference is available, field displays ALIGN ON REF → in blue
which is replaced by CONFIRM ALIGN* in amber when 6R prompt is
pressed. Pressing again the 6R prompt enables the transmission of the
FM reference position displayed in line 1.
WIND PAGES
Ident.: DSC-22_20-50-10-25-00000560.0009001 / 17 MAR 11
Applicable to: ALL
Winds in climb, cruise, descent and approach are necessary to provide the pilot with reliable
predictions and performance. Wind pages enable the pilot to enter and/or review the winds
propagated by the FMGS or sent by ACARS for the various flight phases.
Note:
On WIND pages, wind direction is always true-referenced.
CLIMB WIND PAGE
This page enables the pilot to enter and/or review predicted wind vectors (direction and velocity) at
up to 5 different levels.
THE CLIMB WIND PAGE IS ACCESSED FROM:
TITLE
CLIMB WIND in large white font.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[ 1L ] to [ 5L ] TRU
WIND/ALT
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This field displays the winds, entered at various climb altitudes : In
blue before climb phase activation, and in green after climb phase
activation.
This field may also display history winds or uplink winds. Large
blue brackets are displayed before any wind entry. Pilot-entered
and uplinked winds are displayed in large font. History wind data is
displayed in small font.
Upon sequencing the top of climb, the climb winds are deleted.
Note:
Climb winds are not deleted, when the origin airport is
changed.
[ 1R ] HISTORY WIND Displayed in preflight phase only. This key calls up the history wind
page. This page is not modifiable (small green font), but can be
inserted into the CLIMB WIND page by using the 6R key and modified
accordingly.
[ 2R ] WIND REQUEST Pressing this key sends a request for ACARS winds. (Refer to
DSC-22_20-70 Wind Data - Request for Wind Data).
[ 5R ] NEXT PHASE
Pressing this key calls up the CRUISE WIND page, or the DESCENT
WIND page, if no cruise waypoint exists.
HISTORY WIND PAGE
[ 6L ] CLIMB WIND
[ 6R ] INSERT
This key reverts the display to the CLIMB WIND page.
This key inserts the history wind values into the CLIMB WIND page.
CRZ WIND PAGE
This page displays the wind direction and velocity for each cruise waypoint.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The cruise wind page enables the definition of a temperature at a given altitude, and is accessed
as follows:
TITLE
[ 1L ] to [ 4L ] TRU
WIND/ALT
CRZ WIND AT in large white font.
These fields display the entered wind at various altitudes in blue.
The entered winds are propagated at the same altitude to the downpath
cruise waypoints, if no other winds are entered.
The propagated wind direction and velocity are displayed in small fonts.
Both uplinked winds and pilot-entered winds are displayed in large blue
font. Wind data is modifiable during cruise.
[ 5L ] SAT/ALT
This field allows the pilot to enter a temperature at a given flight level, or
to display a propagated value.
The crew must enter both temperature and altitude at the first entry.
They can then independently modify the temperature, or the altitude.
[ 2R ] WIND REQUEST Pressing this key sends a request for ACARS winds. (Refer to
DSC-22_20-70 Wind Data - Request for Wind Data)
[ 4R ] PREV PHASE
This prompt is displayed in Preflight, Takeoff, Climb and Done phases.
Pressing this prompt calls up the CLIMB WIND page.
[ 5R ] NEXT PHASE
Pressing this prompt calls up the DES WIND page.
Any new entry performed on the CRZ WIND page is immediately inserted into the corresponding
flight plan. Predictions are dashed on the F-PLN pages during the recomputation time. CRZ WIND
page automatically reverts to F-PLN page, if a temporary flight plan is created or the secondary
flight plan is activated.
DESCENT WIND PAGE
This page enables the pilot to define and display the winds used for computing the descent profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The pilot calls it up by selecting NEXT PHASE on the CRUISE WIND page, or the WIND prompt
on the VERT REV page.
[ 1L ] to [ 5L ]
This displays inserted winds or uplinked winds, in large blue fonts, prior
to activating the descent phase (modifiable values), and in green after
descent phase activation (not modifiable values).
An entry of “GRND ” in the “ALT ” field is seen as the wind at ground
level. This wind is copied on the PERF APPR page (and corrected for
the magnetic variation).
A clear action on one key reverts the line to blue brackets.
[ 6L ] ALTERNATE
This field is only displayed when an alternate is defined.
The pilot-entered value or uplinked value is displayed in large blue font.
It is always modifiable by the pilot.
[ 2R ] WIND REQUEST* Pressing this key sends a request for ACARS winds. (Refer to
DSC-22_20-70 Wind Data - Request for Wind Data).
[ 4R ] PREV PHASE
Pressing this key calls up the CRUISE WIND page. The field is erased
after the top of descent has sequenced.
Note:
Descent winds and alternate wind are deleted, if the destination airport is changed.
INIT B PAGE
Ident.: DSC-22_20-50-10-25-00000561.0009001 / 14 MAY 12
Applicable to: ALL
The pilot uses this page to initialize the gross weight and center of gravity, before starting the
engines.
The pilot can call it up from the INIT A page during preflight phase prior to engine start, by pressing
the NEXT PAGE key on the MCDU console, as long as engines have not been started.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G →
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05 SEP 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This page automatically reverts to the FUEL PRED page after the first engine is started.
The FMGC will stop using the pilot-entered block fuel and will compute its predictions based on the
FOB indicated by the FQI computer (or the FAC as a back up) from that moment on.
[ 1L ] TAXI
This is the taxi fuel, which defaults to a preset value, (usually 200 kg or
400 lb in the AMI file). The crew can change the value through this field.
[ 2L ] TRIP/TIME (green) This field displays trip fuel and time when predictions become available.
The pilot cannot modify this data.
[ 3L ] RTE RSV/% (blue) This field displays the contingency fuel for the route and the corresponding
percentage of trip fuel. It may be equal to 0.0, if such is the policy of the
operator. The flight crew can either enter a fuel quantity, or a percentage.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
[ 4L ] ALTN/TIME
(blue/green)
Displays alternate trip fuel and time, assuming that the Cost Index =
0 and that the aircraft flies at the default cruise flight level. (Refer to
DSC-22_20-30-10-15 Alternate Function - Review and Selection of
Alternate Airport). The flight crew can modify the alternate fuel as required.
In this case, alternate time will be dashed.
[ 5L ] FINAL/TIME (blue) Displays the final reserve fuel and time calculated at the alternate airport
(or destination airport, if selected in the “airline fuel policy” section of the
AMI ). Before any crew entry, the FINAL field is dashed and FINAL TIME
field is defaulted to the value specified in the AMI file (typically 30 min).
The flight crew may enter a final fuel or time, and the system will compute
associated holding time/fuel available.
The system assumes a holding pattern at 1 500 ft AGL , with the aircraft
in CONF 1 at maximum endurance speed (racetrack pattern, altitude and
selected airport can be modified through the “airline fuel policy” section of
the AMI).
[ 6L ] MIN DEST FOB
Displays the expected minimum fuel at destination. It is equal by default
(blue)
to the ALTN + FINAL fuel. This field can be modified directly by the flight
crew, and is also impacted by the modification of ALTN and/or FINAL fuel.
Note:
If pilot entry of MIN DEST FOB is lower than ALTN + FINAL
fuel, the message “CHECK MIN DEST FOB” is triggered on the
MCDU.
[ 1R ] ZFW/ZFWCG (blue)Displays the Zero Fuel Weight (ZFW ) and Zero Fuel Weight CG (ZFWCG
). The flight crew must enter the ZFW /ZFWCG values (as appropriate) to
obtain a speed profile and predictions.
Note:
[ 2R ] BLOCK
If the flight crew enters a ZFW value that exceeds the acceptable
range (as defined in the OPC or in the performance database),
the “ENTRY OUT OF RANGE” message appears and the value
is rejected.
The block fuel in this field is a mandatory entry.
When the flight crew enters a block fuel, the page title changes to INIT
FUEL PREDICTION.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 3R ] FUEL PLANNING Initiates an FMGC block fuel computation using current hypothesis and
extra = 0. When the pilot selects this function, FUEL PLANNING becomes
(amber)
green, and the BLOCK field is dashed during FMGC computation. The title
of the page changes to INIT FUEL PLANNING, and BLOCK CONFIRM*
replaces the FUEL PLANNING prompt, when the block fuel is computed
by the FMGC. If the pilot modifies the parameters used to compute
prediction before confirmation, the computation automatically restarts and
FUEL PLANNING is displayed in green.
[ 4R ] TOW/LW (green) Displays the computed Takeoff Weight (TOW ) and Landing Weight (LW)
at the primary destination. This cannot be modified.
[ 5R ] TRIP WIND (blue) This field allows the entry of a mean wind component for the trip from the
origin to the destination. Upon entry of a CO RTE or FROM/TO pair, this
field defaults to HD 000 in small font.
An entry preceeded by –, H, HD is considered to be headwind, +, T, TL to
be tailwind. The entered speed is displayed in large blue font.
When the flight crew inserts a wind on the CLIMB, CRUISE or DESCENT
WIND page, or on the PERF APP page, the system no longer considers
the trip wind, and the corresponding field is dashed.
[ 6R ] EXTRA/TIME
Displays the amount of extra fuel, and the resulting time available for
(green)
holding over the primary destination.
EXTRA FUEL = BLOCK – (TAXI + TRIP + RSV + MIN DEST FOB).
The field displays its information in small font, and it cannot be modified by
the flight crew.
FUEL PREDICTION PAGE
Ident.: DSC-22_20-50-10-25-00000562.0009001 / 14 MAY 12
Applicable to: ALL
The pilot presses the FUEL PRED key on the MCDU console to display fuel prediction information at
destination and alternate, as well as fuel management data after the engines are started.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← G to H →
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05 SEP 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[ 1L ] - [ 1R ]
AT-UTC/TIME-EFOB
(green)
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Display time and fuel predictions to the primary destination.
TIME is displayed before takeoff. UTC predictions are displayed after
takeoff. If the flight crew has entered an Estimated Takeoff Time (ETT), the
UTC is displayed.
The EFOB at destination will turn to amber, if it becomes less than the MIN
DEST FOB value.
These lines display time and fuel predictions to the alternate airport. (Refer
to DSC-22_20-30-10-15 Alternate Function - General).
[ 2L ] - [ 2R ]
AT-UTC/TIME-EFOB
(green)
[ 3L ] RTE RSV% (blue) Before departure, this field displays the route reserve fuel and the
corresponding percentage of trip fuel. It may be equal to 0.0, if such is
the policy of the operator. The crew can either enter a fuel quantity or a
percentage. After takeoff, it becomes green 0.0/0.0, and the corresponding
fuel is added to the EXTRA fuel.
[ 4L ] ALTN/TIME
Displays alternate trip fuel and time, assuming that the Cost Index = 0 and
(blue/green)
that the aircraft flies at the default cruise flight level.
(Refer to DSC-22_20-30-10-15 Alternate Function - Review and Selection of
Alternate Airport).
The flight crew can modify the alternate fuel as required.
In this case, alternate time will be dashed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H→
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05 SEP 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 5L ] FINAL/TIME
(blue)
Displays the final reserve fuel and time calculated at the alternate airport (or
destination airport, if selected in the “airline fuel policy” section of the AMI).
The flight crew may enter a final fuel or time, and the system will compute
associated holding time/fuel available.
The system assumes a holding pattern at 1 500 ft AGL , with the aircraft
in CONF 1 at maximum endurance speed (racetrack pattern, altitude and
selected airport can be modified through the “airline fuel policy” section of
the AMI).
[ 6L ] MIN DEST FOB Displays the expected Minimum Fuel at Destination. It is equal to the FINAL
(blue)
+ ALTN fuel. The field can be modified directly by the flight crew, and is also
impacted by the modification of the ALTN and/or the FINAL fuel.
[ 3R ] ZFW/ZFWCG
Displays the Zero Fuel Weight (ZFW ) and Zero Fuel Weight Center of
(blue)
Gravity (ZFWCG ) values, as entered before engine start on the INIT B
page. The flight crew can re-enter or modify these values after engine start
on the FUEL PRED page. If at engine start, no ZFW or ZFWCG values have
been entered, amber boxes are displayed in the corresponding field. The
flight crew must enter the ZFW /ZFWCG values to obtain a speed profile and
predictions.
[ 4R ] FOB (blue)
Displays the Fuel On Board (FOB ) calculated by the FMGS and the
following fuel sensors:
‐ Fuel flow and fuel quantity sensors (/FF+FQ)
‐ Fuel flow sensors only (/FF).
‐ Fuel quantity sensors only (/FQ).
The flight crew can modify the FOB value in flight, or modify the sensors
used by entering “/FF ”, “/FQ” or “/FF+FQ”, as required.
[ 5R ] GW/CG (green) The FMS continuously updates the GrossWeight (GW ) and Center of
Gravity (CG ) during the flight. The field displays dashes, as long as the
system is not calculating the Fuel On Board, or the ZFW has not been
entered by the flight crew.
The field cannot be modified.
[ 6R ] EXTRA/TIME
Displays the amount of extra fuel, and the resulting time available for holding
(green)
over the primary destination.
EXTRA FUEL = FOB – (TAXI + TRIP + RSV + MIN DEST FOB).
This field displays its information in small green font, and it cannot be
modified by the flight crew.
Note:
All fields are dashed before engines are started.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
FLIGHT PLAN PAGES
Ident.: DSC-22_20-50-10-25-00000563.0009001 / 23 JUN 15
Applicable to: ALL
These pages display all waypoints of the active and alternate flight plans, along with associated
predictions.
The pilot can make all revisions to the lateral and vertical flight plans from these pages:
He presses the left key to revise the lateral flight plan, and the right key to revise the vertical flight
plan.
He presses the F-PLN key on the MCDU console to access the page A of the active flight plan.
FLIGHT PLAN A PAGE
Page A displays time, speed, and altitude predictions for each waypoint of the active flight plan.
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FLIGHT CREW
OPERATING MANUAL
TITLE
Line 1 to Line 5 WPT,
UTC, SPD, ALT
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
FLIGHT NUMBER (blank, if no flight number has been entered).
This line may display: TMPY in yellow if a temporary flight plan exists;
OFST in white, if a lateral offset is flown; or, OFST in yellow, if a lateral
offset revision is pending.
These lines display consecutive waypoints along with associated
predictions of time, speed or Mach and altitude for each.
TIME is displayed before takeoff, and UTC after takeoff. After the pilot
enters an estimated takeoff time (ETT), UTC is displayed.
The time and flight level display at the FROM waypoint (first line of
the flight plan) are values that the system memorized at waypoint
sequencing.
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A318/A319/A320/A321
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OPERATING MANUAL
[ 1R ] SPD/ALT
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The field dedicated to SPEED or MACH is blank at the FROM waypoint,
except at the departure airport. (V1 associated with runway elevation, is
displayed).
Note:
When the HOLD marker is slewed, the HOLD SPD Label will
overwrite the TIME/UTC title.
Line 6, DEST UTC/TIME DIST is the distance to destination along the displayed flight plan.
DIST, EFOB
EFOB is the estimated fuel on board at destination. The EFOB at
destination will turn to amber, if it becomes less than the MIN DEST FOB
value.
The sixth line is permanent and is displayed in white font once
predictions are available, except when a TMPY F-PLN is displayed or
in some cases when an ALT CSTR is entered (“*CLB or DES*” prompt
appears).
Note:
The predicted altitude at a waypoint is related to the QNH below the transition altitude,
and is given as a flight level above the transition altitude.
The generic flight plan page displays the FROM waypoint (last waypoint to be overflown) on the
first line, and the TO waypoint (in white) on the second line. The FROM/TO flight plan leg is called
the active leg.
The flight crew can use the scroll keys to review all flight plan legs down to the last point of the
alternate flight plan. The AIRPORT key serves as a fast slew key. The pilot can press it to call up
the next airport (DEST , ALTN, ORIGIN) to be displayed on the flight plan page.
In order to return to the beginning of the flight plan page, the pilot presses the F-PLN key on the
MCDU console.
The display shows the name of the leg between two waypoints, and the distance between them on
a line between the lines that identify them. During an approach, this in-between line also defines
the angle of the final descent path. For example, “2-3 °” indicates that the leg is two nautical miles
long, and the flight path angle is -3 °.
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OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The display shows the bearing between FROM and TO waypoints as the bearing from the aircraft
position to the TO waypoint. It shows track (TRK) between the waypoints shown in lines 2 and 3.
This is the outbound track of the next leg.
If the database contains a published missed approach procedure, or if someone has inserted one
manually, the display shows it in blue after the destination runway identification. It turns green
when the go-around phase becomes active.
After the last waypoint of the missed approach, the display shows the alternate flight plan in NAV
mode.
When NAV mode is engaged, the flight crew can only clear or modify the TO waypoint by using
the DIR key on the MCDU console.
PREDICTIONS
The system calculates and displays predictions for all waypoints.
It uses the current wind to compute TO waypoint predictions, and uses predicted winds to
compute all others.
CONSTRAINTS
The database may define an altitude and speed constraint for each waypoint of the climb,
descent, and approach phases, or the pilot may manually insert such constraints (except at
origin, destination, FROM, and pseudo-waypoints).
The constraints are displayed in magenta, as long as predictions are not completed.
Once predictions are available, constraints are replaced by speed and altitude predictions,
preceded by stars. If the star is in magenta, the system predicts that the aircraft will match the
constraint (altitude within 250 ft, speed not more than 10 kt above the constraints). If the star is
in amber, the system predicts that the aircraft will miss the constraint and the MCDU displays:
“SPD ERROR AT WPT”.
Note:
SPD and ALT CSTR may either be entered on the VERT REV page or directly on the
F-PLN A page, whereas TIME CSTR may only be entered from the RTA page.
PSEUDO-WAYPOINTS
Pseudo-waypoints are geographical positions corresponding to an event in the vertical flight
plan: T/C (top of climb), T/D (top of descent), SPD /LIM (speed limit), DECEL (deceleration for
approach), etc. The display shows them as waypoints in parentheses.
APPROACH DISPLAY
The flight crew cannot enter an altitude constraint at destination or Missed Approach Point
(MAP).
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
FLIGHT PLAN B PAGE
This page displays fuel predictions and forecast winds at each waypoint.
The pilot calls it up by pressing the NEXT PAGE key when the FLIGHT PLAN A page is displayed.
TITLE
FLIGHT NUMBER (blank if no flight number has been entered).
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Line 1 to Line 5
WPT-EFOB-WIND
These lines display consecutive waypoints and associated fuel
predictions, and the forecast wind profile.
The direction of forecast winds is relative to true north.
Forecast winds include winds entered by the pilot (large font) and the
propagated winds at intermediate waypoints (small font).
If the flight crew uses a trip wind, it will be displayed for each waypoint.
If no other wind entry is made after takeoff, the FROM waypoint will
display the actually recorded wind, and the waypoints downpath will still
display the trip wind.
Identical to F-PLN A page.
Line 6
DEST-UTC/DIST-EFOB
LATERAL REVISION PAGES
Ident.: DSC-22_20-50-10-25-00000564.0009001 / 01 OCT 12
Applicable to: ALL
These pages give the pilot a list of the lateral flight plan revisions, which can be used to change the
flight plan beyond a selected waypoint.
The pilot calls up these pages from the flight plan pages (A or B) by pressing the left key adjacent to
the selected waypoint.
Different lateral flight plan revisions are available for different waypoints.
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OPERATING MANUAL
TITLE
[ 1L ] DEPARTURE
[ 2L ] OFFSET
[ 3L ] HOLD
[ 4L ] ENABLE ALTN
[ 5L ] ALTN
[ 6L ] RETURN
[ 1R ] ARRIVAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The ident of the waypoint or airport selected for revision, along with its
latitude and longitude.
If the selected waypoint is the FROM waypoint, the title omits the aircraft
latitude and longitude, and displays the “PPOS” (present position) instead.
This prompt gives the pilot access to the departure pages, where he can
select and insert runways, SID s, and TRANSs.
This prompt gives the flight crew access to the OFFSET page.
This prompt gives access to the hold pages.
This prompt allows the pilot to switch to the alternate flight plan at the
selected revision waypoint, and use it as a new active flight plan.
The system never displays this prompt at the FROM waypoint.
This prompt gives access to the alternate airport page. The system
displays it only at the destination.
This prompt returns the display to the flight plan page.
This prompt calls up the arrival pages, where RWY , APPR, STAR TRANS
and VIA can be selected and inserted.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 1R ] FIX INFO
FIX INFO is only displayed on the lateral revision page at the origin or
FROM waypoint. It gives access to the FIX INFO page.
[ 2R ] LLXING/INCR/NO This prompt allows the pilot to create the latitude/longitude crossing point.
The increment (INCR) ranges from 1 to 20 °, and the number of crossing
points from 1 to 99. This prompt is not displayed for waypoints belonging
to the descent procedure.
[ 3R ] NEXT WPT
The pilot uses this prompt to enter the next waypoint. If this waypoint is
a latitude/longitude, or is neither in the database nor in the pilot-defined
elements, the display reverts to the NEW WAYPOINT PAGE.
[ 4R ] NEW DEST
The pilot uses this prompt to enter a new destination.
[ 5R ] AIRWAYS
The pilot uses this prompt to access the AIRWAYS page.
[ 6R ] INSERT
This prompt is displayed when the pilot has created a temporary flight
plan. It can be used to activate the temporary flight plan.
TEMPORARY REVISION
When the pilot selects a lateral revision, the system creates a “Temporary F-PLN ” and displays
it in yellow on the MCDU , and as a dashed yellow line on the ND, enabling the pilot to review the
data before inserting it. As long as the temporary flight plan is not inserted, the previous flight plan
remains active and the system guides the aircraft along it.
FIX INFO PAGE
Ident.: DSC-22_20-50-10-25-00000565.0009001 / 14 MAY 12
Applicable to: ALL
This page provides access to the RADIAL, CIRCLE, and ABEAM intercept functions.
The reference may be a given database fix or a pilot-defined element.
If the radial, circle or abeam intercepts the active flight plan, the intersection point can be converted
to a waypoint and inserted into the flight plan.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The FIX INFO page may be accessed from the LAT REV page at the origin airport, or at FROM.
[ 1L ] REF FIX (blue)
Allows entries of the REF FIX. This reference may be any database element
(navaid, waypoint, NDB, airport, runway) or a pilot-defined element. Prior to
entry, amber boxes are displayed.
Enables entry of a radial from the REF FIX.
[ 2L ] - [ 2R ] RADIAL
(blue) and [ 3L ] - [ 3R ]
If the radial line intersects the active flight plan, the FMGS will compute
(blue)
the time, the along path DTG (Distance To Go), and the altitude at the
intersection point (small green font). A large blue star is then displayed to
insert the intersection waypoint into the flight plan. This waypoint is not part
of the pilot-stored elements. Format of the created waypoint is:
XXXNNN
XXX = First 3 letters of REF FIX ident.
NNN = Value of the radial
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 4L ] - [ 4R ] RADIUS This function enables the flight crew to enter a radius that defines a circle
(blue)
around the REF FIX.
When the circle intercepts the current flight path, the FMGS will compute the
time, the along path distance and the altitude at the first intersection point,
from the current aircraft position (small green front).
A large blue star is then displayed to insert the intersection waypoint into the
flight plan. This waypoint is not part of the pilot stored element.
The waypoint is automatically labelled:
“DNNNXXX” NNN = Value of the radius
XXX = First 3 letters of the REF FIX ident.
[ 5L ] - [ 5R ] ABEAM
Note:
This function enables the pilot to create waypoints on a flight plan (primary
or secondary) that are abeam a reference fix.
Once computed, the page displays the radial number in large green font.
Time, distance and altitude predictions are displayed in small green font.
Selecting the key adjacent to the star creates the waypoint and inserts it into
the flight plan.
The waypoint is identified by AB + the REF FIX ident e.g. AB TLS.
Abeam waypoints are not stored in the pilot-stored waypoint database.
Four FIX INFO pages, providing the capability to define four different REF FIX elements,
are available.
OFFSET PAGE
Ident.: DSC-22_20-50-10-25-00013512.0019001 / 14 MAY 12
Applicable to: ALL
This page allows the flight crew to insert a preplanned offset into the flight plan by entering:
‐ A start waypoint
‐ An end waypoint
‐ An offset distance to the left or to the right
‐ The intercept angle value.
The flight crew calls up this page from the LATERAL REVISION page, by pressing [2L] key.
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TITLE
[ 1L ] OFFSET
[ 2L ] START WPT
[ 3L ] to [ 5L ]
[ 6L ] RETURN ERASE
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
OFFSET in white large font. If a temporary flight plan exists, it is displayed
in yellow large font.
This field displays the lateral offset distance, left or right, in the flight plan.
The offset may be between 1 and 50 NM. Blue brackets are displayed until
an offset is inserted. When the flight crew enters an offset, or modifies
another element in the OFFSET page, the OFFSET field becomes yellow.
One time the temporary flight plan is inserted, the field becomes blue.
The flight crew can delete an inserted offset either by pressing the CLR
key, by entering a zero for the amount of the offset, or by pressing
OFFSET DELETE in 6L field.
The START WPT ident for the offset is displayed in yellow if a temporary
flight plan exists, in blue if already inserted, or in green when the field is
not modifiable.
The default START WPT shall be the waypoint where the lateral revision is
performed, the first waypoint offsettable, or PPOS if the offset is currently
flown.
This waypoint can also be selected from the list of waypoints in the fields
3L to 5L, or can be manually entered by the flight crew.
Display the start waypoints available for selection. Two scrolling list are
available. The active start waypoint is displayed in green in the list. Other
waypoints are displayed in blue. The currently selected start waypoint
does not have selection arrow associated.
RETURN: The flight crew presses this key to return to the last displayed
LAT REV page.
ERASE: It is displayed when a temporary flight plan has been created, and
it enables the flight crew to erase the temporary flight plan.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 1R ] INTCPT ANGLE
This field displays the intercept angle. The angle may be between 10 ° and
50 °. The intercept angle in the AMI is the default value, and is shown in
blue. When the flight crew enters an intercept angle, or modifies another
element in the OFFSET page, the field becomes yellow. One time the
temporary flight plan is inserted, the field becomes blue.
[ 2R ] END WPT
The END WPT ident for the offset is displayed in yellow if a temporary
flight plan exists, or in blue if already inserted. The default END WPT
shall be the waypoint terminating the last consecutive offsettable leg from
default or currently selected START WPT.
This waypoint can also be selected from the list of waypoints in the fields
3R to 5R, or can be manually entered by the flight crew.
[ 3R] to [ 5R ]
Display the end waypoints available for selection. Two scrolling lists are
available. The active end waypoint is displayed in green in the lists. Other
waypoints are displayed in blue. The currently selected end waypoint does
not have selection arrow associated.
[ 6R ] INSERT OFFSET INSERT: This field allows the flight crew to activate the temporary flight
DELETE
plan and reverts the display to the active flight plan. This field is displayed
when the offset segment is completely defined on OFFSET page.
OFFSET DELETE: This prompt enables the flight crew to create a
temporary flight plan where the predefined offset is canceled. This field is
displayed when an offset exists in the active flight plan.
Note:
If the waypoint lists in lines 3 to 5 do not fit in one page, the flight crew can scroll in an open
loop, two lines by two lines. To keep the initial order of the list, two markers appear:
‐ - START OF LIST - : This marker is displayed at the beginning of the list
‐ - END OF LIST : This marker is displayed at the end of the list.
AIRWAYS PAGE
Ident.: DSC-22_20-50-10-25-00000566.0009001 / 14 MAY 12
Applicable to: ALL
This page allows the pilot to select up to five airways for stringing into the flight plan, after the revise
waypoint.
The pilot calls up this page by pressing the lateral revision page [ 5R ] key.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
TITLE
[ 1L ] to [ 5L ] VIA
[ 6L ] ERASE or
RETURN
Revise point ident (large green font)
This field displays the airways entered by the pilot.
The flight crew presses this key to return to the lateral revision page. This
field displays ERASE when a temporary flight plan is created. It enables the
temporary flight plan to be erased.
[ 1R ] to [ 5R ] TO
Displays the end points of the corresponding airways entered on the
[ 1L ] to [ 5L ] entries. The ending point is displayed in large blue font, if
manually-entered, in blue small font if FMGC-computed.
[ 6R ] INSERT (amber) Allows the entered VIA/TO segments to be inserted into the flight plan. The
display reverts to the F-PLN page.
Note:
1. If the entered airway contains at least one fixed radius transition waypoint as defined in
the navigation database, and the TO waypoint is defined and, the fixed radius transition
waypoint is in the flight plan, then, “FIXED TURN RADIUS AWY ” is displayed between
the VIA and TO fields.
2. If the condition for display “FIXED TURN RADIUS AWY” is satisfied for two consecutives
airways lines, the second line displays (“) instead of the whole message.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
DEPARTURE PAGES
Ident.: DSC-22_20-50-10-25-00000567.0001001 / 17 MAR 11
Applicable to: ALL
These pages allow the pilot to review departure procedures (RWY , SID , TRANS) and enter them
into the active flight plan.
When the display shows the lateral revision page for the origin, the pilot calls them up by pressing
the 1L key.
Three pages are available: RWY , and SID S and TRANS (if any).
The pilot sequentially calls up each page by selecting a data item (such as RWY ), or by pressing the
NEXT PAGE key on the MCDU console.
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Line 1 RWY, SID
TRANS
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This line displays the RWY , SID , and TRANS in green after they have been
inserted into the active flight plan, or in yellow if selected but not yet inserted.
If nothing has been selected or inserted, the line displays dashes.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 2L ] to [ 5L ]
RWY/SIDs
These fields display selectable and selected RWY s or SID s (including
EOSID and NO SID option). The pilot can slew each list. Selectable RWY s
and SIDs are displayed in blue with an arrow.
Once a RWY or SID is selected, the arrow disappears.
A RWY or SID, already inserted in the flight plan, is displayed in green.
The display shows the length, heading, and, if available, the ILS ident and
frequency for each runway.
[ 6L ] ERASE or
The pilot presses this key to erase a selected data item and revert to the
RETURN
previous selection.
If the pilot erases the page, the display reverts to the active flight plan page.
The display shows RETURN instead of ERASE, when the pilot has not
created a temporary flight plan.
[ 2R ] to [ 5R ] TRANS This field displays the selectable and selected enroute transitions in blue and
green respectively. They are blank, if there are no transitions.
[ 6R ] INSERT or
The pilot uses this key to insert a temporary procedure into the flight
BLANK
plan. The page reverts to the active flight plan page, when the insertion is
completed.
It is associated with RETURN (6L).
[ 6M ] EOSID
Once a runway is inserted into the flight plan, this field displays any ENG
OUT SID for that runway. If there is none, it displays NONE.
HOLD PAGES
Ident.: DSC-22_20-50-10-25-00000568.0001001 / 01 OCT 12
Applicable to: ALL
These pages allow the pilot to review and modify the holding pattern parameters at the selected
revise waypoint.
The flight crew calls up these pages by pressing the HOLD key on the LAT REV page for the
waypoint. The flight crew can insert database hold, holds computed by the FMS or holds that they
manually define.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
At first access, the HOLD page appears as follow:
DATABASE HOLD
If a hold is defined in the navigation database for the revised waypoint, and can be inserted, the
parameters in [ 1L ], [ 2L ] and [ 3L ] appear in yellow.
COMPUTED HOLD
If a default hold is computed by the FMS and can be inserted, the parameters in [ 1L ], [ 2L ] and
[ 3L ] appear in yellow.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
A computed hold has the following default parameters:
[ 1L ] INB CRS
Inbound track of the F-PLN leg leading to the revised waypoint
[ 2L ] TURN
Direction right (R) to turn in the hold
[ 3L ] TIME/DIST
TIME on outbound leg is 1.5 min above 14 000 ft, 1 min below 14 000 ft.
[ 2R ]
This field shows “REVERT TO COMPUTED” when the flight crew has
modified the holding pattern.
HOLD MODIFIED BY FLIGHT CREW
If the flight plan contains a holding pattern that was defined by the pilot from an existing database
or computed hold, the parameters in [ 1L ], [ 2L ] and [ 3L ] appear in blue.
If the pilot has modified holding pattern data from the database, the field next to [2R] displays
“REVERT TO DATABASE” or “REVERT TO COMPUTED” to enable the pilot to revert to default
parameters.
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EXAMPLE
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The pilot modifies the inbound course.
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[ 1L ] INB CRS
[ 2L ] TURN
[ 3L ] TIME/DIST
[ 6L ] ERASE or
RETURN
[ 2R ] REVERT TO...
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This field displays the inbound course of the holding pattern. The data may
be manually or automatically modified.
This field shows the direction to turn in the hold (L or R). The data may be
modified.
This field shows the time and distance for the outbound leg. The data may
be modified, but time and distance cannot be entered simultaneously.
Time and distance are dependent values that the system calculates from
the predicted true airspeed, which in turn depends upon the holding speed
(speed for maximum endurance, ICAO speed limit, or constraint speed,
whichever is lower).
The pilot presses this key when the field shows “ERASE”, to erase the
holding pattern.
The pilot presses this key when the field shows “RETURN”, to return to the
LAT REV page, if the hold is already inserted in the flight plan.
The pilot presses this key to delete manual modifications to the database
hold (or computed hold), and to revert to the database (or computed)
holding data.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 6R ] INSERT
The pilot presses this key to insert the hold into the active flight plan.
LAST EXIT UTC FUEL This field displays the time at which the aircraft must leave the holding
pattern in order to meet fuel policy criteria (extra fuel = 0). The system
also displays the estimated fuel on board at that time. Always displayed in
thousand of kilograms or pounds.
DIRECT TO PAGE
Ident.: DSC-22_20-50-10-25-00000569.0001001 / 23 JUN 15
Applicable to: ALL
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Pressing the “DIR ” key under the MCDU screen brings up the DIR TO page. On this page, the [ 1L ]
key is the DIR TO key. The pilot presses it to modify the flight plan by creating a direct leg from the
aircraft's present position to any selected waypoint. When in NAV mode, the pilot must use this key
to modify the active leg or the TO waypoint. The pilot cannot call up this page when the aircraft's
present position is not valid.
[ 1L ] DIR TO
Pressing this key selects the DIRECT TO or INTERCEPT waypoint.
The pilot can identify the waypoint to be inserted by using its
identifier, its latitude and longitude, place/bearing/distance, or
place-bearing/place-bearing.
Note:
Line 3 to Line 6
[ 2L ] ABEAM PTS
If the entered DIR TO is a latitude/longitude, the NEW WAYPOINT
page is automatically called up.
If the pilot does not select the RADIAL IN (1R) or RADIAL OUT (2R) or
ABEAM PTS (2L), the DIR TO function routes the aircraft from the present
position to the waypoint inserted in the DIR TO field.
These lines display the active flight plan with time/speed/distance
predictions. The display may be slewed ↑↓.
Pressing any key activates the DIRECT TO function from the present
position to the waypoint adjacent to that key.
The flight crew presses this key to activate the DIR TO /ABEAM function
which projects the flight plan waypoints perpendiculary on the DIR TO leg:
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
EXAMPLE: DIR TO BEROK - ABEAM.
[ 1R ] RADIAL IN and The pilot fills in these fields to define a radial, associated to the waypoint
[ 2R ] RADIAL OUT
defined in 1L. These keys respectively activate the DIR TO /INTERCEPT
TO and DIR TO/INTERCEPT FROM functions. The pilot enters the radial
in, or radial out, as : XXX, XXX being the radial.
The aircraft intercepts from its current position and tracks the selected
waypoint and radial to (or from) this waypoint.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
EXAMPLE: RADIAL INBND - DIR TO BEROK - RADIAL 270 ° INBOUND
If the DIR TO /INTCPT WPT entry is to a waypoint already in the flight plan, a default RADIAL IN is
displayed in small font. However, no radial is displayed on the ND for this default radial. No default
radial is provided for the RADIAL OUT field.
Selecting the INTCPT TO (RADIAL IN [ 1R ]) function:
‐ Activates the intercept radial INTO the WPT.
‐ Sets the course = radial IN + 180 °.
‐ Reverts the display to the F-PLN A page.
Selecting the INTCPT FROM (RADIAL OUT [ 2R ]) function:
‐ Activates the intercept radial FROM the WPT.
‐ Sets the course = radial OUT.
‐ Reverts the display to F-PLN A page.
For details, DSC_22_20_30 Flight Planning.
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OPERATING MANUAL
Note:
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
It is not recommended to use the DIR TO function when the aircraft is on the ground. The
use of the DIR TO function when the aircraft is on the ground may result in the loss of all
departure data, that includes both of the following:
‐ The takeoff speeds
‐ The derated level, or the flexible temperature.
ARRIVAL PAGES
Ident.: DSC-22_20-50-10-25-00000570.0009001 / 14 MAY 12
Applicable to: ALL
These pages enable the pilot to review arrival procedures (approaches, VIAs, STAR s, TRANS) and
enter them into the active flight plan.
The pilot calls them up from the LAT REV page for the destination by the pressing the 1R key.
Three pages, APPR , STAR , and VIA, are available, along with a fourth,TRANS, if there are any
transitions.
The pilot calls up each page sequentially, either by selecting a data item (such as APPR ), or by
pressing the NEXT PAGE key on the MCDU console.
Line [ 1L ] - [ 1R ] [ 2R ] This line displays the APPR , VIA, STAR , and TRANS in green, if they have
been inserted in the flight plan, and in yellow, as a temporary flight plan, if
they have been selected but not yet inserted.
It displays dashes or NONE, if nothing has been selected or inserted.
[ 2L ] APPR VIAS
The pilot presses this key to call up transitions from the last point of the
STAR to the first point of the approach.
[ 3L ] to [ 5L ]
These fields list selectable and selected APPR s, STAR s, and VIAs. The
flight crew can slew the pages, when necessary. Selectable APPR s,
STARs, and VIAs are displayed in blue with an arrow.
Once the pilot has selected an APPR , STAR , or VIA, the arrow disappears.
After the APPR , STAR, or VIA is inserted into the flight plan, it is displayed
in green.
For each approach, the display shows runway length, heading, and the
frequency and identifier of the ILS when ILS is available.
In case there are multiple approaches for the same runway, the approach is
identified with the runway plus the multiple indicator (i.e. ILS 33L-S).
[ 6L ] ERASE or
The pilot presses this key to erase selected data and to revert to the
RETURN
previous selection. The page reverts to the LAT REV page.
The field displays “RETURN”, instead of ERASE, when the flight crew has
not created a temporary flight plan.
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[ 3R ] TRANS to [ 5R ] These fields display selectable and selected enroute transitions (if any).
They are blue when selected, and become green when inserted into the
active flight plan.
[ 6R ] INSERT
The pilot presses this key to insert the temporary procedure into the active
flight plan. The page reverts to the active flight plan page when this occurs.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
ALTERNATE PAGE
Ident.: DSC-22_20-50-10-25-00000571.0001001 / 17 MAR 11
Applicable to: ALL
This page enables the pilot to review, in the NAV database, the alternate airports that are paired
with the destination, and define additional alternates, if needed. (Alternate airports are linked to the
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
destination). The pilot calls up this page with the ALTN prompt, from the lateral revision page for the
destination.
TITLE
[ 1L ] ALTN
Line 2 to line 5
The destination airport is displayed large green font.
This field displays the selected alternate: In green, if it is active; in yellow, if
it is temporary. “NONE” is displayed, if NO ALTN option is selected, or if the
destination has no alternate.
These lines display the identifications of alternates (up to 6), the extra fuel
weight remaining after landing at the alternates, and the great-circle track
and distances to them from the destination.
If the database contains a company route between the destination and
the alternate, the distance shown is an airway distance, not a great-circle
distance.
When the database defines a preferred alternate, it is displayed on Line 2 (if
no scrolling has been performed).
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[ 4L ] OTHER ALTN
NO ALTN
[ 6L ] RETURN or
ERASE
[ 1R ] CO RTE
[ 6R ] INSERT
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The pilot can enter an airport identifier in the brackets (Line 3). If that airport
is not stored in the database , the NEW RUNWAY page appears for the pilot
to use in defining it.
If it is stored in the database, the ROUTE SELECTION page appears, and
the pilot can use it to select the best route.
The pilot may enter a distance in the DIST field of the OTHER ALTN prompt,
in order to get preliminary fuel predictions. However, once he has selected
the alternate airfield as a temporary alternate and then inserted it, the ALTN
distance reverts either to the airway distance, if he has selected a company
route, or otherwise to the direct distance to the alternate.
The pilot can use OTHER ALTN to overwrite and replace the previous
OTHER ALTN.
The pilot uses this key to select the NO ALTN option.
The pilot presses this key to make the display revert to the LAT REV page.
Pressing this key erases the temporary selection.
Pressing this key displays the active company route between the destination
and the selected alternate.
Pressing this key activates the temporary selection.
ROUTE SELECTION PAGE FOR ALTERNATE
Ident.: DSC-22_20-50-10-25-00000572.0001001 / 17 MAR 11
Applicable to: ALL
This page enables the pilot to review the company route between the destination and the alternate,
and to select a different route, if that seems appropriate.
This page comes up automatically, when the flight crew enters an ident in the OTHER ALTN field.
See the “Route Selection” page Refer to DSC-22_20-50-10-25 Route Selection Pagefor a description
of this page.
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[ 6R ] SELECT
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Pressing this key reverts the display to the alternate page. (The distance
between the destination and the alternate is then the airway distance).
VERTICAL REVISION PAGES
Ident.: DSC-22_20-50-10-25-00000573.0009001 / 14 MAY 12
Applicable to: ALL
These pages contain the menu of available vertical flight plan revisions that can be applied at a
selected waypoint.
The pilot calls up these pages from the flight plan A or B pages by pressing the right hand key next to
the selected revised waypoint.
The pilot may make several different vertical revisions (although some may not be available at all
waypoints): Speed limit, speed constraint, altitude constraint, time constraint, wind page and STEP
ALTS page.
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← S to T →
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←T→
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TITLE (white)
[ 1L ] “TOO
STEEP PATH
BEYOND” (amber)
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
“VERT REV AT [location]”
The second line shows remaining fuel and extra fuel at the waypoint being
revised.
This message is displayed, if the waypoint is part of a leg with too steep a
descent path.
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 2L ] CLB/DES SPD
LIM (magenta)
This field displays the speed limit applicable to the climb or descent phase. It
displays it in large font when data has been inserted manually, and in small
font when data comes from the database.
[ 3L ] SPD CSTR
This field displays any speed constraint assigned to the revised waypoint. It
(magenta)
is in large font when inserted manually, and in small font when it comes from
the database.
It is not displayed at the origin airport, at a FROM waypoint, a speed limit
pseudo waypoint, or the destination airport.
[ 4L ] QNH
This field only functions when the revised waypoint is the primary
destination.
It allows the pilot to enter the atmospheric pressure at sea level.
This field is identical to the QNH field of the PERF APPR page.
[ 4L ] MACH/START This prompt allows the pilot to enter or modify the start point of a
WPT (blue)
constant Mach segment, and its associated Mach. It is not displayed
at primary destination and alternate flight plan waypoints. (Refer to
DSC-22_20-30-20-25 Constant Mach Segment - Entering a Constant Mach
Segment).
[ 5L ] WIND (blue)
The pilot presses this key to access the wind pages.
The first wind displayed page, corresponds to the selected waypoint (e.g.
climb page), if the selected waypoint is a climb phase waypoint.
A CLR action reverts it to brackets.
[ 6L ] RETURN or CLB The pilot presses this key to return to the last displayed flight plan page.
When displayed, pressing this key assigns the constraint to CLB phase and
inserts it into the vertical flight plan. The page reverts to the flight plan page.
[ 2R ] RTA prompt
This prompt gives access to the RTA page. It is not displayed when the
VERT REV page is accessed from the alternate F-PLN.
[ 3R ] ALT CSTR
This field displays the altitude constraint assigned to this revised waypoint.
(magenta)
It uses large font when the constraint is manually-entered, and small font
when it is from the database.
A CLR action reverts it to brackets.
The constraint may be:
‐ “At”, entered as XXXXX (Example: FL 180).
‐ “At or above”, entered as + XXXXX or XXXXX + (Example: FL +310).
‐ “At or below”, entered as – XXXXX or XXXXX – (Example: -5 000).
‐ A “window” constraint.
The altitude window consists of two altitudes between which the aircraft
should fly. The crew cannot manually enter a “window” constraint.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
G/S INTCP (green)
This field displays the glide intercept altitude for an ILS approach on the
vertical revision page at destination.
[ 4R ] ALT ERROR
When the aircraft misses a predicted altitude constraint, this field displays
(green)
the difference between the altitude constraint and the predicted altitude.
If, for example, “-500” appears in this field in green, the aircraft will reach the
waypoint at an altitude 500 ft below the constraint altitude.
This only applies to waypoints in the climb and descent phases.
[4R] END WPT (blue) This prompt allows the pilot to enter or modify the endpoint of a constant
Mach segment. It is displayed when a pair Mach/start exists in 4L field.
This prompt is not displayed on the destination VERT REV page. (Refer to
DSC-22_20-30-20-25 Constant Mach Segment - Entering a Constant Mach
Segment).
[ 5R ] STEP ALTS
This legend appears for any waypoint, once a cruise altitude has been
(white)
entered. It is not available in engine-out, descent, approach, and go-around
phases.
This gives the pilot access to the STEP ALTS page.
[ 6R ] DES
When this field displays “DES ”, pressing this key assigns the constraints to
the descent phase and inserts them into the vertical flight plan. The page
reverts to the F-PLN page. (See note below).
Note:
Altitude and speed constraints may apply to the climb, descent, or approach phase, but
never to the cruise phase. Fields 6L/6R display “CLB /DES ” when the revised waypoint is
a cruise phase waypoint and the FMGS needs to know if the new constraint is to be applied
in climb or descent phase. The FMGS will modify the cruise phase accordingly. These 2
prompts also display “CLB /DES” when the predictions are not computed. (Top of climb and
top of descent not yet defined).
STEP ALTS PAGE
Ident.: DSC-22_20-50-10-25-00000574.0009001 / 14 MAY 12
Applicable to: ALL
This page allows the pilot to insert up to four geographic step points and one optimal step point into
the flight plan. This page also displays the fuel/time savings associated with the optional step.
The flight crew calls it up either from the vertical revision page.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
TITLE [1L] - [1R] [4L] - STEP ALTS in white followed by the current cruise altitude in green.
[4R]
ALT/WPT {blue} : The waypoint identifier, as well as the altitude to step, can be entered in
this field. Both are displayed in large font. The waypoint may either be an
active (or secondary) flight plan waypoint, or an inserted optimal point (OPT
). When an entry is made, a temporary F-PLN is created.
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FLIGHT CREW
OPERATING MANUAL
DIST / TIME (UTC)
(small green font)
Displays the distance to go, and time from the present aircraft position along
the flight plan to the step point.
Note:
Note:
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The following messages may be displayed in the DIST/TIME field:
‐ ABOVE MAX , if the step altitude exceeds the MAX altitude.
‐ “IGNORED”, if the step start or end point is less than 50 NM
from the top of descent or if the step climb is located prior to the
top of climb or after the top of descent.
‐ “STEP AHEAD”, when the aircraft is within 20 NM of the start
step point.
‐ “NO OPTIMAL” if a non inserted optimal step falls in a
discontinuity due to a flight plan change, or when no new optimal
exists after an UPDATE or when no optimal step point exists for
the entered altitude.
If no optimal step point exists for the altitude displayed in [ 1L ], the “NO OPTIMAL”
message is displayed in the FUEL/TIME field. This message is also displayed, if the optimal
step falls into a discontinuity.
[ 5L ] OPT STEP:
ENTER ONLY ALT
(white) TO OPT S/C
(green small front)
This field displays the distance and time to an uninserted optimal step point,
if one exists. It is displayed to guide the flight crew for the entry format of an
optional step.
[ 6L ] RETURN
[ 5R ] SAVINGS
The flight crew presses this key to return to the previous page.
This field displays the fuel and time savings prior to the insertion of the
optimal step point.
Note:
On any flight plan change, an inserted optimal step remains in the
flight plan at a fixed distance to destination.
Fuel savings are displayed in thousand of kilograms (or pounds) (maxi 99.9).
The value is preceded by:
“–” in case of fuel saving,
“+” in case of additional fuel cost.
Time savings are displayed in hours and minutes. The value is preceded by
“–” in case of time saving,
“+” in case of additional time cost.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 6R ] INSERT* (amber) This field displays INSERT*, when an optimal step point exists but is not yet
inserted. When INSERT is selected:
‐ The optimal step point is inserted into the flight plan.
‐ OPT is displayed in line 1L.
‐ Optimal step distance and time are deleted in line 5L.
‐ The UPDATE* blue prompt replaces the INSERT* prompt.
UPDATE*
This prompt enables the computation of another optimal step point.
The UPDATE* prompt is then replaced by the INSERT* prompt.
RTA PAGE
Ident.: DSC-22_20-50-10-25-00000575.0009001 / 14 MAY 12
Applicable to: ALL
The Required Time of Arrival (RTA) page allows the entry and display of a waypoint identifier, with
associated time constraints. The page also displays the entered or computed Estimated Takeoff
Time (ETT), as well as the following data:
‐ Predicted ETA at the time-constrained waypoint;
‐ Performance adjusted SPD target;
‐ Time error;
‐ Distance to time constrained waypoint;
‐ Active speed mode;
The flight crew calls up this page with the RTA prompt from the vertical revision page.
TITLE
RTA (large white font)
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line 1
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This line displays:
‐ AT WPT , DIST and RTA when a time constraint can be defined. The
identifier of the revised waypoint or the first following waypoint at which
the time constraint can be defined, is displayed by default in large blue
font
‐ AT WPT , DIST and RTA when a time constraint has already been
defined. The associated constrained waypoint identifier is displayed by
default in large blue font
‐ AT WPT and white dashes when no time constraint can be defined
‐ AT WPT and blue brackets if a time constraint can only be introduced
before the waypoint at which the VERT REV has been initiated.
Only when the waypoint identifier has been defined (by the flight crew or by
default), blue brackets and a blue start are displayed in [ 1R ] field.
The flight crew enters the time constraint as “HHMMSS”, preceded by:
- for at or before;
+ for at or after;
no sign for at.
[2L] MANAGED
[3L] ACT MODE
[6L] RETURN
[2R] ETA
[3R] RTA ERROR
[6R] ETT
UTC
This field displays the FMGS -computed ECON speed/Mach (Refer to
DSC-22_20-40-10 Optimization)
This field displays the active speed mode : MANAGED or SELECTED/NNN
(NNN is the selected target speed).
The pilot cannot modify it through this field.
The pilot presses this key to revert the display to the VERT REV page.
When a required time at arrival has been defined, the 2R field displays the
estimated time of arrival as “HHMMSS”.
This field is blank when the RTA is predicted as made.
If the RTA is predicted as missed, “RTA ERROR” is displayed in small white
font, and the time error between ETA and RTA is displayed in small amber
font.
The Estimated Takeoff Time (ETT) field is available in the preflight phase.
If no ETT is available, the 6R field displays blue brackets and a blue star.
Once available, the ETT is displayed in magenta.
Universal time is displayed in green for takeoff, climb, cruise, descent and
approach phases.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
DATA INDEX PAGES
Ident.: DSC-22_20-50-10-25-00000576.0001001 / 17 MAR 11
Applicable to: ALL
There are two INDEX pages:
The DATA INDEX 1/2 page gives access to various pages devoted to navigation.
The DATA INDEX 2/2 page lists the navigation data, entered in the FMGS.
The pilot enters those items labeled “stored” and can modify them. The pilot can call up the others,
but cannot modify them.
The pilot calls up these pages by pressing the DATA key on the MCDU console:
DATA INDEX 1/2 PAGE
[1L] POSITION
MONITOR - [2L] IRS
MONITOR
[3L] GPS MONITOR
[4L] A/C STATUS
[5L] CLOSEST
AIRPORTS.
[6L] EQUITIME POINT
[6R] ACARS/PRINT
When the flight crew presses these keys, the display shows all essential
navigation data.
This key calls up the GPS MONITOR page.
This key calls up the aircraft status page.
This key calls up the closest airports page.
This key calls up the equitime point page.
This key calls up the PRINT function pages and the ACARS function
pages.
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W→
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
DATA INDEX 2/2 PAGE
[ 1L ] WAYPOINTS
[ 2L ] NAVAIDS
[ 3L ] RUNWAYS
[ 4L ] ROUTES
[ 1R ] STORED WAYPOINTS
[ 2R ] STORED NAVAIDS
[ 3R ] STORED RUNWAYS
[ 4R ] STORED ROUTES
These keys call up descriptions of waypoints, NAVAIDs, runways, and routes
stored in the database, so that they can be reviewed.
These keys call up waypoints, NAVAIDs, runways, and routes that the pilot has
stored, enabling the pilot to review and store them in, or delete them from, the
database.
The airline can choose to automatically have all pilot-stored data erased in the
done phase.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
WAYPOINT/STORED WAYPOINT/NEW WAYPOINT PAGES
Ident.: DSC-22_20-50-10-25-00000577.0001001 / 01 OCT 12
Applicable to: ALL
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
WAYPOINT PAGE
‐ The pilot can call up this page by pressing the 1L key on the DATA INDEX page. The display
then shows waypoint information associated with the identifier the flight crew inserts it in the
[ 1L ] field.
‐ With this page it is possible to call any waypoint not stored in the stored waypoint list, if they
belong to the active, temporary, or secondary flight plan.
STORED WAYPOINT PAGE
The pilot calls up this page by pressing the 1R key on the DATA INDEX page.
This page displays waypoints, defined and stored by the pilot. It lists each stored waypoint, along
with a number that shows the relative order in which it was inserted in the database. This number
is displayed in the upper righthand corner of the page. For example, “1/20” indicates that the
waypoint was the first of 20 stored.
Note:
Latitude/Longitude crossing points and Abeam/Radial Intercept points are never included
in the stored waypoint list.
[ 1L ] IDENT
[ 2L ] LAT/LONG
[ 3L ]
[ 5R ] NEW
WAYPOINT
[ 6R ] DELETE ALL
To delete a waypoint, the pilot clears the 1L ident display.
Latitude and longitude of the waypoint are displayed in this field.
This field either displays PLACE/BRG /DIST or PLACE-BRG/
PLACE-BRG or PLACE/DIST, depending on how the waypoint was
defined.
The pilot presses this key to call up the NEW WAYPOINT page.
The pilot presses this key and the label changes to amber CONFIRM
DELETE ALL. Pressing this key a second time deletes all the waypoints,
stored by the flight crew, except those currently used in the active or
secondary flight plan. (“F-PLN ELEMENT RETAINED” appears on the
MCDU).
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
NEW WAYPOINT PAGE
‐ The pilot calls up this page by pressing the 5R key on the STORED WAYPOINT page.
‐ The pilot can use this page to define and store up to 20 waypoints. Entering an additional
waypoint deletes the first one.
The pilot defines a waypoint by entering its ident in the data field next to 1L, then by entering its
position in the amber boxes.
The STORE prompt appears next to 6R when the boxes are filled in, and the pilot presses the
key to store the waypoint in the database.
If the pilot enters the waypoint's position as place/bearing/distance, or
place-bearing/place-bearing, the FMGC computes its latitude and longitude.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
NAVAID/STORED NAVAID/NEW NAVAID PAGES
Ident.: DSC-22_20-50-10-25-00000578.0001001 / 01 OCT 12
Applicable to: ALL
NAVAID PAGE
The pilot calls up this page by pressing the 2L key on the DATA INDEX page 2.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This page displays NAVAID information associated with the identifier the pilot inserts in the [ 1L ]
field.
[ 2L ] CLASS
This field identifies the NAVAID as VOR , DME , VOR DME , VORTAC,
NDB , LOC , ILS , MLS , ILS /DME , MLS /DME , ILS /TAC or TACAN. It
displays NON COLLOCATED, if the NAVAID is uncollocated.
[ 4L ] FREQ or CHAN CHAN is displayed, if the class of NAVAID is an MLS or an MLS DME.
[ 5L ] ELV
This field gives the NAVAID elevation in feet above sea level. It is not
displayed for VOR or NDB.
[ 6L ] FIG OF MERIT This field shows how far out the FMGS can autotune a VOR , VOR /DME ,
VORTAC, or DME for display or for computing position.
0 : up to 40 NM
1 : up to 70 NM
2 : up to 130 NM
3 : up to 250 NM
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OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 1R ] STATION DEC This is the magnetic declination in the NAVAID area (used only for VOR ,
or RWY IDENT
VOR /DME, and VORTAC).
The field displays RWY IDENT , if the NAVAID is a LOC , ILS , MLS , ILS
/DME , MLS /DME or ILS/TAC.
[ 2R ] CATEGORY
This field shows the NAVAID 's category, if it is an ILS , ILS /DME , MLS ,
MLS /DME or ILS /TAC. A LOC DME has a category = 0.
[ 3R ] COURSE
This is the localizer course, if the NAVAID is an ILS or a LOC.
[ 6R ] RETURN
This prompt is displayed, if the page has been accessed from the
SELECTED NAVAID page. The pilot presses this key to return to the
SELECTED NAVAID page.
STORED NAVAID PAGE
The pilot calls up this page by pressing the 2R key on the DATA INDEX page. This page is used to
display or delete defined and stored NAVAIDs.
A number in the upper righthand corner of the screen shows the relative order in which the
NAVAIDs were stored. (For example, 3/7 means the third out of the seven stored).
Slew keys give the pilot access to the different stored NAVAIDs.
[ 1L ] IDENT
The pilot deletes a stored NAVAID by entering its ident in this field, then by
pressing the CLR key at the bottom of the MCDU control panel.
[ 6R ] DELETE ALL
The pilot presses this key to erase all the stored NAVAID s, except those
and CONFIRM
currently used in the active or secondary flight plan. (The MCDU displays
DELETE ALL
“F-PLN ELEMENT RETAINED.”).
NEW NAVAID PAGE
The pilot calls up this page by pressing the 5R key on the STORED NAVAID page.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
It can be used to define and store up to 20 NAVAID s. Entering an additional waypoint deletes the
first one. The NAVAID elements must be entered in two steps:
1. Enter the data in the lines of amber boxes.
2. Enter frequency, elevation, figure of merit, and station declination or ILS category and course, if
applicable.
Note:
The pilot cannot create an ILS /DME or an uncollocated NAVAID.
If the runway associated with the ILS has been entered through the new runway page,
the course, IDENT , and runway IDENT are already displayed on the new NAVAID page
when it comes up (copied from the new runway page). For details, see the new runway
page info below.
[ 1R ] STATION DEC The pilot must enter the magnetic declination, if the prompt is displayed.
This prompt is displayed only for VOR , VORTAC or VOR /DME.
[ 3R ] COURSE
If the NAVAID is an ILS , LOC, enter the course.
[ 6R ] STORE
This prompt appears when all the amber boxes are filled in. The pilot
presses the key to store the NAVAID.
A stored NAVAID is never used for position computation.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
RUNWAYS/STORED RUNWAYS/NEW RUNWAY PAGES
Ident.: DSC-22_20-50-10-25-00000579.0001001 / 17 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
RUNWAY PAGE
This page displays the following information:
[ 1L ] IDENT
The runway IDENT, which comprises the airport identification and the
runway direction, uses six or seven digits (Example: CYYZ 24L and LFRJ
08).
[ 2L ] LAT/LONG
The latitude and longitude of the runway threshold.
[ 4L ] LENGTH
The runway length in meters (M) or feet (ft), in five digits (9 999 ft).
[ 5L ] ELV
The elevation of the threshold in feet above sea level.
[ 6L ] CRS
The runway course (degrees magnetic).
[ 1R ] LS IDENT
The LOC or ILS identifier.
STORED RUNWAY PAGE
The pilot uses this page to display or delete the defined and stored runways. The stored runways
are listed and numbered in the order in which they were inserted. The number is displayed in the
upper righthand corner of the page. (For example, 2/4 means the runway is the second of the four
stored runways).
The pilot can delete any stored runway from the database by displaying its IDENT in the 1L field,
then by pressing the CLR key on the MCDU control panel.
[ 6R ] DELETE ALL
The pilot presses this key to erase all the stored runways, except those
and CONFIRM
used in the active or secondary flight plan. (The MCDU displays “F-PLN
DELETE ALL
ELEMENT RETAINED”).
[ 1L ] to [ 6L ]
These fields are similar to the RUNWAY page fields.
NEW RUNWAY PAGE
The pilot can use this page to define and store up to 10 runways.
When the pilot enters an ILS /LOC IDENT in the [ 1R ] field the new NAVAID page comes
up. When the pilot has entered and stored the necessary data in the new NAVAID page,
the new runway page reappears.
The new runway page and the new NAVAID page (ILS /LOC) are not independent:
When the flight crew first defines the ILS /LOC (on the new NAVAID page) the new
runway page, when called up, already displays the RWY course, RWY IDENT , and ILS
IDENT (copied from the new NAVAID page).
When the flight crew first defines the runway (on the new runway page) the new
NAVAID page, when called up, already displays the ILS course, ILS IDENT , and runway
IDENT.
The pilot must enter the two runway directions on two different new runway pages (Example: LFRJ
08 and LFRJ 26) to allow the flight plan to select either one.
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←Z→
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OPERATING MANUAL
Note:
When 10 runways are stored, entering a new stored runway deletes the first one of the
list (1/10).
[ 1L ] to [ 6L ]
[ 1R ] LS IDENT
[ 5R ] RETURN
[ 6R ] STORE
Note:
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Enter information about the new runway.
Enter the ILS /LOC IDENT . The NEW NAVAID page comes up.
The pilot presses this key to return to the NEW NAVAID page.
This prompt only appears when all the amber boxes have been filled in.
The NEW RUNWAY may be used for departure or destination, but no SID or STAR
can be associated or stored with this runway. Therefore, the pilot will use it as an
“independent” airport.
A new runway is identified by the 4–letter ICAO airport identifier, although all six or seven
digits must be entered.
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FCOM
←Z
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
ROUTE/STORED ROUTE/NEW ROUTE PAGES
Ident.: DSC-22_20-50-10-25-00000580.0001001 / 01 OCT 12
Applicable to: ALL
ROUTE PAGES
(Not-modifiable)
[ 1L ] CO RTE
Any company route IDENT, entered in this field, causes all the elements of
the route to be displayed.
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FCOM
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Line 2 to Line 6
[ 1R ] FROM/TO
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
These lines display the various route elements, including waypoints and
airways.
This field is automatically filled in, when the pilot enters the IDENT for
a company route. When the pilot manually enters a city pair, the MCDU
displays “NOT IN DATA BASE” if the city pair is not in the navigation
database. If the city pair is in the database, the CO RTE field displays the
first route stored (small blue font). If more than one route is stored, the
pilot can slew to see the different routes.
STORED ROUTE PAGE
This page displays up to 5 routes, stored by the pilot. The stored routes are listed and numbered in
the order of insertion. The number is displayed in the upper right-hand corner of the page.
[ 1L ] CO RTE
This field identifies the stored route. Clearing this field deletes the stored
route.
Line 2 to Line 5
The fields in these lines are identical to the corresponding fields in the
route page.
[ 6L ] DELETE ALL
Pressing this key changes the label to amber CONFIRM DELETE ALL.
Pressing this key a second time deletes all previously-stored routes.
[ 1R ] FROM/TO
This identifies the city pair of the stored route.
[ 6R ] NEW ROUTE Pressing this key calls up the new route page.
NEW ROUTE PAGE
The pilot calls up this page by pressing the NEW ROUTE key on the stored route page. It can be
used to store up to five new routes that have already been defined in the active or secondary flight
plan.
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FCOM
← AA →
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 1L ] CO RTE
This field enables the pilot to enter a new company route IDENT . If that
IDENT has already been assigned, the entry is rejected.
[ 2L ] STORE ACTIVE Pressing this key stores parameters of the active flight plan as new route.
F-PLN (blue)
The display shows this prompt when the system contains a FROM/TO, but
only during preflight.
[ 3L ] STORE
Pressing this key stores parameters of the secondary flight plan as
SECONDARY F-PLN new route. The display shows this prompt when the system contains a
(blue)
FROM/TO and the secondary flight plan has not yet been sequenced.
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← AA →
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Note:
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
‐ If it has not already been named, a stored route is automatically named when stored:
SRTE 1 to SRTE 5.
‐ When 5 routes are already stored, the pilot cannot insert a new stored route. The
“STORED ROUTE FULL” message is displayed, and the pilot must manually delete a
route in order to store a new one.
‐ Several flight plan elements are not retained when the route is stored:
‐ Pilot-entered holds
‐ Offset
‐ Pilot-entered constraints
‐ Modifications to terminal procedures
‐ Pseudo-waypoints
‐ Step at optimum.
‐ Pilot-entered constant Mach segment.
The MCDU then displays “REVISIONS NOT STORED”.
AIRCRAFT STATUS PAGE
Ident.: DSC-22_20-50-10-25-00000581.0001001 / 28 APR 14
Applicable to: ALL
The system automatically displays this page at power up, but the pilot may also call it up by pressing
the DATA key on the MCDU console.
TITLE
[ 1L ] ENGINE TYPE
Note:
AIRCRAFT TYPE
The system uses this to calculate predictions.
When the same performance database is used for various aircraft configurations, the
aircraft type displayed may differ from the actual aircraft.
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← AA to AB →
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[ 2L ] ACTIVE
DATABASE
[ 3L ] SECOND
DATABASE
CAUTION
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The validity period and part number are displayed in large font.
The validity period is displayed in small font. The pilot can press the 3L key
to switch to the second database as the active database.
Cycling the database erases the primary and secondary flight plans, as well as the
stored data. The flight crew must never do this in flight.
[ 5L ] CHG CODE
[ 6L ] IDLE/PERF
This field allows the entry of a code to change the IDLE and/or PERF factor,
displayed in 6L. It is displayed in the PREFLIGHT and DONE phases. The
label is displayed in small white font. The brackets, or the entered value, is
displayed in large blue font.
It is only possible to modify these factors when the aircraft is on ground. If
no value was entered, the FMS displays default values coded in the Airline
Modifiable Information (AMI) file.
Default values are displayed in small font, although manually entered values
are displayed in large font.
When it is necessary to modify the IDLE or the PERF factor:
‐ ENTER the change code in the CHG CODE field [5L].
The default value for this code is “ARM” but it is possible to modify it on
airline request (the applicable code is then coded in the Airline Modifiable
Information (AMI) file).
When a valid change code is entered, the IDLE and PERF factors are
displayed in blue.
‐ ENTER the new IDLE and/or PERF factor(s) in the scratchpad.
‐ PRESS the [6L] key to insert the new IDLE and/or PERF factor(s).
The new IDLE and/or PERF factor(s) is (are) displayed in large blue font.
[4R] STORED
This field displays pilot-stored data in a large green font. The field is blank,
if no data is stored. (The airline can choose to have this data automatically
erased at the done phase).
[5R] DELETE ALL
Pressing this key changes the label to amber CONFIRM DELETE ALL.
Pressing this key a second time deletes all pilot-stored data, except data that
is part of the active and secondary flight plans.
[6R] STATUS/XLOAD This prompt gives access to the P/N STATUS and P/N XLOAD pages.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AB
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
P/N XLOAD PAGE
Ident.: DSC-22_20-50-10-25-00000582.0001001 / 17 MAR 11
Applicable to: ALL
This page allows the crossloading of all databases or configuration files part numbers which are
different between both sides. Crossloading from this page avoids reviewing each individual P/N
STATUS page.
TITLE
[1L]
[4L]
Line 5
[5L]
[6L] PREV PAGE
[6R] NEXT PAGE
P/N XLOAD
FMS 1 UPDATE: FMS 1 can be loaded on the right side MCDU.
FMS 2 UPDATE: FMS 2 can be loaded on the left side MCDU
START XLOAD: This blue prompt is displayed, only if the system detects a
difference between both sides' part numbers.
FMS 1/FMS 2 IDENTICAL: Displayed in green, when there is no difference
between both sides' part numbers.
FM 1 TO FM 2 or FM 2 TO FM 1: Indicates the crossloading direction. This
line is not displayed when there is no difference between both side part
numbers.
A/C STATUS: This white prompt is displayed, when there is no crossloading
in process. It gives access to the A/C STATUS page.
MM: SS MIN REMAINING: Indicates the time remaining for crossload
completion, when a crossload is in process.
The pilot presses this key to return to the A/C STATUS page.
Pressing this key calls up the next P/N XLOAD page.
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
P/N STATUS PAGES
Ident.: DSC-22_20-50-10-25-00000583.0001001 / 01 OCT 12
Applicable to: ALL
These pages allow reviewing and crossloading the following databases and configuration files
between both FMS:
‐ Page 2
FMS SOFTWARE part numbers
‐ Page 3
NAV DATA BASE part numbers
‐ Page 4
FM AIRLINE CONFIG part numbers
‐ Page 5
FM OPTIONS CONFIG part numbers
‐ Page 6
PERF DATA BASE part numbers
‐ Page 7
FLIGHT TEST DATA BASE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AD →
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FLIGHT CREW
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
TITLE
Line 1 ELEMENT
P/N STATUS
Indicates the name of the database or configuration file that can be
crossloaded:
‐ FMS SOFTWARE on Page 2
‐ NAV DATA BASE on Page 3
‐ FM AIRLINE CONFIG on Page 4
‐ FM OPTIONS CONFIG on Page 5
‐ PERF DATA BASE on Page 6
‐ FLIGHT TEST DATABASE on Page 7.
Line 2 FMS1 P/N Line 3 These fields display the part numbers of the database or configuration file
FMS2 P/N
(stated on line 1), that are installed on the FMS 1 and 2.
Identical part numbers are displayed in green, different ones in amber.
During crossload, the updated part number is replaced by the amber
“ACCEPTING XLOAD” message.
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← AD →
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Line 4
[5L] A/C STATUS
[6L] PREV PAGE
ABORT
[6R] NEXT PAGE
CONFIRM*
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This line is empty when the active flight phase is not Preflight or Done.
XLOAD FMx TO FMy or START XLOAD FMx TO FMy: This blue prompt is
displayed when the database or configuration file (stated on line 1) can be
crossloaded.
XLOAD ARMED: Displayed in blue on the receiving FM when the crossload
has been requested, but not yet confirmed.
XLOAD IN PROCESS: Displayed in white when the crossload is ongoing.
XLOAD NOT SUPPORTED: Crossloading is unavailable for this element.
NO P/N TO XLOAD: The element is missing.
NEED FG 1/FG 2 IDENTICAL TO XLOAD: The receiving side's FG software
is incompatible with the FG software to be crossloaded.
NEED FM 1/FM 2 SOFTWARE IDENTICAL TO XLOAD: The crossloaded
element is incompatible with the receiving side's FM software.
This prompt is available, when no crossload is in process. This gives the
pilot access to the aircraft status page.
MM: SS MIN REMAINING: Displays the time remaining to complete the
crossload, when a crossload is in process.
This key calls up the previous P/N STATUS page.
This amber prompt is displayed when a crossload is in process. The pilot
uses it to stop the crossload.
This key calls up the next P/N STATUS page.
This amber prompt is displayed when a crossload has been armed. The pilot
presses it to start the crossload.
DUPLICATE NAMES PAGE
Ident.: DSC-22_20-50-10-25-00000584.0001001 / 01 OCT 12
Applicable to: ALL
This page, which automatically appears, allows the pilot to select a specific waypoint, airport, or
NAVAID when the database holds more than one under the same identifier.
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← AD to AE →
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The pilot presses the key adjacent to a waypoint, NAVAID, or airport to select it as the one to be
entered. When the pilot has finished, the page automatically reverts to the previously displayed page.
DISTANCE
The direct distance to the aircraft is displayed in green above each name. If this distance is greater
than 9 999 NM, 9 999 NM is displayed.
LAT /LONG COLUMN
This column lists the rounded off latitudes and longitudes of the different points, using the same
identifier.
FREQ/CHAN COLUMN
This column lists the NAVAID s frequencies, if any. It displays CHAN for a MLS.
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Note:
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
‐ The DUPLICATE NAMES page is not displayed when 2 waypoints with the same
IDENT belong to the same airway. The system selects the first waypoint found in the
database.
‐ The waypoints or NAVAIDs are ranked by their distance from the aircraft position.
‐ When a waypoint is named using ICAO phonetic alpha characters, a minus sign and
the ICAO code of the country where the waypoint is located, are displayed. e.g. Alpha
in France becomes A-LF; Bravo in England becomes B-EG.
POSITION MONITOR PAGE
Ident.: DSC-22_20-50-10-25-00000585.0001001 / 17 MAR 11
Applicable to: ALL
This page displays all the different positions that the FMGC has computed with the various available
methods of navigation. It also shows which method obtained each position. (The positions should be
almost identical).
The pilot calls up this page by pressing the 1L key on the data index page.
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← AE to AF →
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
POSITION MONITOR AND POSITION FROZEN PAGE
Ident.: DSC-22_20-50-10-25-00009133.0001001 / 29 MAR 12
Applicable to: ALL
Line 1 FMGC 1
This line shows the latitude and longitude, as calculated by the FMGC 1, and
the navigation method used by the FMGC for that calculation (Example: “3
IRS /DME /DME”).
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← AF to AG →
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Line 2 FMGC 2
This line shows the latitude and longitude, as calculated by the FMGC 2, and
the navigation method used.
Line 3 RADIO or GPS This line shows the latitude and longitude, calculated by the onside FMGC
or GPIRS
from selected radio NAVAID s (Example: DME /DME , VOR /DME , or LOC )
or from GPS or GPIRS.
Line 4 MIX IRS
This line shows the latitude and longitude of the weighted mean inertial
reference system (IRS ) calculated by the onside FMGC from the available
IRSs.
Line 5 IRS 1,2,3
This line shows the deviation in nautical miles of each IRS position from the
onside FMGC position. It also displays the IRS mode, which can be INVAL,
ALIGN, NAV or ATT.
Note:
INVAL is displayed when an ADIRS has failed, or the IRS position
is not refreshed.
[ 6L ]
The pilot presses this key to freeze (or unfreeze) all the data displayed on
FREEZE/UNFREEZE the page. When the data is frozen, the title of the page specifies the time at
which it was frozen.
[ 6R ] SEL NAVAIDS The pilot presses this key to access the selected NAVAIDs page.
SELECTED NAVAIDS PAGE
Ident.: DSC-22_20-50-10-25-00000586.0014001 / 03 APR 13
Applicable to: ALL
MODIFIABLE ONLY FOR DESELECTION
Line 1
This field displays the NAVAID tuned for display purposes, and the tuning
mode (AUTO, MAN , or RMP).
Line 2 and 3
These fields display the NAVAID s, if any, tuned for the calculation of radio
position by the FMGC.
[ 4L ]
This field displays the tuned ILS, GLS , MLS , if any.
[ 5L ]
The flight crew presses this key to manually select or deselect the
DESELECT/SELECT NAVAIDs.
RADIONAV
If the flight crew selects (deselects) the NAVAID s for position calculation,
“RADIONAV SELECTED” (“RADIONAV DESELECTED”) is displayed in
the label line in blue small font and “DESELECT” (“SELECT”) is displayed
in white large font. By default NAVAIDs are selected.
The deselection of the RADIONAV inhibits use of radio position (either
DME /DME or VOR /DME) for position calculation.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AG to AH →
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
The crew presses this key to manually select or deselect the GPS for
[ 6L ]
DESELECT/SELECT position computation. Upon transition to the DONE phase, the prompt
returns to DESELECT status.
GPS
If the pilot deselects the GPS , “GPS IS DESELECTED” is displayed when
the aircraft is less than 80 NM from the top of descent, or in approach
phase.
[ 1R ] DESELECT to The pilot deselects a NAVAID by entering its identifier in one of these
[ 4R ]
six fields. Once deselected in this way, the NAVAID can no longer be
tuned manually through the entry of its IDENT, nor can it be autotuned for
display or determination of the position for the rest of the flight.
The deselection is cleared:
‐ Manually, by a CLR action into this field, or
‐ Automatically upon transition to the done or preflight phase, or upon
activation of the second database.
The pilot may deselect as many as four stations.
[ 6R ] RETURN
The pilot presses this key to return to the POSITION MONITOR page.
IRS MONITOR PAGE
Ident.: DSC-22_20-50-10-25-00000587.0010001 / 01 OCT 12
Applicable to: ALL
This page displays the IRS data. The crew calls up this page by pressing the IRS monitor prompt of
the DATA INDEX page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AH to AI →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
TITLE DRIFT AT XXXX Displays “DRIFT AT” runway identifier, if at least one IRS average drift is
(amber)
displayed.
[1L] to [3L] IRS 1(2) (3) These prompts allow access to the associated IRS pages. Each label line
(white)
displays the mode (NAV , ALIGN, ATT or INVAL), the average drift (upon
transition to DONE phase), and the Time To NAV (if IRS in align) for each
IRS.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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← AI →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[1R] to [3R]
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Displays the status message of the associated IRS in small green font.
List of available messages:
IR FAULT
CHECK C/B
DELAYED MAINT
CDU FAULT
ENTER PPOS
ENTER HEADING
SELECT ATT
REENTER PPOS
EXCESS MOTION
SYS BELOW -15 °
SWITCH ADR
[5R] SET HDG (white) This field is displayed, if at least one IRS is in ATT mode.
This function allows initialization of a heading for IRS in ATT mode:
‐ If a heading has been entered in this field, or on the ADIRS panel, the
value is displayed in blue.
‐ If not, amber boxes are displayed.
IRS 1 (2)(3) PAGE
This page displays the IRS parameters and GPS /IRS hybrid parameters. The pilot calls up this
page by pressing either the 1L key from the IRS MONITOR page, or the NEXT IRS prompt on
another IRS page (closed loop).
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← AI →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
TITLE
Displays the selected IRS in large white font.
When data is frozen, IRS is replaced by “IRS FROZEN AT”, followed by
the time at which the pilot has frozen the display.
[1L] POSITION
Displays the latitude/longitude given by the selected IRS.
[2L] TTRK
True track
[3L] THDG
True heading
[4L] WIND
True wind direction/velocity
[5L] GPIRS
GPS /IRS hybrid position of the IRS
[6L]
Allows the crew to freeze or unfreeze all data displayed on all three IRS
FREEZE/UNFREEZE pages. When the data is frozen, the title of the page specifies the time at
which it was frozen. It is automatically unfrozen when exiting the page.
[2R] GS
Ground speed
[3R] MHDG
Magnetic heading
[4R] GPIRS ACCUR GPS /IRS Figure of Merit (meters or feet)
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← AI →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[6R] NEXT IRS
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This prompt enables another IRS page (closed loop IRS 1 → 2 → 3 → 1)
to be displayed.
GPS MONITOR PAGE
Ident.: DSC-22_20-50-10-25-00000588.0001001 / 17 MAR 11
Applicable to: ALL
This page displays the GPS data. The pilot calls up this page by pressing the GPS MONITOR
prompt of the DATA INDEX page.
Line 1 and 4 GPS 1,2
[ 2L ] and [ 5L ] TTRK
[ 3L ] and [ 6L ] MERIT
[ 2R ] and [ 5R ] GS
[ 3R ] and [ 6R ]
MODE/SAT
[ 2 ] and [ 5 ] UTC :
[ 3 ] and [ 6 ] GPS :
ALT
POSITION
GPS 1, 2 true track
GPS 1, 2 figure of merit (meters or feet)
GPS 1, 2 ground speed
GPS 1, 2 mode (INIT , ACQ, NAV, TEST, FAULT, AIDED or ALTAID) and
Number of satellites tracked.
INIT
: System initialization
ACQ
: Satellite acquisition
NAV
: Normal mode
TEST
: System test
FAULT
: Invalid system
ALTAID/AIDED : Degraded modes. GPS uses aircraft inputs for
computation purposes.
GPS 1, 2 UTC
GPS altitude is displayed for information purposes. It is not used by the
FMGS.
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← AI to AJ
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
CLOSEST AIRPORTS PAGES
Ident.: DSC-22_20-50-10-25-00000589.0001001 / 17 MAR 11
Applicable to: ALL
The system automatically selects the closest 4 airports from the current aircraft position, and displays
them on these pages. A fifth one can be selected by the pilot.
Page 1 displays the bearing, distance, and time to go to each airport; page 2 displays the EFOB and
allows the crew to enter an effective wind to be flown to each airport.
The flight crew accesses the CLOSEST AIRPORTS page 1 by pressing the 5L key from the DATA
INDEX A page. They access the CLOSEST AIRPORTS page 2 by pressing the EFOB/WIND prompt
(6R key) on page 1.
[1L] - [1R] to [4L] - [4R] The closest four airports are extracted from the database, and ranked by
distance from the aircraft position.
BRG
Displays the current bearing from the aircraft's position
to the airport.
DIST
Displays the current great-circle distance from the
aircraft's position to the airport.
TIME or UTC
Displays the predicted time to the airport, computed
using the current wind or a wind vector entered on
page 2, and the speed according to the current mode
(managed or selected).
The time is only computed in cruise phase.
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FCOM
AK →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[5L]
The crew may enter a fifth airport here, using the 4-letter code. The entry
may be modified at any time, even when “LIST FROZEN” is displayed.
If the pilot enters an airport that is not in the database, then “NOT IN DATABASE” appears in the
scratchpad.
[1L] - [1R] EFOB to [5L] Displays the EFOB at each airport. EFOB is only computed in cruise phase.
- [5R] EFF WIND
Used to enter an anticipated headwind or tailwind along the bearing to the
airport. If the entry is preceded by +, T, or TL, a tailwind is assumed.
If the entry is preceded by -, H, or HD, a headwind is assumed.
Before pilot entry, a default value may be displayed, based on the current
wind.
The effective wind is used to compute the EFOB and time to the airport.
[6L]
This prompt enables the pilot to freeze and unfreeze the list of four airports.
FREEZE/UNFREEZE The list is automatically frozen when accessing page 2. It will remain frozen
upon returning to page 1.
The “LIST FROZEN” message is always displayed on page 2.
RETURN
Returns to page 1.
[6R] EFOB/WIND
Gives access to page 2.
Pressing this prompt automatically freezes the list of the four closest
airports.
Note:
‐ If the aircraft position becomes invalid, all fields are dashed, FREEZE/UNFREEZE and
EFOB /WIND prompts are removed, LIST FROZEN is displayed, and the A/C POSITION
INVALID message is displayed in the scratchpad. Page 2 cannot be accessed.
‐ Predictions (EFOB, TIME) displayed on the page assume:
• ECON CRZ speed (managed) or current selected speed (selected)
• CI (for managed speed only) and CRZ FL from primary F-PLN are kept
• constant wind value
• In case of engine out, the aircraft altitude is the minimum of (CRZ FL , EO MAX ALT)
• Downpath steps are not considered
• Descent fuel burn is a conservative value which only depends on the difference
between current CRZ ALT and destination altitude.
EQUI-TIME POINT PAGE
Ident.: DSC-22_20-50-10-25-00000590.0001001 / 18 DEC 12
Applicable to: ALL
The pilot uses this page to require an equitime point computation between two different points
(airport, NAVAID , runway, NDB or waypoint). This pseudo-waypoint (ETP ) is displayed on the
navigation display along the F-PLN. The EQUI-TIME POINT page is accessed by pressing the 6L
key from the DATA INDEX page:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AK to AL →
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[1L] A/C TO and (blue) [3L] Displays reference waypoint 1.
Displays reference waypoint 2.
Note:
Origin and destination airports are used by default for respective reference points 1 and 2,
until a pilot entry is made.
[1R] BRG/DIST/UTC and
[3R] (green)
Displays the bearing, distance, time, from the aircraft’s current position
to the reference waypoint 1.
Displays the bearing, distance, time, from the current position of the
aircraft to the reference waypoint 2.
BRG :
DIST :
UTC :
[2L] and [4L] TRU WIND
(blue)
Displays the current great-circle bearing from the position
of the aircraft to the reference waypoint.
Displays the current great-circle distance from the position
of the aircraft to the reference waypoint.
Displays the predicted time of arrival at the reference
waypoint (computed using the current wind or a wind
vector, entered by the crew).
The time is only computed in cruise phase. In other
phases, it is dashed.
The pilot may enter the wind (direction/velocity) at the reference
waypoint and the CRZ FL:
This wind is used to compute the time from the aircraft's position to the
reference waypoint, and to locate the equitime point.
If no entry is made, the wind/velocity field will read zero.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AL →
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[2R] and [4R] EPT TO XXX This field displays the bearing distance and the time from the equitime
(green)
point position (ETP) to the reference waypoint.
[5R] ETP LOCATION
This field displays the ident of the next waypoint following the equitime
point. It provides the distance along the flight plan from the equitime
point to the indicated waypoint.
[6L] - [6R] A/C TO (ETP)
This field displays the distance and time from the aircraft's current
DIST/UTC (green)
position to the equitime point along the flight plan.
If at least one reference waypoint exists, but no equitime point exists,
the field is blank and NO ETP is displayed in 6L.
Note:
The assumptions for the equitime point computation include the cost index, speed managed
(with SPD LIM), and winds.
In case of engine-out, the EO LRC speed is considered.
PRINT FUNCTION PAGES
Ident.: DSC-22_20-50-10-25-00000591.0001001 / 01 OCT 12
Applicable to: ALL
The PRINT FUNCTION pages enable the crew to print the data relative to the current flight.
This data comes from 2 different sources:
‐ ACARS uplink messages, and
‐ Active data from the current flight.
The pilot may access these pages from the “DATA INDEX” page1/2 by pressing the [6R]
ACARS/PRINT FUNCTION key.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AL to AM →
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
PRINT FUNCTION PAGE 1/2
This page displays the status of the automatic printing capabilities, for the uplink messages (left
column), and the status of the manual printing capabilities of the current active data (right column).
LEFT COLUMN
AUTO
* YES (blue)
* NO (blue)
NO (without a star)
Blank
Line 1:
Uplink messages related to flight plan INIT data are automatically
printed when received.
Line 2:
Uplink messages related to takeoff data are automatically printed
when received.
Line 3:
Uplink messages related to wind data are automatically printed
when received.
When “NO”, preceded by a star, is displayed in front of a line, automatic printing
is deselected. The pilot can reactivate it by pressing the left key of the line.
Automatic printing is internally deactivated for the data of the line. The pilot
cannot reactivate it manually.
The ACARS function is not available for this line. Uplink messages can neither
be received nor automatically printed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AM →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
RIGHT COLUMN
MANUAL
PRINT * (amber)
Displays the status of the manual printing capability of the active data (and not of
the ACARS uplink data).
Pressing the right keys prints the following active data:
Line 1:
Active flight plan INIT data
Line 2:
Active takeoff data
Line 3:
Active wind data
If the star is not displayed, printing is not possible.
When the key is pressed, the star is removed until the data is printed.
[6L] RETURN
[6R] ACARS FUNCTION
Pressing this key reverts the display to the DATA INDEX page.
Pressing this key reverts the display to the ACARS FUNCTION
page.
PRINT FUNCTION PAGE 2/2
This page describes the printing capabilities of the reports displayed on lines 1 to 4.
LEFT COLUMN
AUTO (white)
* YES (blue)
* NO (blue)
NO (without a star)
Line 1:
Line 2:
Line 3:
The PREFLIGHT report is automatically printed at engine start.
The INFLIGHT report is automatically printed at takeoff.
The POSTFLIGHT report is automatically printed at engine
shutdown.
The report, displayed on the line, is not printed automatically. The pilot can
reactivate the function by pressing the left key of the line.
Automatic printing is internally deactivated for the report. The pilot cannot
reactivate it.
RIGHT COLUMN
MANUAL
PRINT *
Pressing a right key prints the report displayed on the line.
If the star is not displayed, printing is not possible.
When the key is pressed, the star is removed until the report is printed.
For the PREFLIGHT, INFLIGHT and POSTFLIGHT reports, only one type of
report is available for printing at any given time, depending on the current flight
phase.
For the SEC F-PLN report, the print selection start is only displayed if a
secondary flight plan exists.
ACARS FUNCTION PAGE
Ident.: DSC-22_20-50-10-25-00000592.0001001 / 01 OCT 12
Applicable to: ALL
The ACARS FUNCTION pages display the functions enabling the crew to send manual requests or
reports to the ground.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AM to AN →
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
All functions, displayed on pages 1 and 2, may be inhibited through a pin program.
The ACARS /PRINT FUNCTION prompt is displayed on the DATA INDEX page 1/2. Pressing
this key displays the PRINT FUNCTION page from which the ACARS FUNCTION page can be
accessed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AN →
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
ACARS FUNCTION PAGE 1
Ident.: DSC-22_20-50-10-25-00000593.0001001 / 17 MAR 11
Applicable to: ALL
TITLE
ACARS FUNCTION 1/2 in white
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AN to AO →
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Line 1 F-PLN INIT REQ* Pressing this key sends a request for flight plan to the ground (downlink
message)
The INIT REQUEST prompt of the INIT A page provides the same
function.
Line 2 TO DATA REQ* Pressing this key sends a request for takeoff data.
Displayed in the DONE and PREFLIGHT phases.
The TO DATA REQUEST prompt of the UPLINK TO DATA REQ page
provides the same function.
Line 3 WIND DATA REQ* Pressing this key sends a request for wind data.
The WIND REQUEST prompt of the CLIMB, CRUISE, and DESCENT
WIND pages provides the same function.
Note:
If “REQ” is not followed by a star, the request cannot be sent (downlink message).
When a function (line 1 or 2 or 3) is deactivated internally, the corresponding line is blank.
[6L] RETURN
The pilot presses this key to make the display revert to the DATA INDEX
page.
[6R] PRINT FUNCTION The pilot presses this key to access the PRINT FUNCTION page. (Refer to
DSC-22_20-50-10-25 Print Function Pages).
UPLINK TO DATA REQ PAGES
Ident.: DSC-22_20-50-10-25-00000594.0009001 / 14 MAY 12
Applicable to: ALL
This page allows the flight crew to send a request for takeoff data for up to 2 runways. There is one
page for each runway. The page is accessed from the PERF TAKEOFF page, or from the UPLINK
XXX (MAX or DRT or FLX) TO DATA page, by pressing the UPLINK TO DATA prompt.
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← AO to AP →
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
TITLE
[ 1L ] TOW/TOCG
(green)
White.
This field is dashed, until a runway is defined in the [ 1R ] field.
The TOW /TOCG is defaulted to the values of the INIT B and FUEL PRED
pages. If not available, dashes are displayed.
It cannot be modified by the pilot.
[ 2L ] TEMP/QNH or This field is dashed, until a runway is defined in the [ 1R ] field. It displays
QFE (green/blue)
the temperature at origin and baro setting.
TEMP = If the temperature is not defined, blue brackets are displayed, and
the flight crew can modify this field according to the weather information.
BARO = Defaulted to FCU selection and can be modified by the pilot.
[ 3L ] MAG WIND (blue) This field is dashed, until a runway is defined in the [ 1R ] field. It displays
the wind at the origin.
If the wind is not defined, blue brackets are displayed.
The pilot can modify this field.
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← AP →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 4L ] CONTAM (blue) This field is dashed, until a runway is defined in the [ 1R ] field. The display
is defaulted to DRY.
The scroll keys allow the crew to modify the runway contamination.
DRY, WET, 1/4 WATER, 1/2 WATER, 1/4 SLUSH, 1/2 SLUSH, COMP
SNOW.
[ 6L ] RECEIVED TO This field calls up the UPLINK MAX (or FLX or DRT) TO DATA page that
DATA
displays the data received by AOC.
[ 1R ] SHIFT/RWY
(blue)
This field is dashed, until a runway is defined in the F-PLN . If a runway is
defined in the F-PLN, it is automatically filled in as:
SHIFT
= Value from the PERF TO page, or blue brackets [ ], if no
value is defined.
RWY
= F-PLN departure runway. The pilot can modify this field.
[ 2R ] TO LIMIT (blue) It is dashed, until a runway is defined in the [ 1R ] field.
It displays blue brackets [ ], when a runway is defined.
The pilot may enter a length, considering runway obstacles.
[ 3R ] FLAPS/THS
This field is dashed, until a runway is defined in the [ 1R ] field; it is then
(blue)
defaulted to values from the PERF TO page. Blue brackets are displayed, if
the PERF TO page does not have any defined values.
[ 4R ] FLEX TO TEMP This field is dashed, until a runway is defined in the [ 1R ] field; it is then
(blue)
defaulted to values from the PERF TO page. Blue brackets are displayed, if
the PERF TO page does not have any defined values.
The pilot can modify this field and enter a FLEX TO temperature (FXX).
[ 6R ] TO DATA
Pressing the key sends the takeoff data request message to the ground.
REQUEST* (amber) The asterisk disappears when the request is sent. It reappears when the
data is available.
Page 2/2 is a page used for requesting a second runway data.
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← AP →
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FLIGHT CREW
OPERATING MANUAL
Note:
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
If the UPLINK TO DATA REQ Page 2 is accessed (Page 1 being filled), the fields of this
page are filled with default values after entry of a runway in [ 1R ]. QNH or QFE and wind
are common with Page 1.
UPLINK MAX TO DATA PAGES
Ident.: DSC-22_20-50-10-25-00000595.0010001 / 01 OCT 12
Applicable to: ALL
This page is accessed from the UPLINK TO DATA REQ page by pressing the RECEIVED TO DATA
key.
There is a set of 2 pages (MAX TO DATA and FLEX TO DATA) for each of the 4 uplinked runway
data. Uplinked data is displayed in green. (It cannot be modified by the flight crew).
[1L] TOW/TOCG
Uplinked reference Takeoff Gross Weight and Takeoff Center of Gravity.
[2L] TEMP/QNH (or
Uplinked assumed temperature and BARO setting.
QFE)
[3L] MAG WIND
Uplinked takeoff runway wind.
[4L] CONTAM
Uplinked takeoff runway contamination.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[5L] THR RED/ACC
Uplinked Thrust Reduction and Acceleration altitudes.
[6L] UPLINK TO DATA Pressing the key calls up the UPLINK TO DATA REQ page.
V1, VR, V2
Uplinked takeoff speeds.
[1R] SHIFT/RWY
Uplinked TO runway IDENT, runway intersection and position shift.
[2R] TO LIMIT
Uplinked runway length remaining.
[3R] FLAPS/THS
Uplinked FLAPS/SLATS CONF and TRIM position.
[4R] FLEX TO
Pressing this key calls up the UPLINK FLEX TO DATA pages.
[5R] ENG OUT ACC Uplinked engine-out acceleration altitude.
[ 6R ] INSERT UPLINK* Uplinked takeoff data is available for insertion.
Selecting this prompt inserts the following data on the PERF TO page:
‐ V1 , VR , V2
‐ THR RED/ACC, ENG OUT ACC altitudes
‐ FLAPS/THS
‐ SHIFT
‐ FLEX
The display reverts to the PERF TO page, the asterisk disappears.
This field is not displayed, if the runway does not match the active runway.
If the runway matches the active runway but the uplinked TOW differs from
the current TOW (the uplinked TOW is 3 t greater or 1 t lower than the TOW
estimated by the FMS):
‐ The asterisk disappears and the insertion is not possible
‐ The TOW value is displayed in amber in [1L] field.
Note:
All previously-received data is replaced by the new uplinked data.
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FCOM
← AQ
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
UPLINK FLX TO DATA PAGES
Ident.: DSC-22_20-50-10-25-00000596.0001001 / 23 JUN 15
Applicable to: ALL
TITLE
[2L]
[4R] MAX TO
UPLINK FLX TO DATA.
FLX/QNH (or QFE)
When the UPLINK FLEX TO DATA page is selected, it displays uplink
assumed Flex Temperature and BARO setting (QNH or QFE).
Pressing this key calls up the MAX TO DATA page.
For all other fields, Refer to DSC-22_20-50-10-25 Uplink MAX TO Data
Pages
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AR
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
ACARS FUNCTION PAGE 2
Ident.: DSC-22_20-50-10-25-00000597.0001001 / 17 MAR 11
Applicable to: ALL
Line 1 F-PLN RPT
Pressing this key sends the flight plan report to the ground.
SEND
Line 2 POSITION RPT Pressing this key sends a Position Report to the ground.
SEND
Note:
‐ No report can be sent, if “SEND” is not followed by a star
‐ When a function (line 1 or 2) is deactivated through the navigation database policy file,
the corresponding line is blank.
[6L] RETURN
The pilot presses this key to revert to the DATA INDEX page.
[6R] PRINT FUNCTION The pilot presses this key to access the PRINT FUNCTION page.
PERF PAGE
Ident.: DSC-22_20-50-10-25-00000598.0001001 / 17 MAR 11
Applicable to: ALL
The flight plan is divided into the following phases:
PREFLIGHT, TAKEOFF, CLIMB, CRUISE, DESCENT, APPROACH, GO-AROUND, DONE.
Each phase, except for the preflight and done phases, has a performance (PERF ) page. The PERF
pages display performance data, speeds related to the various phases, and predictions.
Pressing the PERF key on the MCDU console calls up the performance page for the current active
phase. Performance pages, relating to phases already flown, are not available.
In the preflight and done phases, pressing the PERF key brings up the takeoff performance page.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Pressing the PERF key in the done phase makes the phase transition to the preflight phase.
The FMGS flight phases are not related to the FWC flight phases.
Line 6
Fields may display two different prompts, depending upon whether the
phase is active or not.
[6L] PREV PHASE
To review the performance page for the previous phase.
The prompt is unavailable on the takeoff performance page. It is also
unavailable for phases already flown.
[6L] ACTIVATE APPR To activate, then confirm, the APPR phase. Available only on the page
PHASE
corresponding to the active phase.
[6R] NEXT PHASE
To review the performance page for the next phase.
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FLIGHT CREW
OPERATING MANUAL
Note:
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Engine-out condition
‐ When the FMGS detects an engine-out condition, the system automatically calls up
the performance page for the current flight phase (except when this occurs before the
diversion point during takeoff or no EOSID exists in the flight plan) and displays “EO CLR
*” in the [1R] field and EO LRC (engine-out long range cruise) in the [2L] field. On the
CLB , CRZ and DES (when the descent phase is not active) PERF pages, the pilot can
enter a cost index value and overwrite to “EO LRC”. Clearing the cost index reverts to
EO LRC.
If the pilot presses the [1R] key, the system reverts to the normal processing (with no
engine failed) and suppresses the EO information. (Refer to DSC-22_20-30-10-15
General).
‐ If the engine-out condition is detected before the diversion point at takeoff, a temporary
flight plan is created.
PERF TAKEOFF PAGE
Ident.: DSC-22_20-50-10-25-00000599.0010001 / 08 JUL 15
Applicable to: ALL
During the preflight phase, the pilot presses the PERF key to call up the takeoff performance page.
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FCOM
← AT to AU →
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OPERATING MANUAL
TITLE
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
TAKE OFF RWY is in large green font when the takeoff phase is active, and
in large white font when it is inactive. The active flight plan selected runway
is displayed in large green font.
Note:
If the takeoff shift, or the flaps/THS , or the runway is changed after
V1 , VR or V2 insertion, but the origin airport remains the same,
the MCDU “CHECK TAKE OFF DATA” message appears. All
takeoff parameters are retained except in case of runway change.
In case of runway change, the parameters are invalidated, but
still displayed adjacent to each field. The “CONFIRM TO DATA”
prompt in [6R] allows reverting to the previous values.
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FCOM
← AU →
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
[1L] V1 [2L] VR [3L] V2 The boxes remain amber, as long as the pilot does not make entries in them.
The pilot can modify any entry, as long as the takeoff phase is not active.
Note:
[4L] TRANS ALT
(transion altitude)
[5L] THR RED (thrust
reduction altitude)
ACC (Acceleration
altitude)
1. If the flight crew does not enter V2 , the SRS mode will be
unavailable at takeoff.
2. The MCDU “V1 /VR /V2 DISAGREE” amber message appears if
the inserted V1 , VR , V2 speeds do not satisfy the condition: V1
≤ VR ≤ V2.
3. The MCDU “TO SPEED TOO LOW” amber message appears
if the inserted V1 , VR , V2 speeds do not satisfy the existing
regulatory conditions regarding VMCG /VMCA and VS1G
speeds.
This field displays the navigation database default altitude (if defined) once
the origin airport is entered. The pilot can modify it.
This is the altitude at which the pilot should reduce the thrust from TOGA
/FLX to MAX CLIMB (CL detent) with all engines operative (“CLB ” or “LVR
CLB ” flashing on the FMA).
‐ The thrust reduction altitude defaults to 1 500 ft above the runway
elevation, or to the altitude set by the airline
‐ The pilot can modify this altitude: The minimum is 400 ft above the runway
elevation.
This is the altitude at which the climb phase is triggered.
‐ The target speed jumps to the initial climb speed
‐ The default value is 1 500 ft above runway elevation
‐ The flight crew can modify the value. The minimum value is 400 ft above
runway elevation, and it can be higher than, or equal to, or lower than
THR RED.
Note:
‐ A clearing action reverts both values to the defaulted ones
‐ When the flight crew selects an altitude on the FCU that is
below THR RED, it brings THR RED and ACC down to this
altitude. (The 400 ft minimum still applies).
[6L] UPLINK TO DATA This key calls up the UPLINK TO DATA REQ page.
It is only displayed in the preflight and done phases.
[1R] EO CLR
EO CLR is displayed when an engine-out is detected and when active flight
phase is takeoff.
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FCOM
← AU →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[2R] TO SHIFT
The takeoff shift is the distance in meters or feet between the beginning
of the runway and the aircraft's takeoff position. When taking off from an
intersection, the flight crew should insert this value to ensure a correct
update of the FM position. The takeoff shift value must be positive, and
cannot be greater than the runway length.
[3R] FLAPS/THS
This is a flight crew entry for the positions of the flaps and the trimmable
horizontal stabilizer (THS) at takeoff.
The flight crew can modify it until takeoff, by entering “UP X.X” or “X.X UP”,
or “DN X.X” or “X.X DN ” for the THS.
[4R] FLX TO TEMP
The flight crew inserts the FLX TO temperature for FLX takeoff setting
purposes. The flight crew can only enter it during preflight.
The system sends it to the FADEC and displays the entered data on the
upper ECAM display. The TEMP value is always entered in degrees Celsius.
[5R] ENG OUT ACC This field displays the engine-out acceleration altitude, as defined in the
database, or is manually entered by the flight crew. This is for display only,
as a reminder. It cannot be cleared. The above ACC altitude rules of [5L]
apply to this field.
[6R] NEXT PAGE or This key calls up the climb performance page, or allows the flight crew to
CONFIRM TO DATA* revert to the previously-entered T.O. parameters, in case of runway change
with the same origin airport.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AU
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
PERF CLIMB PAGE
Ident.: DSC-22_20-50-10-25-00000600.0001001 / 14 MAY 12
Applicable to: ALL
TITLE
[1L] ACT MODE
[2L] CI (Cost Index)
[3L] MANAGED
CLB is displayed in large white fonts when the climb phase is inactive, and in
large green fonts if it is active.
This field displays the preselected or active speed mode: SELECTED or
MANAGED.
The pilot cannot modify it from this field.
This field displays the cost index, as initialized on the INIT A or defaulted
from the database, or inserted in this field by the pilot. EO LRC automatically
replaces the cost index value in case of engine-out.
This field displays the FMGS computed ECON speed/Mach (Refer to
DSC-22_20-40-10 Optimization).
Before CLIMB phase is active, if the preselected speed mode is SELECTED,
a star is displayed next to the MANAGED speed. Pressing the 3L key in this
case preselects MANAGED speed, and 4L reverts to brackets.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[4L] PRESEL or
SELECTED
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
If the climb phase is not active:
This field displays PRESEL as long as the climb phase is not active.
The pilot can enter a preselected speed only.
If the climb phase is active:
The title of this field becomes SELECTED.
This field displays the selected (or preselected) SPD or MACH target.
The pilot cannot modify it directly in this field, but can adjust it with the
SPD /MACH selection knob on the FCU.
If the pilot pushes in the FCU SPD /MACH selection knob to revert to
managed speed, the system selects (or reselects) ECON SPD/MACH
and [4L] is blank.
[5L] Blank or
EXPEDITE
This field is blank as long as the aircraft is in preflight.
This field displays this legend when the takeoff or climb phase is active. The
flight crew cannot engage EXPEDITE from this field.
It indicates the time and distance required to reach the altitude displayed in
the 2R field, in case of climb at green dot.
[6L] PREV PHASE
This field displays this legend if climb phase is not active. The pilot presses
this key to call up the takeoff page.
[6L] ACTIVATE APPR The field displays this legend if the climb phase is active.
PHASE
Pressing this key once displays “CONFIRM APPR PHASE*”. Pressing it
again activates the approach phase.
[1R] EO CLR
The system displays the EO CLR prompt in case of engine out in climb.
[2R] PRED TO...
This field displays the target altitude for the predictions shown in 3R, 4R, or
5L. It defaults to FCU altitude, but the pilot can modify it to any altitude below
CRZ FL.
[3R] [4R] [5R]
These fields show time and distance predictions for the target altitude
selected in [2R], computed for the current vertical mode and speed mode
(MANAGED, SELECTED).
These fields are displayed only while the takeoff, or climb phase is active.
[6R] NEXT PHASE
The flight crew presses this key to call up the PERF CRZ page.
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FCOM
← AV
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
PERF CRUISE PAGE
Ident.: DSC-22_20-50-10-25-00000601.0009001 / 30 MAR 15
Applicable to: ALL
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FCOM
AW →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TITLE
[1L] ACT MODE
[2L] CI
[3L] MANAGED
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
CRZ in white large font, when cruise phase is not active, in green large font,
when it is.
This field shows the preselected or active speed mode: SELECTED or
MANAGED.
The pilot cannot modify it through this field.
This field shows the cost index as initialized on the INIT A page or defaulted
from the database, or as inserted in this field by the crew.
EO LRC replaces automatically the cost index value in case of engine out.
This field displays the FMGS computed ECON speed/Mach (Refer to
DSC-22_20-40-10 Optimization).
Before CRUISE phase is active, if the preselected speed mode is
SELECTED, a star is displayed next to the MANAGED speed. Pressing the
3L key in this case preselects MANAGED speed, and 4L reverts to brackets.
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← AW →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[4L] PRESEL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
If cruise phase is not active:
The pilot can enter a preselected speed or Mach number.
If cruise phase is active:
This field is blank.
Note:
If the flight crew enters a value in the PRESEL field during the
cruise altitude capture (ALT CRZ*), the FCU selected speed may
revert to M 0.01.
[6L] PREV PHASE or
The pilot can press this key to call up the climb page, if the cruise phase is
not yet active.
[6L] ACTIVATE APPR This field displays this legend if the cruise phase is active. The flight crew
PHASE
presses the key once to change the legend to “CONFIRM APPR PHASE*”.
A second press activates the approach phase.
Note:
If the pilot activates the approach phase inadvertently, it can
reselect the cruise flight level into the progress page to reactivate
the cruise phase.
[ 1R ] TIME/UTC DES Before takeoff this field displays the flight time to destination and the
EFOB
predicted remaining fuel on board. If the crew enters an estimated takeoff
time, the field displays automatically the predicted arrival time (UTC ) at
destination. After takeoff it displays the predicted arrival time at destination
(UTC ) and the remaining fuel on board (DEST EFOB ) at destination,
in green font. The DEST EFOB field will turn to amber, if the EFOB at
destination becomes less than the MIN DEST FOB value displayed on the
FUEL PRED page. EO CLR is displayed when an engine-out is detected.
[2R] STEP TO FL XX, The field, in combination with 3R, displays the predictions for the step point
DRIFT DOWN TO FL and the step altitude, the drift down altitude, or the Top of Descent.
XX, or TO T/D
[3R] TIME/UTC and
This field displays the time and distance to go to the various points identified
DIST
in 2R.
[4R] DES CABIN RATE This field displays MAX [computed DES cabin rate, maximum descent cabin
rate]. The pilot may modify the value: the FM recomputes then the top of
descent in order to match this value. If the FM cannot match the pilot entry,
the FM computed value overwrites the pilot entry.
A clear action reverts to the default value (-350 ft/min). DES CAB RATE
being a negative value, 'minus” is not a necessary entry.
[5R] STEP ALTS
This key calls up the STEP ALTS page (vertical revision Refer to
DSC-22_20-50-10-25 VERTICAL REVISION Pages).
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[6R] NEXT PHASE
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This key calls up the DES page.
PERF DESCENT PAGE
Ident.: DSC-22_20-50-10-25-00000602.0011001 / 23 JUN 15
Applicable to: ALL
TITLE
[1L] ACT MODE
[2L] CI
DES is in large white font if the descent phase is not active; it is in large
green font, if it is.
This field displays the preselected or active speed mode (MANAGED or
SELECTED). The flight crew cannot modify it through this field.
This field displays the cost index, as initialized on the INIT A page or
defaulted from the database, or inserted in this field by the flight crew. The
flight crew cannot modify it when the descent phase is active.
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← AW to AX →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[3L] MANAGED
[4L] blank or
SELECTED
[5L] Blank or
EXPEDITE
[6L] PREV PHASE
or ACTIVATE APPR
PHASE
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
If the descent phase is not active:
Before the flight crew makes any entry. This field displays MANAGED
in white, with the associated ECON descent Mach or speed in blue. The
crew may overwrite the ECON descent Mach or speed by entering a
Mach number or a speed in this field. The system uses the pilot entry to
compute the descent profile. The descent may be flown in managed using
this new pilot entry.
The entry is modifiable. It can be cleared to revert to ECON speed/Mach.
If the descent phase is active:
The flight crew cannot make an entry in this field.
The field displays the ECON speed/Mach or the speed/Mach value
previously entered by the pilot.
If the descent phase is not active, or the descent phase is active but the
active speed mode is MANAGED:
This field is blank.
If the descent phase is active and the active speed mode is SELECTED:
The field displays the speed or Mach target manually selected by the pilot.
“SELECTED” is displayed in the [1L] field.
To modify the field value, the pilot will use the SPD /MACH selector knob
of the FCU . [4L] field and FCU window will display the same value.
Pushing in the FCU speed selector knob activates the managed
SPD/MACH target displayed in the [3L] field.
If the descent phase is not active this field is blank.
Displays this legend if the descent phase is active.
It indicates the time and distance required to reach the altitude displayed in
the 2R field at MMO /VMO speed. The pilot cannot select the EXPEDITE
mode through this field.
This key calls up the cruise phase page if the descent phase is not yet
active.
Displayed if the descent phase is active. First press causes “CONFIRM
APPR PHASE” to be displayed. Second press activates the approach
phase.
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← AX →
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[ 1R ] TIME/UTC DEST Before takeoff, this field displays the flight time to destination and the
EFOB
predicted remaining fuel on board. If the crew enters an estimated takeoff
time, the field displays automatically the predicted arrival time (UTC).
After takeoff, it displays the predicted arrival time at destination (UTC ) and
the remaining fuel on board (DEST EFOB ) at destination in green font. The
DEST EFOB field will turn to amber, if the EFOB at destination becomes
less than the MIN DEST FOB value displayed on the FUEL PRED page. EO
CLR is displayed when an engine-out is detected.
[2R] PRED TO...
This field displays the target altitude for the predictions in [3R] [4R], or [5R].
The display defaults to the altitude selected on the FCU. The flight crew can
modify it to any altitude lower than present altitude.
[3R] [4R] [5R]
These fields display time and distance predictions down to the target altitude
selected in [2R], computed for the current vertical mode (DES or OP DES)
and the indicated speed mode (MANAGED, SELECTED).
[6R] NEXT PHASE
The pilot presses this key to call up the PERF APPR page.
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
PERF APPR PAGE
Ident.: DSC-22_20-50-10-25-00016132.0010001 / 24 FEB 15
Applicable to: ALL
PERF APPR Page
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
PERF APPR Page (with BARO/RADIO option)
APPR is in large white font, if the approach phase is not active; it is in large green font, if it is.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[1L] QNH
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This field displays brackets, when the aircraft is more than 180 NM from the
destination. Inside 180 NM, a mandatory amber box appears. The flight crew
must enter the QNH in hPa or in inches of mercury.
‐ For hPa, enter three or four digits
‐ For inches of mercury:
• Enter two digits, or
• Enter two digits followed by a decimal point and two additional digits.
The system interprets:
‐ 1 003 as 1 003 hPa;
‐ 29 as 29.00 in.
‐ 29.92 as 29.92 in.
Note:
[2L] TEMP
[3L] MAG WIND
[4L] TRANS ALT
[5L] VAPP
The flight crew can modify this entry at any time.
The Cabin Pressure Controller (CPC) uses the QNH to compute the cabin
repressurization segment. Therefore, an erroneous QNH entry may result in
a cabin pressurization that is not appropriate.
This field displays the temperature at destination. The field displays brackets
until the pilot enters the temperature. The pilot can modify this figure.
The system uses this temperature to refine its computation of the descent
profile (ISA model).
The flight crew enters the magnetic wind in knots at the destination in
this field. The system transmits any entry made in this field to the vertical
revision and flight plan B pages (which display wind direction as true, not
magnetic).
This field displays the transition altitude taken from the data base (small font)
or entered by the flight crew (large font).
The flight crew can modify it at any time.
The FMGC computes this approach speed, using the formula:
VAPP = VLS + 1/3 of the headwind components (limited to VLS + 5 as a
minimum and VLS + 15 as a maximum).
The flight crew can modify VAPP . A clear action reverts VAPP to the
computed value.
Note:
[6L] PREV PAGE
An erroneous entry of an OAT in QNH field, for example 22 °C, or
a higher value, is accepted by the system.
VLS = 1.23 VS1G of the selected landing configuration (full or 3).
This field displays this legend if the approach phase is not active.
Pressing this key calls up the descent performance page.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[1R] FINAL
[2R] MDA/MDH or
BARO
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This field displays the approach specified in the flight plan.
The flight crew cannot modify it through this field.
This field displays:
‐ The Minimum Descent Altitude with associated brackets, or
‐ The Minimum Descent Height with associated brackets, if:
‐ The QFE pin program is activated, or
‐ The FCU setting is QFE, on aircraft equipped with the BARO
option.
The flight crew inserts the value, which it can modify at any time. If the flight
crew makes an entry in [3R] or changes the approach, it clears this figure.
[3R] DH or RADIO If the flight plan includes an ILS approach, this field displays “DH " or
"RADIO" and empty brackets. The flight crew inserts the decision
height. The system will accept an entry of “NO", "NODH" or "NO DH". If the
flight crew inserts an MDA or an MDH (or a BARO value) in FIELD [2R],
this erases the decision height, and this field reverts to brackets. The DH or
RADIO range is 0 to 700 ft.
[4R] LDG CONF CONF The flight crew can select configuration 3 by pressing the 4R key.
3
This moves the * down to the [5R] field, which is displaying “FULL"?.
[5R] FULL
The flight crew can use this key to select configuration FULL when
necessary configuration FULL is the default landing configuration.
[6R] NEXT PHASE
Pressing this key calls up the go-around performance page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AY
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OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
PERF GO AROUND PAGE
Ident.: DSC-22_20-50-10-25-00000604.0002001 / 01 OCT 12
Applicable to: ALL
TITLE
GO AROUND is in large white font, if the go-around phase is not active; it is
in large green font, if it is.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AZ →
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[5L] THR RED ACC
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This field displays the thrust reduction altitude and the acceleration altitude.
Thrust reduction altitude:
‐ Altitude at which thrust must be reduced from takeoff/go-around thrust to
maximum climb thrust
‐ “CLB ” or “LVR CLB” flashing on flight mode annunciator
‐ Defaults to 1 500 ft above destination runway elevation, or to the altitude
set by the airline
‐ Can be modified by the crew (minimum 400 ft above destination runway
elevation).
Acceleration altitude:
‐ Altitude at which target speed jumps to green-dot speed (see the note
below)
‐ Defaults to 1 500 ft above destination runway elevation, or to the altitude
set by the airline.
‐ Can be modified by the crew, but is always equal to (or higher than) the
thrust reduction altitude.
[6L] PREV PHASE or This field displays this legend if the go-around phase is not active.
Pressing the key calls up the PERF APPR page.
ACTIVATE APPR
This field displays this legend if the go-around phase is active.
PHASE
Pressing it once makes “CONFIRM APPR” appear.
A second press activates the approach phase.
[5R] ENG OUT ACC This display has the same characteristics as the display beside the 5R key
on the takeoff page. It is for display only, and the pilot can modify it.
[6R] NEXT PHASE
Pressing this key calls up the PERF APPR page.
[IR] Blank or EO CLR* This field is normally blank.
EO CLR* is displayed when GO AROUND is the active phase and an
engine-out condition is detected.
Note:
When the go-around phase is active, if the pilot enables ALTN or if the pilot inserts a new
destination in the active flight plan and a new cruise flight level on the progress page, the
go-around phase shifts automatically into the climb phase. (The target speed jumps from
green dot speed to initial climb speed).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AZ
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OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
PROG PAGES
Ident.: DSC-22_20-50-10-25-00000605.0051001 / 22 MAR 17
Applicable to: ALL
The progress page is a multifunction page that enables the pilot to:
‐ Select a new cruise flight level
‐ Crosscheck the navigation accuracy of the Flight Management (FM) system and validate it
‐ Update the FM position
‐ Monitor the descent.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
BA →
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FLIGHT CREW
OPERATING MANUAL
TITLE
Line 1 CRZ (blue)
OPT
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Different for each flight phase (see above). The vertical phase is in large
green font. The flight number is in large white font. EO is large amber font, if
the engine-out condition is detected.
This line displays the cruise flight level, inserted on the INIT A page or
directly in this field in blue. If the flight crew uses the FCU to select an
altitude that is higher than the one displayed in this field, the system
changes the number displayed to agree. In this line, the flight crew cannot
insert a flight level that is lower than the FCU-selected altitude.
This field shows dashes when the descent or approach phase is active.
This field displays the optimum flight level (in green), that is computed based
on the current gross weight, cost index, temperature and wind. This flight
level requires a 5 min minimum cruise at a minimum cruise flight level of
FL 100.
It displays dashes if an engine-out is detected.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← BA →
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OPERATING MANUAL
REC MAX
[2L] REPORT
[2R] VDEV
Line 3 POSITION
UPDATE AT
Note:
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This field displays the recommended maximum altitude (in magenta),
that is computed based on the current gross weight and temperature,
and assuming that the anti-ice is off (if icing conditions are expected,
Refer to QRH/PER-M Optimum & Maximum Altitudes (Paper Only) or the
performance application of FlySmart with Airbus). It provides the aircraft with
a 0.3 g buffet margin, a minimum rate of climb at MAX CL thrust, and level
flight at MAX CRZ thrust. This field is limited to FL 398.
If one engine is out, this field displays the recommended maximum
engine-out altitude, that is computed based on the long-range cruise speed
and assuming that anti-ice is off.
This key calls up the REPORT PAGE.
This field is displayed during the descent and approach phases, when NAV
mode is engaged, or in HDG mode, provided that the crosstrack error (XTK
) is less than 5 NM. It displays the vertical deviation between the aircraft's
current altitude and the FMS-computed vertical profile.
The flight crew can update the FMS position via this field by entering either
the IDENT of a waypoint, a NAVAID , an airport, a latitude and longitude
(LL), a place/bearing/distance, or a place-bearing/place-bearing (PBX).
When the flight crew has entered this data, this field changes its format to:
“CONFIRM UPDATE AT”, followed by the latitude/longitude and IDENT of
the inserted position with an asterisk.
The flight crew presses the right-hand key adjacent to the asterisk to confirm
the update, when the aircraft overflies the inserted position.
If no IDENT has been inserted, the field displays “ENTRY” instead of an IDENT.
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FCOM
← BA →
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OPERATING MANUAL
Line 4 BRG/DIST
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
On this line, the pilot can enter an airport, a waypoint, a NAVAID , or a
runway. The pilot may enter each as an IDENT , a latitude/longitude (LL ), a
place/bearing/distance (PBD), or a place-bearing/place-bearing (PBX). The
field then shows the FMGC -computed bearing and distance from this site to
the aircraft's present position. The last distance digit is in 1/10 of a NM. If it
does not have an IDENT, the point is called “ENTRY”.
Example:
BRG /DIST
340 °/95.4 to ENTRY
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FCOM
← BA →
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OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[5L] PREDICTIVE GPS This prompt gives access to the PREDICTIVE GPS page.
[5R] GPS PRIMARY This prompt is displayed, when the FMS navigation mode is GPS PRIMARY.
When GPS PRIMARY is not available, or navigation mode is not GPS /IRS,
this field is blank.
The scratchpad displays the relevant “GPS PRIMARY″ message when this
prompt appears; and “GPS PRIMARY LOST”, when the field turns to blank.
[6L] REQUIRED
This field displays the default value for the required navigation accuracy
level. The pilot can modify it. Provided no pilot entry has been made, the
default value changes according to the actual flight area (En route, terminal,
approach).
ACCUR HIGH/LOW
This field shows the flight management system's estimate of the navigational
accuracy. “HIGH” indicates that the FMS estimates that the navigational
accuracy matches the accuracy criteria of the area currently flown. “LOW”
indicates that the criteria are not matched.
[6R] ESTIMATED
This field displays the current estimated navigation accuracy value (EPE) as
computed by the FMS.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← BA
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OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
PREDICTIVE GPS PAGES
Ident.: DSC-22_20-50-10-25-00009139.0001001 / 31 AUG 17
Applicable to: ALL
Note:
1. This page is only operative with Honeywell ADIRS.
2. This page cannot be used as a substitute to determine pre-flight planning RAIM
availability when required by operational regulations. Refer to PRO-NOR-SOP-02 GPS
PRIMARY Availability (If Installed).
The pilot accesses this page by pressing the PREDICTIVE GPS prompt of the PROG page.
This page displays information relative to theoretical predictive availability of GPS PRIMARY at
destination, and at any waypoint selected by the crew.
[1L] DEST
[1R] ETA
Destination, airport as currently selected in active flight plan. It is not
modifiable. This field displays dashes, when no destination airport exists.
This field is defaulted to the Estimated Arrival Time, as computed by the
FMS (small blue font). The pilot may enter a value in this field (large blue
font). Amber boxes are displayed, when no prediction exists, or the crew
entry has been cleared.
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FCOM
BB →
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OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Line 2 PRIMARY Y/N
Predicted primary status at destination airport, at the following times:
Estimated time of arrival ±5, 10, 15 min.
Availability of GPS PRIMARY at the corresponding time is indicated by
Y, when PRIMARY is predicted to be available; and, by N, when GPS
PRIMARY is predicted not to be available.
These fields are blanked when the destination [1L] field, or the time [1R] field
is not defined.
[3L] WPT
The pilot may enter a reference waypoint in this field. Blue brackets are
displayed, when no entry has been made.
[3R] ETA
When a reference waypoint has been entered in the [3L] field, amber boxes
are displayed.
The crew is requested to enter a reference time in this field.
Line 4 PRIMARY Y/N Information equivalent to [2L] / [2R] is displayed for any pilot-selected
waypoint. The corresponding time of arrival is also displayed.
Line 5 DESELECTED Enables the pilot to deselect up to four satellites by inserting the
SATELLITES and Line corresponding satellite number ; the number is then displayed in large blue
6 SATELLITES
font. When deactivated, the satellites are not considered for predictive GPS
availability at destination, or at the selected waypoint. The deselection is
cancelled when the entry is cleared (blue brackets are displayed), or the field
is overwritten by a different satellite number.
REPORT PAGE
Ident.: DSC-22_20-50-10-25-00000606.0009001 / 14 MAY 12
Applicable to: ALL
The pilot calls this page by pressing the [2L] key on the PROG page:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← BB to BC →
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OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This page displays information related to the FROM, TO , NEXT and DEST waypoints, as well as the
current wind, temperature, distance and time to the next cruise profile change.
TITLE (White)
Displays the flight number. This line displays EO in amber, in case an
engine-out is detected.
[1L] OVHD (green)
Displays the last sequenced waypoint. This field never displays the
pseudo-waypoints and the F-PLN markers (T-P , PPOS, IN-BND,
OUT-BND).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← BC →
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OPERATING MANUAL
[1R] UTC/TIME ALT
(green)
[2L]-[2R] TO (green)
This field displays the time and altitude recorded at the time of sequence.
This field displays the active waypoint, predicted time of arrival and predicted
altitude at this waypoint.
Note:
[3L]-[3R] NEXT (green)
[4L] [4R]
SAT/T.WIND/FOB
(green)
[5L] T/D/UTC/DIST
(green)
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Time and altitude values are identical to those values on the F-PLN
pages.
Same information for the next waypoint.
This field displays the static air temperature, the wind direction and velocity,
and the FOB recorded at waypoint sequencing.
This field displays the estimated time, and the distance to go to the next
change of the cruise profile (T/D , S/C , S/D). These data are only displayed
when the cruise phase is active.
[5R] SEND* (blue)
The crew uses this prompt to downlink a position report.
This field may be blank, depending on airline policy.
Line 6
This field displays the estimated time of arrival, the distance along the F-PLN
DEST/UTC/DIST/EFOB , and the estimated fuel on board (DEST EFOB) at destination.
The DEST EFOB field will turn to amber, if the EFOB at destination becomes
less than the MIN DEST FOB value displayed on the FUEL PRED page..
This display is identical to the information on the F-PLN pages.
Note:
No data can be inserted or modified on the REPORT page.
RADIO NAV PAGE
Ident.: DSC-22_20-50-10-25-00000607.0009001 / 06 APR 16
Applicable to: ALL
This page enables the pilot to select or verify the radio NAVAIDs, tuned for display purposes only.
These NAVAID s include: VOR , VOR /DME , TAC , VORTAC, ILS , and ADF.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← BC to BD →
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05 SEP 17
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FLIGHT CREW
OPERATING MANUAL
Line 1 VOR1/FREQ
FREQ/VOR2
Line 2 CRS
[3L] LS/FREQ
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
This line displays the identifiers and frequencies of VORs 1 and 2, whether
they are automatically or manually tuned.
To manually tune a VOR , the pilot inserts the IDENT or frequency. If the
IDENT is not in the database, the new NAVAID page comes up. A “clear”
action reverts the selection to the autotuned NAVAID.
This line displays courses for the NAVAIDs in Line 1.
The pilot can manually enter the courses through these fields.
This field displays the IDENT of an ILS and its frequency (for ILS ). It is
autotuned, if the ILS is associated to the departure runway, or if the flight
plan contains an ILS approach. The flight crew may also enter an ILS
manually. When the manually entered ILS differs from the ILS that the FMS
would autotune, “RWY-LS MISMATCH” appears.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← BD →
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FLIGHT CREW
OPERATING MANUAL
[4L] CRS SLOPE
CRS : This field displays the course associated with the LS displayed in
Line 3. It comes up automatically if an LS is autotuned, or if an LS has
been manually tuned via its IDENT. Otherwise, the course must be entered
manually. The course may be backbeam (Bxxx) or frontbeam (Fxxx)..
SLOPE: This field displays the slope associated with the LS displayed in
Line 3. It comes up automatically if an LS is autotuned for approach, or if an
LS has been manually tuned via its IDENT.
Note:
Line 5 ADF1/FREQ
FREQ/ADF2
Line 6 ADF1/BFO
BFO/ADF2
Note:
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
1. The slope does not apply to LOC only, LDA, SDF or Backbeam
approaches.
2. If the flight crew intends to manually tune an ILS that is not in the
navigation database or to manually tune an ILS by its frequency
(ident not entered), and if they do not enter the course, the flight
crew will not be able to arm approach modes.
This line displays the identifiers and frequencies of ADFs 1 and 2.
The pilot can use the IDENT or the frequency to manually tune the ADF.
When an ADF is selected, these fields display an ADF /BFO prompt. The
flight crew presses the key once to erase the arrow and put the ADF in BFO
mode. A clear action brings the arrow back and cancels BFO.
‐ The autotune function only works for NAVAIDs stored in the database.
‐ When tuning manually, the operator should use the IDENT , rather than the frequency,
unless the NAVAID is not in the database.
‐ Manually-tuned frequencies are displayed in large font.
SECONDARY PAGES
Ident.: DSC-22_20-50-10-25-00000608.0009001 / 13 FEB 13
Applicable to: ALL
The SEC F-PLN key on the MCDU console allows the flight crew to call up the secondary index
page and the secondary flight plan page. The secondary flight plan is generally for a diversion, for
predictable runway changes for takeoff or landing, or for training.
There are two types of secondary index pages. The type selected depends on the presence of a
secondary flight plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← BD to BE →
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
SECONDARY INDEX PAGE
A SECONDARY FLIGHT PLAN IS ALREADY DEFINED
[1L] COPY ACTIVE
(blue)
[2L] SEC F-PLN
(white)
[3L] DELETE SEC
(blue)
[4L] ACTIVATE SEC
(amber)
Note:
The flight crew presses this key to copy the active flight plan into the
secondary flight plan and delete the previous secondary plan.
The flight crew presses this key to call up the secondary flight plan
pages.
The flight crew presses this key to delete the current secondary flight
plan.
The flight crew presses this key to activate the secondary flight plan as
the active flight plan.
“ACTIVATE SEC ” routinely appears if the HDG /TRK mode is active. If the NAV mode
is active, “ACTIVATE SEC” appears only if the active and secondary flight plans have
a common active leg.
[ 1R ] INIT (white)
[2R] PERF (white)
The flight crew presses this key to call up the SEC INIT A page.
The flight crew presses this key to call up the performance pages for the
secondary flight plan.
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FCOM
← BE →
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
A SECONDARY FLIGHT PLAN IS NOT DEFINED
[1L] COPY ACTIVE
(blue)
[2L] SEC F-PLN
(white)
[1R] INIT (white)
The pilot presses this key to copy the primary active flight plan into the
secondary flight plan.
The pilot presses this key to call up the secondary flight plan pages.
The pilot presses this key to call up the secondary INIT page.
It is similar to the active INIT page, but blue brackets replace all the
amber boxes.
SECONDARY FLIGHT PLAN PAGES
The secondary flight plan pages A and B are identical to those of the active flight plan, but are
automatically sequenced, only when the secondary is copied from the primary and their active legs
are identical.
The active and secondary flight plans pages differ from each other as follows:
SECONDARY LATERAL REVISION PAGES:
‐ ERASE and INSERT are not displayed.
‐ FIX INFO is not available.
‐ A lateral revision of the secondary flight plan does not create a temporary flight plan:
All revisions are directly applied to the secondary flight plan.
SECONDARY VERTICAL REVISION PAGES:
A vertical revision on the secondary flight plan does not create a temporary flight plan.
SECONDARY INIT A AND B PAGES:
‐ They use blue brackets, instead of amber boxes.
‐ They have no align prompt.
‐ They do not provide for slewing or entering data in the 4L-4R fields (airport reference).
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FCOM
← BE →
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
SECONDARY STEP ALTITUDE PAGES:
These pages operate as the primary STEP ALTS page, except that optimal step, savings are
not available.
SECONDARY WIND PAGES:
They have no history wind page.
SECONDARY PERFORMANCE PAGES:
‐
‐
‐
‐
‐
‐
All boxes are replaced by blue brackets.
They have no engine-out mode, no engine-out long range cruise cost index.
They have no expedite predictions.
They have no ACTIVATE/CONFIRM APPROACH PHASE prompt.
They have no PRED TO ALTN predictions on the PERF CLB and PERF DES pages.
They have no engine-out drift down, no top of descent, no cabin descent rate information on
the PERF CRZ page.
The secondary flight plan has no FUEL PRED page.
SECONDARY INIT A PAGE IS ALSO USED TO REQUEST OR DISPLAY AN UPLINK INIT
MESSAGE RECEIVED AFTER ENGINE START.
This uplink INIT message can be cleared or inserted as SECONDARY INIT data.
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FCOM
← BE →
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OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
[2R] INIT REQUEST* Enable to request init data from the ground or,
[2R] INSERT UPLINK* A downlink message has been received following a request.
The message can be cleared or entered in the SEC INIT page.
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FCOM
← BE
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CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
BACK UP NAV PAGES
Ident.: DSC-22_20-50-10-25-00013508.0019001 / 29 JAN 13
Applicable to: ALL
The MCDU features a back up navigation function which provides simplified point-to-point GPIRS
and IRS based navigation in case of a dual FM failure.
The backup Navigation mode allows limited lateral flight planning within the MCDU , that can be used
to drive the Navigation Display and provides relative path position information and auto-sequencing
of the Backup Navigation flight plan. The Backup Navigation flight plan reflects, as much as possible,
the active primary FM flight plan upon its initial activation.
During FM normal operation, the F-PLN is continuously downloaded in the MCDU memory: the
BACK UP NAV function links the MCDU of the failed FM to its onside IRS . All navigation data
related to the MCDU F-PLN are displayed on the associated ND.
BACK UP NAV function is activated on the MCDU MENU page by pressing the NAV B/UP prompt.
The MCDU back-up F-PLN may accept a maximum of 165 legs, including information such as
waypoint position/identification, leg type, discontinuity, overfly and turn direction information (radial,
pattern, heading leg... cannot be part of the MCDU F-PLN ). No secondary or temporary F-PLN
exists.
BACK UP NAV pages display the data related to the BACK UP NAV function. There are six pages
available while BACK UP NAV is active:
‐ B/UP F-PLN
‐ B/UP F-PLN for DIRECT TO
‐ B/UP PROG
‐ B/UP IRS for onside IRS (1+2)
‐ B/UP IRS 3
‐ B/UP GPS (if the GPS is installed)
B/UP F-PLN PAGE
The B/UP F-PLN page displays the MCDU F-PLN data. The pilot calls up this page by pressing
the F-PLN key while B/UP NAV is active.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
BF →
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OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
TITLE line 1 to line 5
B/UP F-PLN is displayed in a white large font
Display consecutive waypoints with their associated latitude/longitude.
If a waypoint is to be overflown, an overfly symbol (▵) is displayed after
the identifier.
If a turn is specified into the next leg, a large font arrow is displayed after
the identifier.
Label lines contain the bearing, time to go and distance to the next
waypoint displayed in small font.
white bearing
green time to go and distance
BRG Between FROM and TO waypoints: True or Mag depending
on the TRUE pb-sw position. T is displayed when the
bearing is true referenced.
Between other waypoints: out bound true track of the great
circle joining the 2 related waypoints, independant of TRUE
pb-sw .
TTG HHMM limited to 9 959. Time between the 2 related
waypoints.
DIST NM limited to 9 999.
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
line 6 DEST
DEST airport identifier and associated latitude/longitude.
DIST to destination is computed as the direct distance from the aircraft
to the active waypoint plus the along flight plan distances.
time to go to destination is computed as distance to destination divided
by ground speed.
TTG and DEST are dashed if aircraft position is unavailable.
B/UP F-PLN (DIR TO)PAGE
The pilot calls up this page using the DIR key on MCDU while BACK UP NAV is active and aircraft
position is valid.
TITLE [1L] DIR TO
B/UP F-PLN is displayed in a white large font
Allows DIRECT TO selection to the desired waypoint.
This waypoint can be selected from the F-PLN or manually entered
through the scratchpad (IDENT /LAT /LONG or LAT /LONG)
line 2 to line 6
Display consecutive waypoints of the F-PLN.
Same as the B/UP F-PLN page.
The TO WAYPOINT is displayed in [2L].
Vertical slewing function is available.
After a DIR TO selection, the B/UP F-PLN page is modified as following:
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AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
B/UP PROG PAGE
It displays flight parameters relative to the F-PLN or a selected waypoint.
The flight crew calls up this page by pressing the PROG key on MCDU when BACK UP NAV is
active.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
TITLE line 1 OVHD/ALT B/UP PROG is displayed in a white large font.
Displays the identifier of the last sequenced waypoint and the altitude at
the time of the sequence.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
line 2 BRG/DIST/TTG/TOAllows the flight crew to enter an existing MCDU F-PLN waypoint
identifier or LAT /LONG or IDENT /LAT /LONG.
MCDU then computes bearing, distance and time to go to that waypoint
from the present position.
The pilot may modify or clear this entry (2R field).
BRG True or magnetic outbound track of the great circle joining
aircraft present position to the entered waypoint: dependent on
the TRUE pb-sw position.
DIST limited to 9 999.
TTG HHMM limited to 9 959. time to go to the entered position
computed assuming current ground speed.
These fields are displayed in a green small font.
They are dashed if present position is unavailable.
[3L]
Means of navigation used by the Back-Up Navigation. If GPS is fitted
and is the navigation source, “GPS NAV ” is displayed, otherwise “IRS
ONLY NAV” is displayed.
If the GPS is not installed, this field is blank.
[4L] IRS 1 (2 or 3)
Current aircraft position provided by the selected IRS GPIRS
BASED POS GPIRS 1 (2 IRS 1 (or 3 if IRS 1 failed) on MCDU 1
or 3) (green)
IRS 2 (or 3 if IRS 2 failed) on MCDU 2
GPIRS 1 (or GPIRS 3) or MCDU 1
GPIRS 2 (or GPIRS 3) or MCDU 2
[4R] GS (green)
Current ground speed from the selected IRS or GPS .
[5L] DTRK/TRK (green) Desired track of the MCDU F-PLN active leg and current aircraft track
from the selected IRS /GPS (True or Mag).
These tracks are true or magnetic depending on TRUE pb-sw
position.
[6L] IRS 1 (2)
Gives access to onside B/UP IRS (1 or 2) page
[6R] GPS
Gives access to B/UP GPS page.
This prompt only appears when the GPS is installed.
B/UP IRS 1 OR 2 OR 3 PAGE
Display IRS 1, 2, 3 navigation data.
The pilot calls up this page from B/UP PROG page, by pressing the corresponding prompt.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
TITLE
[1L] POSITION
[2L] T TRK
[2R] GS
[3L] T HDG
[3R] M HDG
B/UP IRS 1, 2, 3 displayed in a white large font.
Current aircraft position from selected IRS
True track
Ground speed
True heading
Magnetic heading
Dashed when in polar area.
[4L] WIND
Wind direction and velocity
Wind direction is always true referenced.
[4R] GPIRS ACCUR
GPS accuracy in meters as in the IRS page.
[5R] GPIRS POSITION If GPS is installed, the GPS IRS position is provided as in the IRS page.
[6L] RETURN
Gives access to B/UP PROG page
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Gives access to the next IRS page.
(Closed loop 1 → 2 → 3 → 1)
This page is not modifiable by the crew.
[6R] NEXT IRS
Note:
The fields [4R] and [5L] are blanked when the GPS is not installed.
B/UP GPS
Display GPS navigation data.
The flight crew calls up this page from B/UP PROG page, by pressing the corresponding prompt.
TITLE
[1L]
Line 2:
Line 3:
B/UP GPS 1, 2 displayed in a white large font.
GPS POSITION
TTRK GPIRS position (latitude/longitude)
UTC: Time
GS: Ground Speed
MERIT: GPS figure of merit
GPS ALT : GPS altitude
MODE/SAT: Navigation mode and number of tracked satellites. These
values are displayed as in the FM GPS page.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
[5R]
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
DESELECT/SELECT GPS : The flight crew may select and deselect the
GPS for navigation Backup function. The default configuration is GPS
selected.
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - PAGE DESCRIPTION
Intentionally left blank
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - MESSAGES
FLIGHT CREW
OPERATING MANUAL
FMS2 Honeywell
MCDU MESSAGE LIST
Ident.: DSC-22_20-50-20-35-00000918.0020001 / 03 NOV 14
Applicable to: ALL
Messages displayed on the MCDU are of two types and displayed in two colors.
Type I : A direct result of a pilot action;
Type II : Information about a situation, or a call for pilot action;
Type II messages are stored in a first-in/first-out message queue (5 messages max)
They are suppressed, if correct data is entered or when they no longer apply
The flight crew can clear all messages by pressing the CLEAR key on the MCDU console.
Amber (A) : Important
White (W) : Less important
MESSAGE
A/C POSITION INVALID
TYPE/COLOR
II/A
ACT RTE UPLINK
(ACARS msg)
ALIGN IRS
II/W
AREA RNP IS XX-XX
II/A
AWY /WPT MISMATCH
I/W
BLOCK IGNORES RTA
II/W
CABIN RATE EXCEEDED
II/W
CHECK ALTN WIND
(ACARS msg)
II/W
II/A
GLG A318/A319/A320/A321 For A/C: HC-CRU
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CONDITIONS
The aircraft position has become invalid. If the message has been
cleared and the flight crew attempts to call up the HOLD at PPOS
or DIR TO page while the aircraft position is still invalid, then the
message is displayed again.
A flight plan is stored in the active flight plan.
Appears when the IRS are ready for alignment, but the INIT A
page is not displayed on either side of the flight deck. The ALIGN
IRS message requires that one of the flight crew call up the IRS
INIT page, to align the IRS.
Displayed when the RNP value, manually-entered on the PROG
page, is larger than the default RNP value associated to the
current flight area and when there is no RNP value defined in the
navigation database for the active leg or route.
The pilot entered VIA on the AIRWAYS page does not contain the
revised point. If you enter a second airway IDENT, it must contain
the first airway ending point.
A time constraint existing at initiation of flight planning, or an entry
of a time constraint made after initiation of flight planning, are
ignored by the fuel planning function.
This message appears when the aircraft gets within 200 NM
of the destination and the computed rate of descent makes it
impossible for the cabin to be repressurized at the maximum rate.
The uplinked alternate cruise flight level differs from the defaulted
alternate cruise flight level.
Continued on the following page
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - MESSAGES
FLIGHT CREW
OPERATING MANUAL
MESSAGE
CHECK APPR SELECTION
*EFIS PFD (FMA)
TYPE/COLOR
II/W
CHECK CO RTE
(ACARS msg)
CHECK DATA BASE CYCLE
II/W
CHECK IRS 1(2)(3)/FM
POSITION
CHECK IRS /AIRPORT POS
II/A
CHECK DEST DATA
(ACARS msg)
II/A
CHECK FLT NBR
(ACARS msg)
CHECK MIN DEST FOB
II/A
II/W
I/A
II/W
CHECK NORTH REF
* EFIS ND
II/A
CHECK QFE
II/A
CHECK TAKEOFF DATA
II/A
CHECK WEIGHT
II/A
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Continued from the previous page
CONDITIONS
Displayed when a NON ILS approach is part of the F-PLN and an
ILS is manually tuned on RAD NAV page. This message reminds
the flight crew that available guidance modes for the approach are
APP NAV/FINAL.
Displayed when in cruise at less than 100 NM from the top of
descent or in descent or approach phase.
The uplinked company route identifier differs from the one
specified in the request.
The current date does not match the effective date of the active
database, and someone attempts to enter a FROM/TO or
CO RTE.
Each IRS position is compared to the FM position. The difference
is greater than a threshold function of time.
The distance between ADIRS alignment position and the NAV
Database Airport Reference Point is at least 5 NM
The aircraft is at 180 NM from destination and the destination
QNH , TEMP or WIND displayed on the PERF APPR page
received by ACARS uplink has to be checked.
If a modification of these parameters is performed creating a
conflict with previous data, the message is triggered again.
The uplinked flight number differs from the flight number specified
in the request.
This message appears when the flight crew has manually entered
the MIN DEST FOB value, and MIN DEST FOB < ALTN + FINAL,
being FINAL an ALTN valid data.
The MAG/TRUE sw does not correspond to the airport MAG
/TRUE bearing reference (as stored in the FMGS navigation
database), either at the departure airport (during preflight), or at
the destination airport (when entering the ARRIVAL area).
This appears at the transition from QNH to QFE reference, when
the QFE altitude differs by more than 100 ft from the predicted
altitude, with the QNH set on the MCDU by means of the airport
elevation in the NAV database.
Following a flight crew entry or modification of one of the take-off
parameters, there may be an inconsistency between the take-off
runway or the TO shift and V1 , VR , V2 , FLEX TO temperature
or derated level.
The flight crew activated the secondary F-PLN in PREFLIGHT or
DONE phase.
The gross weights (GW ) computed by the flight management
computer (FMC) and the flight augmentation computer (FAC)
disagree by more than 7 t (7.7 US tons).
Continued on the following page
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - MESSAGES
FLIGHT CREW
OPERATING MANUAL
MESSAGE
CLK IS TAKEOFF TIME
TYPE/COLOR
II/W
CLOCK/GPS TIME DIFF XX
CROSSLOAD ABORTED
II/A
II/W
CROSSLOAD COMPLETE
II/W
CRZ FL ABOVE MAX FL
II/W
CSTR DEL ABOVE CRZ FL
II/W
CSTR DEL UP TO WPT 01
II/W
DECELERATE or T/D
REACHED
(Also displayed on PFD)
DELETING OFFSET
II/W
DEST /ALTN MISMATCH
I/W
DEST EFOB BELOW MIN
II/A
DIR TO IN PROCESS
I/W
ENTER DEST DATA
II/A
ENTRY OUT OF RANGE
I/W
FLT NBR UPLINK
(ACARS msg)
F-PLN ELEMENT RETAINED
II/W
II/W
I/W
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Continued from the previous page
CONDITIONS
This appears when the flight crew has entered an Estimated
Takeoff Time (ETT), and the actual time is equal to ETT.
Aircraft clock time and GPS time differ by more than XX minutes.
Message displayed on the transmitting MCDU, indicating an error
in the transmission process.
The database crossload from one FMGC to the other was
successfully completed.
This appears when the flight crew enters a cruise altitude that is
above the computed maximum altitude.
This appears when a flight plan altitude constraint has been
deleted because the flight crew has inserted a cruise flight level,
or step-down altitude that is at or below the flight plan constraint.
This appears when constraints get deleted because the aircraft
transitions to a go-around flight phase, before the FMGS
sequences the flight plan destination.
One of these messages appears when the aircraft has reached
the T/D in managed speed and it has not yet begun the descent.
This appears when the system is deleting an offset automatically,
which it does under certain specific conditions, such as:
‐ Change of active leg due to lateral revision.
‐ Termination of next leg at destination runway and the current
distance to go is less than or equal to the distance required to
reach the path, or the next leg is not a CF, FM or TF leg.
The pilot attempts to enter an alternate CO RTE (which starts at
an origin that is not the primary flight plan destination).
The EFOB at destination calculated by the FMS is less than the
MIN DEST FOB value specified on the FUEL PRED page, for
more than 2 min. The message is triggered in flight, except during
Takeoff and Climb phases.
The flight crew calls up the vertical or lateral revision page on one
MCDU while the direct to page is displayed on the other MCDU.
The flight crew has not entered wind, QNH, or temperature for the
destination, and the aircraft is 180 NM out.
The flight crew attempts to enter data that is out of the range
specified for the selected field.
A flight number has been added to the uplink flight plan without
previous request.
The flight crew attempts to delete stored NAVAIDs, waypoints
or runways that are contained in any flight plan or that are being
tuned.
Continued on the following page
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - MESSAGES
FLIGHT CREW
OPERATING MANUAL
MESSAGE
F-PLN FULL
TYPE/COLOR
II/W
FMS 1/FMS 2 A/C STS DIFF
II/W
FMS 1/FMS 2 GW DIFF
FMS 1/FMS 2 PGM PIN DIFF
FMS 1/FMS 2 POS DIFF
II/W
II/W
II/A
FMS 1/FMS 2 SPD TGT DIFF
II/W
FORMAT ERROR
I/W
GPS PRIMARY LOST
(also displayed on ND)
GPS PRIMARY
GPS IS DESELECTED
II/A
II/W
II/A
INDEPENDENT OPERATION
INITIALIZE WEIGHT/CG
II/A
II/A
INVALID FLT NBR UPLINK
(ACARS msg)
INVALID PERF UPLINK
(ACARS msg)
INVALID RTE UPLINK
(ACARS msg)
INVALID TAKEOFF UPLINK
(ACARS msg)
INVALID WIND UPLINK
(ACARS msg)
LAT DISCONT AHEAD
II/W
LIST OF 10 IN USE
I/W
Continued from the previous page
CONDITIONS
There is not enough memory in the flight plan allotment for the
computer to accept more flight plan data.
This message always precedes a transition to independent mode,
and appears at power-up if the system detects a difference in one
of the following:
‐ NAV database serial number
‐ Performance database
‐ FM operational program
‐ Aircraft and airline program pins
Onside and offside aircraft weight differ by 2 t or more.
Onside and offside program pins are different.
Onside and offside positions differ by 0.5 NM or more (5 NM
when GPS is not installed).
Onside and offside target speeds displayed on the PFD differ by
5 kt or more.
A data entry does not meet the specified entry format for a given
field.
Displayed when GPS PRIMARY mode is lost.
II/W
Displayed when the FMS is transitioning to GPS PRIMARY
This message appears when GPS has been manually deselected
and the aircraft is 80 NM before the top of descent or in approach
phase.
The FMGCs operate independently of each other.
The zero-fuel weight or block fuel (FOB) is undefined after engine
start.
The uplink message contains a valid flight plan but no flight
number.
Performance uplink message has been rejected.
II/W
An error was detected into the uplink message and it is rejected.
II/W
The current uplink takeoff data message is rejected.
II/W
The current uplink wind message is rejected.
II/A
The next leg is a discontinuity and the aircraft is 30 s from flying
the leg.
The flight crew has tried to enter more than ten stored runways
into the database, and all of the first ten are included in a flight
plan or a pilot-stored route.
Continued on the following page
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - MESSAGES
FLIGHT CREW
OPERATING MANUAL
MESSAGE
LIST OF 20 IN USE
TYPE/COLOR
I/W
MACH SEGMENT DELETED
II/W
MCDU OVERHEATED
MORE DRAG
(EFIS PFD)
II/A
II/W
NAV ACCUR DOWNGRAD
(also displayed on ND)
NAV ACCUR UPGRAD
(*EFIS ND)
NEW ACC ALT-HHHH
NEW CRZ ALT-HHHHH
NEW THR RED ALT-HHHH
NO ANSWER TO REQUEST
(ACARS msg)
NO INTERSECTION FOUND
II/A
II/W
II/W
II/W
II/W
I/W
I/W
NON UNIQUE ROUTE IDENT
I/W
NOT ALLOWED
I/W
NOT ALLOWED IN NAV
I/W
NO NAV INTERCEPT
II/A
NOT IN DATA BASE
I/W
NOT XMITTED TO ACARS
(ACARS msg)
ONLY SPD ENTRY ALLOWED
II/W
I/W
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Continued from the previous page
CONDITIONS
The flight crew has tried to create a PBD, LAT /LONG , or PBX, or
store a pilot-defined waypoint or NAVAID when 20 are already in
use (in a flight plan or pilot-stored routes).
A constant Mach segment of the active flight plan has been
automatically deleted. This occurs when the secondary flight plan
or the alternate is activated, or engine out is detected or when the
flight phase changes from CRZ to another one.
This message is displayed for 15 s in case of MCDU overheating.
DES mode is engaged, idle is selected and the aircraft must
decelerate in order to recover the path, or to respect an altitude
constraint, a speed limit or a speed constraint.
NAV accuracy has been downgraded from HIGH to LOW. (See
FMGS principles for an explanation).
NAV accuracy has been upgraded from LOW to HIGH.
The acceleration altitude has been changed.
The cruise altitude has been changed.
The thrust reduction altitude has been changed.
A crew request, was previously sent to the ground and no answer
has been received for 4 min.
The system could not find any common waypoint nor intersection
point through the airway.
The flight crew has tried to enter on the new route page a
company route IDENT that is identical to an existing company
route IDENT (pilot-defined or in the database).
Data entry is not allowed in the selected field, or a selection action
is not allowed.
An attempt to modify the TO waypoint is made while in NAV
mode.
It is triggered, when NAV mode is armed and, no INTERCEPT
waypoint exists before the TO waypoint.
The pilot is trying to enter or call up a company route IDENT , a
FROM/TO pair, a place defined by place-bearing-distance (PBD)
or place-bearing/place-bearing (PBX) or an airport NAVAID ,
waypoint runway, or NAVAID frequency (including pilot-defined
elements) that is not in the current database.
A pilot request or a crew report was sent but the communication
was not established or not acknowledged.
The pilot is trying to enter a Mach number for a preselected speed
value on the CLIMB page.
Continued on the following page
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - MESSAGES
FLIGHT CREW
OPERATING MANUAL
MESSAGE
OPP FMGC IN PROCESS
TYPE/COLOR
II/W
PAGE UPDATE IN PROCESS
I/W
PERF DATA UPLINK
(ACARS msg)
PLACE/D IN TRANSITION
II/W
PLEASE WAIT
PROCEDURE RNP IS XX.XX
I/W
II/A
PRINTER NOT AVAILABLE
(ACARS msg)
RADIONAV IS DESELECTED
II/W
REF/GPS POS DIFF
I/A
REF/LAST IRS POS DIFF
I/A
REVISIONS NOT STORED
II/W
I/W
II/A
Continued from the previous page
CONDITIONS
The offside FMGC is unhealthy, and the FM system mode is
SINGLE. The message indicates that the MCDU on which the
message is displayed is being driven by the FMGC on the other
side.
The pilot presses a key on the flight plan page while predictions
are being updated.
Performance data are received from ground.
If a place/distance waypoint is defined within a pre-planned “fixed
turn radius” transition, the entry is rejected and the “PLACE/D IN
TRANSITION” scratchpad message is displayed.
Resynchronization between both FMGCs is in progress.
Displayed when the RNP value, manually-entered on the PROG
page, is larger than the RNP value defined in the navigation
database for the active leg or route.
A printer communication error has been detected while printing a
report. The printing is terminated.
Radio navaids have been manually deselected and the aircraft is
80 NM before the top of descent or in approach phase.
This message is displayed when there is a discrepancy between
the reference position entered by the pilot and the GPS position.
This message is displayed when there is a discrepancy between
the reference position entered by the pilot and the last stored IRS
position.
This message, displayed when a pilot-defined route or company
route (active or secondary flight plan) is stored, indicates that the
following elements are not retained:
‐ Pilot-entered holds
‐ Offsets
‐ Modifications to terminal area procedures
‐ Pilot-entered constraints
‐ Pseudo waypoints
‐ Step at optimum.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - MESSAGES
FLIGHT CREW
OPERATING MANUAL
MESSAGE
RTA DELETED
TYPE/COLOR
II/W
Continued from the previous page
CONDITIONS
A time constraint is automatically deleted:
‐ In case of engine-out
‐ When entering the holding pattern
‐ In case of go-around
‐ At phase transition from descent or approach to climb or cruise
‐ When a time constraint is inserted in the same flight plan at a
different waypoint
‐ When the alternate flight plan is activated
‐ When a DIR TO/ABEAM is performed, only if the time
constrained waypoint is projected as an ABEAM waypoint
‐ The time constrained waypoint is cleared or sequenced
(regardless of active lateral mode)
‐ Valid clock data is lost
‐ The time constraint belongs to the active flight plan and the
secondary flight plan is activated
‐ The time constraint belongs to the secondary flight plan and
COPY ACTIVE is performed.
RTA EXISTS
I/W
RTE DATALINK IN PROG
(ACARS msg)
I/W
RWY/LS MISMATCH
II/A
SEC RTE UPLINK
(ACARS msg)
SELECT DESIRED SYSTEM
SELECT TRUE
(also displayed on the ND)
SENSOR IS INVALID
II/W
A flight plan is stored in the secondary flight plan.
I/W
II/A
The MCDU displays its MENU page.
The MAG/TRUE sw is set to MAG , while the IRS send true HDG
/TRK.
I/W
Displayed if the pilot tries to clear an estimated takeoff time
defined by the system.
A flight plan modification is performed after a F-PLN INIT request
has been sent. This message is displayed until the uplink is
entirely received.
‐ During climb, cruise, (ILS or MLS ) descent approach, or
go-around, the LS frequency entered on the RAD NAV page
does not match the LS associated with the destination runway.
‐ During preflight or takeoff, the LS frequency entered on the
RAD NAV page does not match the LS associated with the
takeoff runway.
‐ The pilot has selected FF or FQ, or FF + FQ, or FQ + FF
on the FUEL PRED page and the sole sensor or both of the
selected sensors are invalid, or
‐ The flight crew has entered fuel on board only, and the FF
sensor is invalid.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_20-50-20-35 P 7/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - MESSAGES
FLIGHT CREW
OPERATING MANUAL
MESSAGE
SET GREEN DOT SPEED
("SET GREEN DOT" displayed
on PFD)
TYPE/COLOR
II/W
(W)
SET HOLD SPEED
(also displayed on PFD)
II/W
(W)
SET MANAGED SPEED or
CHECK SPEED MODE
(Also displayed on PFD)
II/W
(W)
SETTING SPD/RTA
II/W
SPECIF NDB UNAVAIL
II/A
SPECIF VOR-D UNAVAIL
(also displayed on ND)
II/A
SPD ERROR AT WPT 01
II/W
SPD LIM EXCEEDED
II/A
STEP ABOVE MAX FL
II/W
STEP AHEAD
STEP DELETED
STORED ROUTES FULL
II/W
II/W
I/W
TAKEOFF DATA UPLINK
(ACARS msg)
II/W
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued from the previous page
CONDITIONS
This message appears when the following conditions are all met:
‐ Engine-out condition
‐ Aircraft in selected speed mode
‐ FCU -selected speed equal to or greater than green-dot speed
+10 kt, and ALT * or ALT not active, or FCU-selected speed
equal to or less than green-dot speed -10 kt.
This instruction appears when the aircraft is in selected speed,
the pilot has inserted a hold in the flight plan, the aircraft is 30 s
or less from the point where it must start decelerating towards
hold speed, and the selected speed differs from the hold speed by
more than 5 kt.
The target speed is selected for the current phase, but there is
no preselected speed for the next flight phase. When this is so,
one of these messages is displayed at transitions from climb
to cruise, and from climb or cruise to descent. The message is
always displayed at the transition to descent from climb or cruise
if selected speed is active. It is not displayed if managed speed is
active.
Displayed when the system recomputes its managed speed target
to satisfy the RTA constraints.
The NDB to be autotuned (specified for a NDB approach) is not
available.
‐ The VOR , VOR -DME , or VORTAC to be autotuned
(specified for an RNAV or VOR approach) has previously been
deselected by the flight crew, or
‐ The bearing, the frequency, or the IDENT of the VOR (or
VORDME or VORTAC) to be autotuned is invalid.
In lateral managed flight, the system predicts that the aircraft will
miss a speed constraint by more than 10 kt. When the prediction
changes to bring the miss within 5 kt, the message is cleared.
The aircraft is more that 150 ft below the speed limit altitude and
more than 10 kt over green dot or the speed limit (which ever is
smaller).
The pilot has entered a step altitude that is above the predicted
maximum altitude.
Indicates that the aircraft is within 20 NM of the active step point.
A step has been automatically deleted.
The system already contains five pilot-defined routes. (Only five
are allowed.)
A takeoff data message is received.
Continued on the following page
←A→
DSC-22_20-50-20-35 P 8/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - MESSAGES
FLIGHT CREW
OPERATING MANUAL
MESSAGE
TEMPORARY F-PLN EXISTS
TYPE/COLOR
I/W
TIME ERROR AT WPT 01
II/W
TIME MARKER LIST FULL
I/W
TIME TO EXIT
II/A
TO SPEED TOO LOW
II/A
TOO STEEP PATH AHEAD
II/A
TUNE BBB FFF.FF
II/A
TURN AREA EXCEEDANCE
II/A
UNKNOWN PROGRAM PIN
II/W
UPLINK INSERT IN PROG
(ACARS msg)
USING COST
INDEX-NNN
II/W
V1 /VR /V2 DISAGREE
II/A
WAIT FOR SYSTEM
RESPONSE
I/W
WIND DATA UPLINK
(ACARS msg)
WIND UPLINK EXISTS
(ACARS msg)
II/W
I/W
I/W
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued from the previous page
CONDITIONS
The flight crew has selected any key (except ERASE or INSERT)
or attempted a flight planning operation on the secondary flight
plan while the system is displaying a temporary flight plan.
While the aircraft is in lateral managed flight the FMGC predicts
that it will miss a time constraint (Refer to DSC-22_20-30-20-25
Required Time of Arrival (RTA) - Entering a Required Time of
Arrival).
The system already contains four time markers. (Only four are
allowed).
The aircraft must leave holding immediately to satisfy fuel reserve
requirements. (Extra fuel is zero).
This message appears if the inserted V1 , VR , V2 speeds do
not satisfy the existing regulatory conditions regarding VMC and
VS1G speeds.
The system displays this message in cruise phase if the aircraft is
within 150 NM of its destination or in descent or approach phase
and in NAV mode and the descent profile contains a segment that
is too steep.
The system cannot autotune the VOR for approach or position
because of a manual VOR selection.
This message is displayed 1.5 min before entry of the PI leg,
when in NAV mode, if the PI lateral path exceed the protection
envelope defined in the Navigation database.
The system has been unable to initialize because of an
incompatible or undefined aircraft pin program combination (A/C
type, engine type, VMO /MMO parity) in the FMGC software.
Displayed when an uplink message is currently inserted in the
FMGS.
This message is displayed when the system contains a flight plan,
and the flight crew tries to enter a zero fuel weight or a gross
weight into it before defining a Cost Index (CI). (In this case, the
FMS defaults to the Cost Index from the last flight).
It is also displayed when the flight crew inserts the ALTN F-PLN
(in this case, the FMS defaults the cost index to 0).
This message is displayed when the entered V1 , VR and V2
speeds do not satisfy the condition V1 ≤ VR ≤ V2.
During the time between a subsystem selection and the display of
the subsystem page, the MCDU MENU page remains displayed
with this message.
Uplink wind message has been received.
A flight plan modification (active or secondary) is attempted when
uplink winds are not inserted yet.
Continued on the following page
←A→
DSC-22_20-50-20-35 P 9/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
CONTROLS AND INDICATORS - MCDU - MESSAGES
FLIGHT CREW
OPERATING MANUAL
MESSAGE
WIND UPLINK PENDING
(ACARS msg)
XXXX IS DESELECTED
TYPE/COLOR
II/A
I/W
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued from the previous page
CONDITIONS
A temporary flight plan exists or a DIR TO page is displayed and
a wind uplink is received and stored.
The flight crew attempts to enter a deselected NAVAID , via the
SELECTED NAVAID page, that has already been deselected.
←A
DSC-22_20-50-20-35 P 10/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MCDU - DATA FORMAT LIST
MCDU DATA FORMAT LIST
Ident.: DSC-22_20-50-30-00000920.0051001 / 21 MAR 16
Applicable to: ALL
The following chart lists all the data the pilot may enter on the MCDU.
It also shows the acceptable format for the various data items, the acceptable range, the units of
entry, and the MCDU pages on which the data can be entered.
The following codes are used to indicate various data formats:
A : letters
N : numbers
X : letters and numbers
DATA NAME
FORMAT
RANGE
(X is input)
UNITS
ACCEL ALT
See ALT
ALT
Max ALT = 39 000
Entry is rounded to the
nearest 10 ft
See ALT
ft (MSL)
ALT CSTR
NNNN or NNNNN
(leading zeros must
be included)
See ALT
AIRWAYS (VIA)
XXXX
N/A
ARPT
AAAA
1 character
minimum.
4 maximum.
If not in data base
"NOT IN DATA BASE"
is displayed
If AAAA is not in the
database airport file,
the New Runway page
is displayed
BARO
Same as ALT
BLOCK FUEL
CG
NN.N leading zeros
may be omitted.
- NNN
(- may be omitted)
NN.N
CHANNEL
NNN
CABIN RATE
Ldg elevation to ldg
elevation + 5000
0-80/0-175.2
DISPLAY PAGE
ft (MSL)
TAKEOFF (ACT/SEC (2))
GO AROUND (ACT/SEC
(2))
PERF CLB
PERF DES
ft (MSL)
VERT REV
F-PLN A
SEC F-PLN A
LAT REV
AIRWAYS
INIT A (ACT/SEC (2) )
LAT REV
ALTN
F-PLN A-B (ACT/SEC (2) )
WAYPOINT
DIR TO
PERF APPR (ACT/SEC(2))
ft (MSL)
100 - 999
Thousands of Kg
or thousands of Lb
ft/min
8.0 - 45.0
% MAC
500 - 699
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
INIT B (ACT/SEC (2))
DES FORECAST or
CRUISE PERF PAGE
INIT B. (ACT/SEC (2))
FUEL PRED
NEW NAVAID
RAD NAV
Continued on the following page
DSC-22_20-50-30 P 1/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATA NAME
CONTROLS AND INDICATORS - MCDU - DATA FORMAT LIST
FORMAT
CLASS (NAVAID) AAAAAA
CO RTE
COST INDEX
CRS
CRZ FL
RANGE
(X is input)
VOR
(refer to RANGE for DME
exact inputs allowed) VORDME
VORTAC
LOC , ILS
NDB
ILSDME
MLS
TACAN
XXXXXXX
If not in the
7 or 10 characters
NAVdatabase, a
(pin program)
message will be
displayed
NNN
0 to 999
may be entered as
1-3 digits; leading
zeros lay be omitted
See INB CRS
See INB CRS
CRZ TEMP
Must be entered as
FLIGHT LEVEL
See TEMP
CRZ WIND
See WIND DIR/MAG See WIND DIR/MAG
DIST
NN.N leading and
trailing 0's may be
omitted.
“D”NN
DRT TO
EFF WIND
Maximum FL
(See FLIGHT LEVEL)
0 - 99.9
or
0 - 999 (or 9999 )
Eight possible values
± NNN
0 - 500
”+” may be entered
as “T” or “TL”
"-” may be entered
as “H” or “HD”
Leading zeros may
be omitted
If no sign is input, “+”
is taken
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
UNITS
N/A
Continued from the previous page
DISPLAY PAGE
NEW NAVAID
N/A
INIT A
ROUTE SELECTION
NEW ROUTE
ALTERNATE
Kg/Min or
INIT A (ACT/SEC (2))
100 lb/Hr
PERF CLB (ACT/SEC (2))
PERF CRZ (ACT/SEC (2))
PERF DES (ALT/SEC (2))
degrees
RADIO NAV
NEW NAVAID
NEW RUNWAY
Hundred of ft
INIT A (ACT/SEC (2))
PROG
See TEMP
INIT A (ACT/SEC (2))
FUEL PREDICTION
See WIND DIR/MAG INIT A (ACT/SEC (2))
FUEL PREDICTION
NM
HOLD
NM
ALTN
kts
PERF
TAKEOFF
CLOSEST
AIRPORT
EQUI-TIME
INIT A
SEC INT A
Continued on the following page
←A→
DSC-22_20-50-30 P 2/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATA NAME
ELV
CONTROLS AND INDICATORS - MCDU - DATA FORMAT LIST
FORMAT
± NNNN
if no sign,
+ assumed
Leading 0's may be
omitted
RANGE
(X is input)
Entry displayed to
nearest 10 ft
-400 to 20 470 ft
(RWY)
(or - 1000 to 20 470 ft
)
-2 000 to 20 470
(NAVAID)
00:00:00 to 23:59:59
ETT/RTA
HH:MM:SS
FF/FQ Sensors
One or both may be
entered,
Both - /FF + FQ
or - / FQ + FF
Fuel flow - /FF
Fuel Quantity - / FQ
N
0-3
FIG OF MERIT
FINAL/TIME
FLAPS
FLEX TO TEMP
FLIGHT LEVEL
Only one may be
entered at a time.
NN.N or (NNN.N
) for FINAL
NNNN for TIME
FINAL 0 - 10.0
(or 0 - 100 )
or
0 - 22.0
0 - 90
TIME
0, 1, 2, or 3
1. If Derated TO
option not
implemented:
same as TEMP
2. If Derated TO
option is
implemented:
F NN
UNITS
Continued from the previous page
DISPLAY PAGE
ft (MSL)
NEW RUNWAY
NEW NAVAID
Hour HH
Min MM
Sec SS
N/A
N/A
Thousand of kg
or Thousand
of lb minutes
NN in degrees
centigrade
RTA
FUEL PREDICTION
NEW NAVAID
FUEL PRED
INIT B
TAKEOFF
TAKEOFF
FLNNN or NNN
Max FL = 390
Hundreds of ft (MSL) F-PLN A-B,
Leading zeros on
PROG VERT REV
(or Max FL = 410
NNN may be omitted )
INIT A (ACT, SEC (2))
PERF CLB
PERF DES
STEP PRED
STEP ALTS
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_20-50-30 P 3/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATA NAME
FORMAT
FLIGHT NUMBER XXXXXXXX
FOB
FREQ
FROM/TO
GW
IDLE FACTOR
INB CRS
LAT
LAT /LONG
CONTROLS AND INDICATORS - MCDU - DATA FORMAT LIST
RANGE
(X is input)
N/A
The 8 alphanumeric
are not mandatory
NN.N (leading zeros See BLOCK
may be omitted)
NNN.NN ILS /VOR 108.00 - 117.95
NNN.N NDB
190.0 - 1 750.0
AAAA /AAAA
AAAA must be in data
base or message will
be displayed
NN.N Leading and 35 - 99.9
trailing zeros may be or
omitted
77.2 - 218
± N.N Leading and -9.9. +9.9
trailing zeros may be
omitted
NNN
000 - 359
Leading zeros may
be omitted. An entry
of 360 is displayed
as 0.
DDMM.MB or
B: N or S
BDDMM.M
0 ≤ DD ≤ 90
DD - degrees,
0 ≤ MM.M ≤ 59.9
MM.M - minutes,
B - direction.
Leading zeros may
be omitted but the
direction (B) is
necessary.
Latitude is displayed
as DDMM.MB
LAT /LONG
See LAT and
See LAT and See
See LONG
LONG except both
must be entered with
"/" in between
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
UNITS
Continued from the previous page
DISPLAY PAGE
N/A
INIT A
F-PLN A-B
Thousands of kg or
Thousands of Lb
MHz
KHz
N/A
Thousands of kg
or
Thousands of Lb
%
Degrees
Degree minutes
tenths of minutes
See LAT and
See LONG
FUEL PREDICTION
PROG.
NEW NAVAID
RADIO NAV
INIT A (ACT/SEC (2))
FUEL PREDICTION
A/C STATUS
HOLD
INIT A (ACT/SEC (2))
F-PLN A-B (ACT/SEC (2))
PROG
NEW WAYPOINT
NEW NAVAID
DIR TO
LAT REV
NEW RUNWAY
Continued on the following page
DSC-22_20-50-30 P 4/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATA NAME
LENGTH
LONG
MACH
MACH/SPD
NAVAID
OFST
PERF FACTOR
CONTROLS AND INDICATORS - MCDU - DATA FORMAT LIST
FORMAT
NNNN
Leading zeros may
be omitted
DDDMM.MB or
BDDDMM.M
DDD - degrees
MM.M - minutes
B - direction.
Leading zeros may
be omitted but the
direction (B) is
necessary
.NN
The decimal point is
necessary.
Trailing zeros are not
necessary
MACH and SPD
must be entered with
"/" between (See
MACH and See SPD
formats )
XXXX
NNB or BNN
NN offset distance
B direction
NN.N leading or
trailing zeros may be
omitted (± N.N)
RANGE
(X is input)
1 000 - 8 000 m
3 282 - 9 999 ft
B: E or W
0 ≤ DDD ≤ 180
0 ≤ MM.M ≤ 59
UNITS
Continued from the previous page
DISPLAY PAGE
Meters or feet
Degree minutes
tenths of minutes
NEW RUNWAY
INIT A
MAX = 0.82
MIN = 0.15
Mach Number
F-PLN A (ACT/SEC (2))
PERF CLB
PERF CRZ
PERF DES
See MACH and
See SPD
See MACH
and See SPD
PERF DES (ACT/SEC (2))
Any alphanumeric
N/A
B: L or R
1 < NN < 50
NM
PROG
NEW NAVAID
NAVAID
F-PLN A-B (ACT/SEC (2))
LAT REV
DIR TO
RADIO NAV
SELECTED NAVAIDS
LAT REV
-10.0 to +10.0
(or -9.9 - +9.9 )
N/A
A/C STATUS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
←A→
DSC-22_20-50-30 P 5/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATA NAME
PLACE/BRG
/DIST
PLACE-BRG /
PLACE-BRG
PLACE/DIST
QNH
CONTROLS AND INDICATORS - MCDU - DATA FORMAT LIST
FORMAT
PLACE can be
any data base
ARPT , NAVAID or
WAYPOINT - BRG
must be a 3 digit
entry without decimal
digit.
An entry of BRG =
360 is displayed as
0.
DIST is NNN.N
where leading zeros
may be omitted ; all
3 parameters must
be entered with "/"
between
See PLACE/BRG/
DIST
A couple PLACEBRG is entered with
a dash in the middle.
2 couples have to
be entered with "/"
between
PLACE: See PLACE/
BRG/DIST
DIST: See PLACE/
BRG/DIST
NNNN (leading zero
may be omitted).
NN.NN (leading and
trailing zeros may be
omitted).
NNN(T) 3 digits entry
RANGE
(X is input)
PLACE - If not in data
base, a message
"NOT IN DATA BASE"
is displayed
BRG - 000 - 360
DIST - 0 - 999.9
UNITS
N/A
degrees
Continued from the previous page
DISPLAY PAGE
LAT REV (ACT/SEC (2))
NEW WAYPOINT
PROG
DIR TO
F-PLNA-B (ACT/SEC (2))
STEP ALTS
NM
See PLACE/BRG/DIST See PLACE/BRG/DIST See PLACE/BRG/DIST
PLACE: See PLACE/
BRG/DIST
DIST: 0 - 999.9
950 - 1 050
(or 745 - 1050 )
28.06 - 31.01
(or 22.00 - 31.00 )
000 - 360
RADIAL
NNN(T)
3
digits
entry
000 - 360
RADIAL IN
RADIAL OUT NNN(T) 3 digits entry 000 - 360
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
N/A NM
F-PLN A and B
SEC F-PLN A and B
LAT REV
NEW WAYPOINT
DIR TO
STEP ALTS
Hecto-Pascals (hPa) PERF APPR (ACT/SEC (2))
In.Hg
Degrees
Degrees
Degrees
←A→
FIX INFO 1 to 4
DIR TO
DIR TO
FIX INFO 1 to 4
Continued on the following page
DSC-22_20-50-30 P 6/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATA NAME
RADIO
RADIUS
REF FIX
RTE RSV
RWY
SAT /ALT
SET HDG
SLOPE
SPD
SPD CSTR
CONTROLS AND INDICATORS - MCDU - DATA FORMAT LIST
FORMAT
RANGE
(X is input)
NNN
0–700 No is accepted
if an ILS / GLS ;
APPR is selected
DNNN 3 digits entry 000 - 256
D is the identifiant of
the circle radius
See waypoint
may be entered as
fuel or percentage of
trip fuel
AAAANND
Where AAAA is See
ARPT.
NN is runway
number (2 digits)
must be entered
D is L or R to be
included only when
there is more than
one runway with the
same number at
ARPT.
TEMP /ALT
Fuel 0 - 10.0
0 - 21.7
% : 0 - 15.0
See TEMP and
See ALT
NNN/N (leading and 000.0 - 360.0
trailing zeros may be
omitted) will always
be displayed as
NNN/N
NN.N
00.0 -90.0
NNN
MAX = 350 kt
(leading zero may be MIN = 90 kt
omitted)
See SPD
See SPD
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
UNITS
ft
NM
thousands of kg
thousands of lb
PERF APPR (ACT/SEC (2))
FIX INFO 1 to 4
FIX INFO 1 to 4
INIT B (ACT/SEC (2))
FUEL PRED
RUNWAY
NEW RUNWAY
F-PLN A-B
N/A
CRUISE WIND
Degrees
IRS MONITOR
Degrees
NEW NAVAID
kt (CAS)
kt (CAS)
←A→
Continued from the previous page
DISPLAY PAGE
SEC F-PLN A
PERF CLB
PERF CRZ (ACT, SEC (2))
PERF DES
F-PLN A (ACT/SEC (2))
VERT REV (ACT/SEC (2))
Continued on the following page
DSC-22_20-50-30 P 7/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATA NAME
SPD LIM
SPD/MACH
STATION DEC
STEP ALT
TAXI
TEMP
THR RED ALT
THS
FORMAT
RANGE
(X is input)
SSS: See SPD
SSS/NNNNN
SSS is a speed
NNNNN is an ALT
or FLIGHT LEVEL
(See ALT and
See FLIGHT LEVEL)
See MACH/SPD
See MACH and
See SPD
NND
NN: 01 - 99
Where NN is the
D: E or W
declination and D is
the direction.
Leading zeros may
be omitted.
D is not required
for an entry of zero
declination.
SNNN or NNNS
See FLIGHT LEVEL
(where NNN is
or See ALT
in Flight Level)
or SNNNNN or
NNNNNS (where
NNNNN is in ALT)
Leading zeros may
be omitted
N.N
0 - 9.9
Leading or trailing
zeros may be omitted
± NN
± 99
If no sign,
+ assumed
See ALT
400 ft AGL mini
AAN.N or N.NAA
where AA is UP or
DN
See ALT
TRANS ALT
N.N
TIME
TIME MARK. HHMM
T.O SHIFT
CONTROLS AND INDICATORS - MCDU - DATA FORMAT LIST
NNNN
UNITS
kt/ft (MSL)
VERT REV (ACT/SEC (2))
See MACH
and See SPD
Degrees
PERF DES (ACT/SEC (2))
INIT B (ACT/SEC (2))
Degrees celsius
INIT A (ACT/SEC (2))
FUEL PRED
PERF APPR
PERF TAKE OFF
ft (MSL)
0 - 9.9
Minutes
←A→
F-PLN A
Thousands of kg
degrees
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
NEW NAVAID
See FLIGHT
LEVEL or See ALT
max UP 7.0
max DN 5.0
increment 0.1
HH: 0 - 23
MM: 0 - 59
1-Length of origin
runway
Continued from the previous page
DISPLAY PAGE
Hours Minutes
m or ft
PERF TAKEOFF
PERF GO AROUND
HOLD
F-PLN A and B
PERF TAKEOFF
Continued on the following page
DSC-22_20-50-30 P 8/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATA NAME
FORMAT
CONTROLS AND INDICATORS - MCDU - DATA FORMAT LIST
RANGE
(X is input)
UNITS
TRIP WIND
See EFF WIND
TROPO
See ALT
UTC CSTR
V1
HH MM
HH: 0 - 23
Where HH are hours MM: 0 - 59
and MM are minutes.
Leading zeros
may be omitted 1
or 2 digit entry is
interpretated as
minutes
See SPD
V2
See SPD
kt (CAS)
VR
See SPD
kt (CAS)
WIND
See WIND DIR/
See WIND DIR/
VELOCITY
VELOCITY
XXXXX - may be
from . 1-5 (1-7
) characters for
waypoint. Acceptable
as waypoint IDENT:
ARPT
NAVAID
WAYPOINT
LAT /LONG,
PLACE BRG /
PLACE BRG
and PLACE/BRG /
DIST PLACE/DIST
may be entered
to define a waypoint
WAYPOINT
See ALT
(or 60 000 )
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued from the previous page
DISPLAY PAGE
kts
ft
Hours and minutes
kt (CAS)
←A→
See WIND DIR/
VELOCITY
INIT A
SET INIT A
INIT A
FUEL PREDICTION
SEC FUEL PREDICTION
VERT REV
PERF TAKEOFF
(ACT/SEC (2))
PERF TAKEOFF
(ACT/SEC (2))
PERF TAKEOFF
(ACT/SEC (2))
F-PLN B (ACT/SEC (2))
FUEL PREDICTION
WAYPOINT
NEW WAYPOINT
F-PLN A and B (ACT/SEC
(2)
)
LAT REV
PROG
DIR TO
FIX INFO 1 AND 2
EQUI-TIME POINT
STEP ALTS
PREDICTIVE GPS
Continued on the following page
DSC-22_20-50-30 P 9/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATA NAME
CONTROLS AND INDICATORS - MCDU - DATA FORMAT LIST
FORMAT
WIND DIR /WIND NNN/NNN
Both must be
MAG
entered ; leading
zeros may be
omitted.
An entry of WIND
DIR = 360 is
displayed as 0.
NNN/NNN/FL NNN
WIND
DIRECTION/ MAG or
NNN/NNN/NN NNN
/ALT
ZFW
RANGE
(X is input)
WIND DIRECTION
0 - 360
WIND MAG
0 - 200
(or 0 - 500 )
Direction and Velocity
as above
Minimum ALT 1 000
NN.N OR NNN.N
MIN ZFW See – Max
Leading and trailing ZFW See
zeros may be omitted
(1)
As defined in the Performance Data Base.
(2)
ACT/SEC = Active or Secondary
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
UNITS
Continued from the previous page
DISPLAY PAGE
Degrees
Kt
INIT A
PERF APPR (ACT/SEC (2))
STEP PRED
WIND
F-PLN B
VERT REV
FL in hundred
of ft, ALT in ft
DES FORECAST
WIND PAGES
Thousands of kg
or
thousands of Lb
INIT B (ACT/SEC (2))
DSC-22_20-50-30 P 10/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - EFFECT OF BARO REFERENCE SETTING
GENERAL
Ident.: DSC-22_20-60-10-00000921.0001001 / 10 DEC 09
Applicable to: ALL
The baro reference selector of the EIS (Electronic Instrument System) allows the pilot to use the
standard barometric reference (STD ), sea level atmospheric pressure (QNH ), or atmospheric
pressure at airfield elevation (QFE option) for the barometer setting.
The selected value is displayed in the baro reference display window of the EFIS control panel and
on the Primary Flight Display (PFD) below the altitude scale.
The barometer setting is used as a reference for the altimeter of the PFD and for the PFD target
altitude. In flight, it affects the predicted altitudes on the MCDU and the descent path computation.
MCDU ALTITUDE PREDICTIONS
Applicable to: ALL
Ident.: DSC-22_20-60-10-A-00000922.0001001 / 10 DEC 09
GENERAL
The FMGS predicts at each waypoint of the flight plan an altitude that is a function of all data in the
lateral and vertical flight plans.
Ident.: DSC-22_20-60-10-A-00000927.0001001 / 10 DEC 09
ON THE GROUND
The altitude predicted at each waypoint is displayed as altitude in feet above mean sea level
(AMSL) when it is below the transition altitude and as flight level when it is above the transition
altitude. The altitude constraints are also displayed, and they follow the same rule (feet or flight
level).
The predicted altitude is equal to the airport elevation plus the height you must attain in order to
reach the waypoint in the applicable mode (climb or descent).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_20-60-10 P 1/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - EFFECT OF BARO REFERENCE SETTING
Ident.: DSC-22_20-60-10-A-00000924.0001001 / 16 FEB 11
IN FLIGHT
The predicted altitude is equal to the aircraft altitude (as a function of the barometer setting),
plus or minus the height you must attain to reach the waypoint in the applicable mode (climb or
descent).
‐ In climb:
Altitude predictions and constraints are displayed as altitude in feet above mean sea level
(AMSL) at, or below, the transition altitude, and as the flight level above it.
For example : If the transition altitude is 5 000 ft and you insert an altitude constraint as 8 000 ft,
the MCDU F-PLN A page displays it as FL 80
‐ In descent:
If “STD ” is selected on the EIS control panel, altitude predictions and constraints above the
transition level are displayed as flight levels, and those below the transition level are displayed
as altitude AMSL.
If sea level standard pressure (QNH ), or field elevation pressure (QFE option), is selected on
the EIS control panel, altitude predictions and constraints are displayed as altitudes AMSL,
regardless of the transition altitude.
For example: If the transition level is FL 50 and you insert an altitude constraint of 8 000 ft into
the MCDU , the MCDU F-PLN S A page will display it as FL 80, if “STD ” is selected, and as
8 000 ft, if “QNH ” (or “QFE ” option) F-PLN A page is selected.
TARGET ALTITUDE ON PFD
Ident.: DSC-22_20-60-10-00000925.0001001 / 01 OCT 12
Applicable to: ALL
The PFD target altitude may either be:
‐ The altitude selected on the FCU, or
‐ A flight management altitude constraint, if the climb mode or descent mode is engaged and the
system predicts a level-off at a constraint that comes before reaching the FCU altitude.
The PFD target altitude depends on the barometer setting:
‐ If “STD” is selected, the target is a flight level
‐ If “QNH ” or “QFE” is selected, the target is an altitude or height.
The aircraft will level off accordingly.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_20-60-10 P 2/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
OTHER FUNCTIONS - EFFECT OF BARO REFERENCE SETTING
‐ If the pilot changes the barometer setting during ALT * or ALT CST*, the aircraft may
overshoot the target altitude, because the current value has been changed. However, the
ALT * and ALT CST* modes allow the aircraft to regain the FCU altitude. As a general
rule, avoid changing the barometer setting when in ALT * or ALT CST*
‐ In aircraft equipped to use field elevation pressure (QFE option), switching from STD
to QFE (or vice versa) in ALT CST* green changes the target value and may revert the
vertical mode into V/S mode.
NOTE FOR AIRCRAFT WITH QFE (FIELD ELEVATION PRESSURE) PIN PROGRAM
If you select “QFE ” on the EFIS control panel:
‐ The MCDU predictions follow the basic rules (altitudes are AMSL below the transition level,
flight levels above it)
‐ The altitude constraints on the MCDU follow the basic rules
‐ The target altitude on the PFD is QFE related:
• If the target altitude has been selected by the FCU, the aircraft will level off there.
• If the target altitude is an altitude constraint, the PFD automatically shows that constraint as
corrected by the airport elevation.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-22_20-60-10 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - EFFECT OF BARO REFERENCE SETTING
PROCEDURES
Ident.: DSC-22_20-60-10-00000928.0001001 / 16 FEB 11
Applicable to: ALL
a. The altitude constraints in departure and arrival procedures should be defined in the navigation
database or by the pilot on the MCDU:
‐ in terms of altitude AMSL below the transition altitude
‐ in terms of flight level above the transition altitude
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
DSC-22_20-60-10 P 4/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - EFFECT OF BARO REFERENCE SETTING
If a departure procedure defines an altitude constraint as an AMSL altitude above the transition
altitude, you must convert it to STD, because the system and guidance will treat it as a flight level
whenever you select the standard barometer setting.
b. In climb you should switch from QNH (or QFE ) to STD on both EFIS control panels
simultaneously when you reach the transition altitude.
All MCDU altitude predictions and altitude constraints and all PFD altitude targets will be displayed
as flight levels.
c. In descent, when ATC clears you to an altitude below the transition altitude, you can select QNH
(or QFE ) on both EFIS control panels simultaneously.
All MCDU altitude predictions and contraints and PFD targets are now altitude AMSL.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
DSC-22_20-60-10 P 5/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - EFFECT OF BARO REFERENCE SETTING
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_20-60-10 P 6/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - CLEAR KEY (CLEARING FUNCTION)
CLEARING THE SCRATCHPAD OF DATA OR MESSAGES
Ident.: DSC-22_20-60-20-00000929.0001001 / 16 FEB 11
Applicable to: ALL
Press the “CLR” key with a single brief touch to erase the last alphanumeric character inserted in the
scratchpad.
Press the key for more than three seconds to erase all the data inserted in the scratchpad. If the
scratchpad is empty, it displays “CLR”.
CLEARING DATA FIELDS
Ident.: DSC-22_20-60-20-00000930.0001001 / 16 FEB 11
Applicable to: ALL
Clear a data field by pressing the “CLR” key, the scratchpad displays CLR, then select the prompt for
the field you want to clear (3L for example).
‐ You cannot clear all data fields:
• If the field contains data that has a default value or a value computed by the FMGC, the data
reverts to this value.
• Any attempt to clear the defaulted value has no effect.
‐ Clearing a constraint on the F-PLN page deletes both the speed constraint and the altitude
constraint associated with the waypoint
‐ If you clear a data field that is a waypoint in the flight plan (primary or secondary), you delete this
waypoint from the flight plan and create a discontinuity. The discontinuity can also be cleared in a
similar way.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_20-60-20 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - CLEAR KEY (CLEARING FUNCTION)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-22_20-60-20 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - HOW TO EXECUTE A DIVERSION
GENERAL
Ident.: DSC-22_20-60-30-00000932.0002001 / 16 FEB 11
Applicable to: ALL
Various features are provided to the crew in order to execute a diversion:
‐ The EQUITIME POINT
‐ The CLOSEST AIRPORTS pages
‐ The SECONDARY F-PLN
‐ The ENABLE ALTN function
‐ The NEW DEST revision
EN ROUTE DIVERSION WITH SEVERAL AIRPORTS AVAILABLE
Ident.: DSC-22_20-60-30-00009508.0002001 / 16 FEB 11
Applicable to: ALL
SELECT the CLOSEST AIRPORTS page.
SELECT the EFOB/WIND prompt.
INSERT the effective wind at selected airport.
CHECK the predictions and CHOOSE the adequate diversion airport.
PREPARE the diversion flight plan on the SEC F-PLN.
Note:
Fuel/time predictions on the CLOSEST AIRPORTS page assume managed speed profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-22_20-60-30 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - HOW TO EXECUTE A DIVERSION
EN ROUTE DIVERSION OVER OCEANIC OR DESERTIC AREA
Ident.: DSC-22_20-60-30-00009528.0001001 / 16 FEB 11
Applicable to: ALL
The diversion airports are usually determined before departure or using the CLOSEST AIRPORTS
data.
SELECT the EQUI-TIME POINT page.
ENTER the airport idents in 1L and 3L fields.
ENTER the associated winds in 2L and 4L fields.
CHECK the ETP position and time.
ENTER a predicted time at ETP as time marker.
PREPARE a diversion flight plan on the secondary flight plan.
DIVERSION PREPARATION ON THE SECONDARY FLIGHT PLAN
Ident.: DSC-22_20-60-30-00009530.0002001 / 16 FEB 11
Applicable to: ALL
The following procedure shall be applied for all diversion cases, once the diversion airport has been
selected, as well as the “most probable diversion point of the F-PLN”:
PRESS the SEC F-PLN key
PRESS the COPY ACTIVE prompt
SELECT a lateral revision at diversion waypoint
ENTER the ident of the diversion airport in the NEW DEST field.
Then finalize the flight plan between the diversion point and the diversion airport. When the diversion
airport is no longer applicable or ETP is sequenced, repeat the same procedure for the next diversion
airport.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D
DSC-22_20-60-30 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - HOW TO EXECUTE A DIVERSION
MISCELLANEOUS
Ident.: DSC-22_20-60-30-00009531.0002001 / 16 FEB 11
Applicable to: ALL
In some cases, the diversion airport may be simply chosen using the airports displayed on ND when
AIRPORT is selected on the EIS control panel.
During oceanic or desertic area flights, the flight crew may use the PROG page, as follows:
ENTER the ident of the diversion airport in the 4R field of MCDU 1
ENTER the next diversion airport in the 4R field of MCDU 2
Then, the FMS continuously calculated the BRG /DIST to the selected diversion airports.
UPDATE the PROG pages when sequencing the ETP.
EXECUTION OF THE DIVERSION
Ident.: DSC-22_20-60-30-00009532.0001001 / 16 FEB 11
Applicable to: ALL
When the crew decides to divert:
PRESS the SEC F-PLN key.
SELECT the ACTIVATE SEC prompt.
SELECT DIR TO required point.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E to F
DSC-22_20-60-30 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - HOW TO EXECUTE A DIVERSION
DIVERSION TO THE ALTERNATE AIRPORT
Ident.: DSC-22_20-60-30-00009537.0001001 / 16 FEB 11
Applicable to: ALL
The primary F-PLN includes an alternate flight plan from destination to the preferred alternate airport.
All fuel prediction and management (EXTRA fuel) take the alternate flight plan into consideration.
If the crew decides to divert at the end of the cruise, or beyond the last ETP, or in the descent or
go-around phases, this will most probably be to the alternate airport.
When the crew decides to divert:
SELECT a lateral revision at suitable waypoint
SELECT ENABLE ALTN prompt
CHECK the temporary flight plan and INSERT
SELECT DIR TO required waypoint
Note:
‐ In most cases, the LAT REV shall be selected at the TO WPT . This will facilitate the
subsequent selection of the DIR TO waypoint.
‐ The ALTN flight plan shall be finalized, whenever the landing runway is known by the
crew (before approach briefing).
In most cases, this will ensure that the most probable flight plan is displayed on the
MCDU once ENABLE ALTN is selected.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
DSC-22_20-60-30 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - ENGINE OUT
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_20-60-40-00000937.0001001 / 16 FEB 11
Applicable to: ALL
When the FMGS detects an engine-out condition, the following occurs:
FLIGHT MANAGEMENT PART
Ident.: DSC-22_20-60-40-00000938.0026001 / 16 MAR 11
Applicable to: ALL
‐
‐
‐
‐
‐
‐
The managed target speeds is immediately set to a value that depends upon the flight phase
All preselected speeds entered in the MCDU are deleted
Step climb (or step descent), if entered, is deleted
The time constraint is deleted
The PROG page shows the engine-out maximum recommended (EO MAX REC) altitude
The system automatically calls up the current performance page, which has the EO CLR
(engine-out clear) prompt displayed in the 1R field (except during takeoff, before the diversion
point is reached).
If the crew presses the EO CLR , the 2 engine predictions and performance will be restored.
Reverting back to one engine-out performance is not possible, unless the system detects a new
EO condition. Therefore, the pilot should not press the EO CLR key, if an actual engine-out is
detected
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-22_20-60-40 P 1/10
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - ENGINE OUT
FLIGHT CREW
OPERATING MANUAL
FLIGHT GUIDANCE PART
Ident.: DSC-22_20-60-40-00000939.0002001 / 04 JUL 17
Applicable to: ALL
‐ All selected modes remain available (the “HDG/TRK”, “V/S”, and “OPEN” modes, for example)
‐ In the speed reference system (SRS ) mode, the takeoff speed target is V2 , or the current speed
if it is higher but no more than V2 +15. The magenta triangle indicates V2 in all cases. The GO
Around speed target is VAPP , or the current speed if higher, limited to VLS +15 kt
‐ The system limits autopilot (AP ) and flight director (FD) bank angles during takeoff and approach
phases as follows:
• 15 ° when the aircraft speed is below the maneuvering speeds (F, S, or Green Dot speed) -10 kt
, and then
• In selected lateral guidance:
• Linear increase to 25 ° up to maneuvering speeds (F, S, or Green Dot speed) -3 kt
• 25 ° above maneuvering speeds (F, S, or Green Dot speed) -3 kt .
• In managed lateral guidance:
• Linear increase to 30 ° up to maneuvering speeds (F, S, or Green Dot speed) -3 kt
• 30 ° above maneuvering speeds (F, S, or Green Dot speed) -3 kt .
Note:
The engine-out bank angle limits apply, when the FG part of the FMGS has detected an
engine-out. It cannot be cleared by the crew through the MCDU EO CLEAR prompt.
AUTOTHRUST
Ident.: DSC-22_20-60-40-00000940.0001001 / 16 FEB 11
Applicable to: ALL
The system extends the active range of the active engine from idle to maximum continuous thrust
(MCT instead of CL thrust).
The Flight Mode Annunciator requests maximum continuous thrust on the live engine at a time that
depends on when the engine-out occurs.
ENGINE-OUT CONDITIONS
Ident.: DSC-22_20-60-40-00000941.0001001 / 16 FEB 11
Applicable to: ALL
The FMGS considers the aircraft to be in an engine-out condition, when one of the following
conditions is present and the aircraft has commenced takeoff or is in flight:
‐ One engine master switch off, or
‐ N2 below idle, or
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to E →
DSC-22_20-60-40 P 2/10
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - ENGINE OUT
FLIGHT CREW
OPERATING MANUAL
‐ One thrust lever angle is below 5 ° with the other above 22 °, or
‐ The FADEC shows an engine fault.
ENGINE-OUT SID
Applicable to: ALL
Ident.: DSC-22_20-60-40-A-00000942.0001001 / 14 MAY 12
GENERAL
An engine-out standard instrument departure (EOSID), when defined in the database, is always for
a specific runway. It is indicated on the bottom line of the SID page for that runway, and you can
select it manually.
The pilot can review the SID either by selecting the PLAN mode on the navigation display (solid
yellow line), or by selecting it on the SID page. In the latter case, the navigation display shows the
SID as a temporary flight plan.
The last point, if any, that is common to both the SID and engine-out SID is called the diversion
point (DP).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F →
DSC-22_20-60-40 P 3/10
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - ENGINE OUT
Ident.: DSC-22_20-60-40-A-00000943.0001001 / 14 MAY 12
WHEN AN ENGINE-OUT CONDITION OCCURS BEFORE THE DIVERSION POINT
The MCDU automatically shows the engine-out SID as a temporary flight plan on the F-PLN page
and on the ND. The EOSID can be inserted or erased.
Note:
The EOSID Diversion Point is the waypoint at which the EOSID diverges from the active
SID.
If there is no common leg between the SID and the EOSID in the navigation database,
the diversion point is by default the runway threshold. Therefore the SID and EOSID
common leg(s) before the flight paths separation must be the same type and nature.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
DSC-22_20-60-40 P 4/10
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - ENGINE OUT
Ident.: DSC-22_20-60-40-A-00000944.0001001 / 14 MAY 12
WHEN AN ENGINE-OUT CONDITION OCCURS AFTER THE DIVERSION POINT
REMAIN on the SID path
Note:
The navigation display shows the engine-out SID as a yellow line for your information.
Directing the aircraft to the EOSID should not be performed unless it allows obstacle
clearance and the flight crew considers it is the best strategy for a particular case.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
DSC-22_20-60-40 P 5/10
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - ENGINE OUT
Ident.: DSC-22_20-60-40-A-00000945.0002001 / 14 MAY 12
BELOW THRUST-REDUCTION (THR RED) ALTITUDE
‐ The managed target speed changes to V2
‐ The PROG page displays the engine-out maximum recommended altitude
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
DSC-22_20-60-40 P 6/10
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - ENGINE OUT
‐ The PERF TO page comes up on the display automatically with the “EO CLR” prompt in the 1R
field
‐ The MCDU and the navigation display show the engine-out SID as a temporary flight plan, or
the navigation display shows it for information only, depending upon the diversion point location.
PROCEDURE
When the aircraft reaches the engine-out acceleration altitude
PUSH in the V/S knob to level off.
CLEAN up your configuration as the speed increases toward target speed.
When the aircraft is clean and has reached Green Dot speed, “LVR MCT” flashes on the
FMA,
PULL out the altitude selector knob to resume the climb.
The OP CLB. mode engages.
MOVE the thrust lever for the live engine to “MCT” detent.
Ident.: DSC-22_20-60-40-A-00000946.0006001 / 16 FEB 11
ABOVE THRUST REDUCTION (THR RED) ALTITUDE
‐
‐
‐
‐
‐
The managed target speed changes to V2
“LVR MCT” flashes amber on the flight mode annunciator
The PROG page displays the engine-out maximum recommended altitude
The PERF TO page displays the “EO CLR*” prompt in the 1R field
The navigation display shows the EO SID.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
DSC-22_20-60-40 P 7/10
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - ENGINE OUT
PROCEDURE
MOVE the thrust lever of the active engine to the MCT detent.
When the aircraft reaches the engine-out acceleration altitude:
PUSH the V/S knob, in order to level off.
CLEAN UP configuration as the speed increases.
When the aircraft reaches Green Dot speed:
PULL the ALT knob to resume the climb.
Note:
If necessary, move the thrust lever of the active engine to the TOGA detent. The
Flight Mode Annunciator will display “LVR MCT”, flashing in white, when the
aircraft reaches Green Dot speed.
ENGINE-OUT IN CLB PHASE (ABOVE ACCELERATION ALTITUDE)
Applicable to: ALL
Ident.: DSC-22_20-60-40-B-00000947.0003001 / 16 FEB 11
ENGINE-OUT OCCURS WHILE AIRCRAFT IS ACTUALLY CLIMBING
‐ The managed target speed changes to Green Dot speed
‐ “LVR MCT” flashes white on the Flight Mode Annunciator
‐ The climb mode reverts to open climb (OP CLB) and the aircraft slowly decelerates down to
Green Dot speed
‐ The MCDU shows the PERF CLB page with an “EO CLR*” (clear engine-out) prompt
‐ The PROG page shows the engine-out maximum recommended altitude (EO MAX REC ALT).
PROCEDURE
MOVE the thrust lever of the active engine to the MCT detent.
SET the altitude on the Flight Control Unit to an altitude below the engine-out maximum
recovery altitude, as cleared by ATC.
INITIATE a diversion, when cleared to do so.
Ident.: DSC-22_20-60-40-B-00000948.0001001 / 16 FEB 11
ENGINE-OUT OCCURS WHILE THE AIRCRAFT IS FLYING IN ALT MODE AT AN ALTITUDE
SET ON THE FLIGHT CONTROL UNIT
‐ The target speed is set to engine-out cruise speed (EO CRZ SPD ), computed at the altitude set
on the Flight Control Unit, but limited by the limit speed (SPD LIM), if there is one.
Other consequences and procedures are similar to previous engine out climb.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G
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05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - ENGINE OUT
FLIGHT CREW
OPERATING MANUAL
ENGINE-OUT IN CRUISE PHASE
Ident.: DSC-22_20-60-40-00000949.0001001 / 21 MAR 17
Applicable to: ALL
‐ The system sets the managed target speed to the higher of engine-out cruise Mach number or
speed, or current speed.
‐ “LVR MCT” (or MCT) flashes on the Flight Mode Annunciator.
‐ The PERF CRZ page appears with the “EO CLR*” (clear engine-out) prompt.
‐ The PROG page displays the engine-out maximum recommended altitude (EO MAX REC ALT).
PROCEDURE
Perform engine out abnormal procedure.
Refer to PER-OEI-GEN INTRODUCTION “SINGLE ENGINE OPERATIONS”
‐ For standard strategy,Refer to FCTM/PR-AEP-ENG Engine Failure During Cruise
‐ For obstacle strategy,Refer to FCTM/PR-AEP-ENG Engine Failure During Cruise
‐ For fixed strategy, Refer to FCTM/PR-AEP-ENG Engine Failure During Cruise
Initiate a diversion if necessary.
Note:
The engine-out descent strategy requires disconnection of the autothrust, and descent in
OPEN DES mode.
Disconnecting the autothrust prevents an automatic setting of THR IDLE; therefore, the
autopilot will fly the target speed in OP DES mode, with a thrust manually selected by the
crew.
When reaching the FCU-selected altitude, or whenever normal descent is resumed to a
lower altitude, reengage the autothrust.
ENGINE-OUT IN DESCENT PHASE
Ident.: DSC-22_20-60-40-00000951.0001001 / 16 FEB 11
Applicable to: ALL
‐ The managed target speed remains unchanged (ECON DES Mach number or speed, with any
speed limitations).
‐ “LVR MCT” (or MCT) flashes on the Flight Mode Annunciator.
‐ The PERF DES page appears, showing the “EO CLR*” prompt.
‐ The PROG page displays the engine-out maximum recommended altitude (EO MAX REC ALT).
‐ The descent mode (if engaged) reverts to V/S , if the aircraft is above the EO REC MAX. If not, the
descent mode is maintained.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H to I →
DSC-22_20-60-40 P 9/10
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - ENGINE OUT
FLIGHT CREW
OPERATING MANUAL
PROCEDURE
MOVE the thrust lever for the live engine to the MCT detent.
If necessary, SELECT a suitable flight mode for descent.
DISCONNECT the autothrust and ADJUST thrust if necessary.
ENGINE-OUT IN APPROACH PHASE
Ident.: DSC-22_20-60-40-00000952.0001001 / 04 JUL 17
Applicable to: ALL
‐
‐
‐
‐
The aircraft maintains approach speed (VAPP).
“LVR MCT”(or MCT) flashes on the Flight Mode Annunciator.
The PERF APPR page appears, showing the “EO CLR*” prompt.
The progress page displays the engine-out maximum recommended altitude (EO MAX REC ALT).
PROCEDURE
MOVE the thrust lever for the live engine to the MCT detent.
CAUTION
Below maneuvering speed (F, S, Green Dot) – 10 kt, the autopilot or flight director
(AP/FD) cannot order a bank angle greater than 15 °.
Above maneuvering speed – 10 kt, this limit linearly increases until it reaches:
‐ In selected lateral guidance: 25 ° at maneuvering speed – 3 kt. The limit is then
25 ° for all speeds above maneuvering speed – 3 kt.
‐ In managed lateral guidance: 30 ° at maneuvering speed – 3 kt. The limit is
then 30 ° for all speeds above maneuvering speed – 3 kt.
ENGINE-OUT IN GO-AROUND PHASE
Ident.: DSC-22_20-60-40-00000953.0002001 / 16 FEB 11
Applicable to: ALL
The results and procedures for takeoff phase apply, except that the displays do not show the
engine-out SID.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← I to K
DSC-22_20-60-40 P 10/10
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - SECONDARY FLIGHT PLAN
SECONDARY FLIGHT PLAN
Ident.: DSC-22_20-60-50-00000954.0011001 / 14 MAY 12
Applicable to: ALL
The secondary flight plan (SEC F-PLN) is an alternative flight plan which can be activated when
required.
It may include all the vertical elements except history wind data.
The flight crew can:
‐ Create a secondary flight independently from the active flight plan (a secondary flight plan can be
created while a temporary flight plan exists).
‐ Copy it from the active flight plan.
‐ Delete it completely.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - SECONDARY FLIGHT PLAN
‐ Activate it, when the “ACTIVATE SEC” prompt is displayed: The secondary flight plan becomes
the active flight plan.
‐ The screen displays the “ACTIVATE SEC” prompt in flight if:
• HDG (or TRK) mode is engaged, or
• NAV mode is engaged, and the active leg of the primary and secondary flight plans is the same.
The FMS sequences the secondary flight plan the same way as the active flight plan, when it is a
copy of the active flight plan.
The navigation display shows the secondary flight plan in white. In PLAN mode, the crew can use the
slew keys to review the secondary flight plan (as for the primary flight plan).
PREDICTIONS
The FMGS computes predictions using the same performance methods and performance factor it
uses for the active flight plan. However, it predicts pseudo waypoints only for the MCDU not for the
Navigation Display (ND).
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - SECONDARY FLIGHT PLAN
‐ When the flight crew initializes the secondary flight plan with the SEC INIT function:
The FMGS computes the secondary flight plan predictions as if the aircraft were on ground
before engine start. The FMGS computes these predictions one time and does not update them
to indicate the progress of the flight (aircraft position, fuel consumption, etc.).
‐ When the flight crew initializes the secondary flight plan with the COPY ACTIVE function:
The FMGS computes the secondary flight plan predictions as for the active flight plan. However:
• The FMGS stops the update of the predictions if the first leg of the active flight plan is no
longer the same as the active leg (i.e. if both flight plans diverge). The flight phase is the
same as the flight phase at the time of the divergence.
Note:
This does not apply to the preflight phase, when the FMGS computes the
predictions if the departure airports are the same, even if the takeoff runways are
different.
‐ The flight crew may use the secondary flight plan in the following cases:
• At takeoff when an alternate takeoff runway is probable
• On ground to initialize the FMGS again if the flight that the flight crew initially prepared is
replaced by another flight (Refer to PRO-NOR-SRP-01-05 Introduction)
• In flight to prepare a diversion
• In flight when an alternate landing runway is probable
• To prepare the next flight.
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←A
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - SECONDARY FLIGHT PLAN
Intentionally left blank
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FCOM
DSC-22_20-60-50 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - PILOTS/STORED ROUTE FUNCTION
STORED ROUTE FUNCTION
Ident.: DSC-22_20-60-60-00000955.0002001 / 01 OCT 12
Applicable to: ALL
The stored route function allows the pilot to store or review as many as five different routes defined in
an active or secondary flight plan.
This also allows the pilot to store a company route that is not yet in the database, but is expected to
be flown several times (a charter route, for example).
Access the STORED ROUTES page from the DATA INDEX page.
A stored route can be reviewed by using the slew key.
In order to store a new route, first define the route through the active flight plan (on the ground only)
or the secondary flight plan (on the ground or in flight) then proceed as described below.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - PILOTS/STORED ROUTE FUNCTION
HOW TO STORE THE ACTIVE FLIGHT PLAN (DURING PREFLIGHT ONLY)
SELECT the DATA key on MCDU
PRESS the “STORED ROUTES” key
PRESS the “NEW ROUTE” key
ENTER the name of the company route (optional).
PRESS the “STORE ACTIVE F-PLN” key
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - PILOTS/STORED ROUTE FUNCTION
HOW TO STORE THE SECONDARY FLIGHT PLAN
SELECT the DATA key on MCDU
PRESS the “STORED ROUTES” key
PRESS the “NEW ROUTE” key
ENTER the company route name (optional)
PRESS the “STORE SECONDARY F-PLN” key
Note:
1. In either case, you may only store a company route if the active or secondary flight
plan is complete from origin to destination.
2. If you do not enter a name, the FMGS automatically names the stored route as “SRTE
1 (or 2 ...)” when it is stored.
3. The system does not retain several elements of the flight plans, when they are stored:
‐ Pilot-entered holds
‐ Offsets
‐ Pilot-entered constraints
‐ Modifications to a terminal procedure
‐ Pseudo waypoints
When this happens, it displays “REVISIONS NOT STORED”.
4. If five routes are already stored the system will reject a new entry and display
“STORED ROUTES FULL” on the MCDU . Delete one stored route by clearing the
CO RTE name before inserting a new one.
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←A
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - PILOTS/STORED ROUTE FUNCTION
Intentionally left blank
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FCOM
DSC-22_20-60-60 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - REPORT PAGE
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_20-60-70-00006017.0001001 / 16 FEB 11
Applicable to: ALL
The REPORT page allows the crew to achieve the position reporting.
REPORT PAGE ACCESS
Ident.: DSC-22_20-60-70-00009524.0008001 / 29 SEP 15
Applicable to: ALL
The report page is accessed from the PROG PAGE.
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
OTHER FUNCTIONS - REPORT PAGE
In case a DIR TO with ABEAM WPT s is achieved, or in case a FIX INFO with ABEAM
or RADIAL/CIRCLE intersection is inserted in the F-PLN , the TO WPT (provided on the
REPORT page) will be the ABEAM WPT or the RADIAL/CIRCLE intersect waypoint, if any,
as on the F-PLN page.
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←B
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - CLOSEST AIRPORTS
FLIGHT CREW
OPERATING MANUAL
CLOSEST AIRPORTS
Ident.: DSC-22_20-60-80-00006018.0001001 / 07 APR 11
Applicable to: ALL
The CLOSEST AIRPORTS page displays the four closest airports, from the position of the aircraft,
found in the navigation database (Refer to DSC-22_20-50-10-25 Closest Airports Pagesfor the page
description), and the 5th airport, as selected by the crew.
For each airport, the FM computes:
‐ The BRG /DIST /ESTIMATED UTC from the position of the aircraft to the corresponding airport.
‐ The EFOB at the airport, assuming an EFFECTIVE WIND (defaulted or entered by the pilot).
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
OTHER FUNCTIONS - CLOSEST AIRPORTS
When the CLOSEST AIRPORTS page 2 is selected, the list of airports is automatically
frozen, as indicated on the page.
The FUEL/TIME predictions to the closest airports use simplified assumptions:
‐ Managed speed profile in cruise, with the effective wind from the CLOSEST AIRPORTS page 2. In
case of EO, Engine Out condition is considered.
‐ Continuous descent from CRZ FL down to the airport elevation.
Note:
In case SELECTED SPD is used, the CLOSEST AIRPORTS page still provides good use
to choose the applicable closest airport for diversion purposes. However, when SELECTED
SPD is significantly different from MANAGED SPD, the predictions in terms of time and fuel
must be disregarded since they are misleading.
The predictions may then be checked on the SEC F-PLN.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←A
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - TIME MARKER
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_20-60-90-00006019.0001001 / 16 FEB 11
Applicable to: ALL
The crew can enter a time marker in the F-PLN A or B page. Once entered, the FMGS displays a
pseudo waypoint along the flight plan on the MCDU and on the Navigation Display. This pseudo
waypoint shows the predicted location of the aircraft at the entered time.
HOW TO INSERT A TIME MARKER
Ident.: DSC-22_20-60-90-00009522.0001001 / 01 OCT 12
Applicable to: ALL
WRITE the time marker in the scratchpad. The entry format is HHMM.
SELECT any left key of the F-PLN A or B page, to insert the time marker in the active flight plan.
The time marker is inserted in the flight plan according to time criteria, irrespective of the key chosen
for entry.
Up to four time markers may exist at a time. An attempt to enter a fifth time marker will cause the
“TIME MARKER LIST FULL” message to appear on the scratchpad.
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - TIME MARKER
The FMGS updates the time marker position with the predictions.
When the current clock time equals or exceeds the time marker entry, the FMGS sequences the time
marker (even in preflight).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-22_20-60-90 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - STEP ALTS
FLIGHT CREW
OPERATING MANUAL
STEP CLIMB/STEP DESCENT
Ident.: DSC-22_20-60-100-00006020.0012001 / 12 APR 17
Applicable to: ALL
The STEP ALTS function enables to define the successive cruise Flight Levels. The optimum
position to initiate a climb, from the initial (or current) cruise Flight Level to the next one, can also be
determined.
PRINCIPLE
GEOGRAPHIC STEPS
Up to four geographic steps may be defined on the STEP ALTS page. These steps are initiated
at the geographical position, along the F-PLN.
Rules
‐ The minimum step size is 1 000 ft.
‐ A Step Climb (S/C ) cannot follow a Step Descent (S/D).
‐ A STEP is automatically cleared, if:
• The S/C (S/D) is sequenced without any level change done by the crew.
• The crew achieves a LAT REV , which deletes the associated waypoint from the F-PLN
• By EO condition.
‐ A STEP is manually cleared:
• On the STEP ALTS page, by CLEARING the corresponding field.
• On the F-PLN page, by CLEARING the (S/C ) or (S/D) pseudo-waypoints.
‐ A STEP entry is IGNORED, if the remaining CRZ distance is less than about 50 NM.
‐ Once the steps are inserted in the F-PLN, they are displayed:
‐ On the MCDU , as (S/C ), (S/D ), (T/C ), (T/D) pseudo waypoints.
‐ On the ND, by associated , , , white symbols.
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12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - STEP ALTS
OPTIMUM STEP
When geographic steps are inserted, or an altitude is entered, the FM proposes an OPTIMUM
STEP start of climb position for the first step climb altitude ahead. Predicted FUEL and TIME
savings are displayed when calculated to be greater than 100 kg or 1 min respectively. If no
savings are found, no optimum step is proposed.
The OPT STEP is not automatically inserted. The crew must insert it, if appropriate. Once
inserted, the OPT STEP point (OPT) becomes a fixed geographical point.
If some F-PLN parameters are subsequently changed (e.g. winds, new waypoints), an update
of the optimum position relative to the previous one may be proposed. If savings exist, this new
optimum may be inserted to replace the previous optimum step point.
Once an OPT STEP is inserted in the F-PLN , and the crew achieves a lateral F-PLN revision,
the FM keeps the (OPT ) along the new F-PLN, at the same distance from the aircraft’s position,
as previously determined.
Rules
‐ The OPT STEP is only computed by the FM , if data required for the prediction
computation are inserted : F-PLN , CRZ FL , CI, GW , CG at least.
‐ The search of the OPT STEP begins 20 NM beyond (T/C) before Cruise, or ahead of the
aircraft’s position.
‐ The search of the OPT STEP ends 20 NM before the next STEP POINT, or 300 NM before
the (T/D).
‐ Only one OPT STEP is computed at a time.
Guidance
When reaching the step point, the steps must be initiated by the crew by selecting the new
CRZ FL , and pressing the FCU ALT selector knob. If sequenced without any crew action, the
step is automatically deleted.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - STEP ALTS
If the crew initiates the step:
‐ The CRZ FL is automatically reassigned to its new value.
‐ The guidance is
THR CLB /CLB for a step climb.
THR IDLE/DES with V/S = -1 000 ft/min for a step descent.
STEP ENTRY
The STEP ALTS page is either accessed from
the
:
‐ The VERT REV page, or
‐ PERF CRZ page.
FOR GEOGRAPHIC STEP:
PRESS the F-PLN or PERF key.
SELECT vertical revision at a cruise waypoint.
SELECT the STEP ALTS prompt.
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12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - STEP ALTS
WRITE the ALT /WPT in the scratchpad, and ENTER it in [1L] to [4L].
Note:
‐ The position may be a waypoint ident, PBD, PD.
‐ The pilot may enter FL 350/LMG/–20. The FM will compute the geographic step
20 NM before LMG to FL 350.
‐ To modify an inserted STEP:
• To modify the CRZ FL only, enter it in the left key, as “FLXXX”.
• To modify the position only, enter it in the left key, as “/XXX”.
• To modify both, modify the position first, and then the CRZ FL (it is not possible to
modify both in a single entry).
CHECK the PREDICTIONS.
FOR OPTIMAL STEP
Once all geographical steps are inserted, and the predictions are available, the STEP ALTS
page displays the FUEL/TIME savings for the first step climb. If no significant savings are
predicted, the NO OPTIMAL message is displayed.
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - STEP ALTS
To INSERT the proposed OPT STEP displayed in [5L]:
SELECT the INSERT* prompt in [6R].
The computed (OPT ) step replaces the initially inserted step position, and is then considered
at a fixed geographic position. Savings are no longer displayed, and the UPDATE* prompt
replaces the INSERT* prompt. This prompt allows the crew to update the (OPT ) step position,
considering possible F-PLN or inserted wind changes.
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - STEP ALTS
If pressed, a new OPT point is proposed, with the associated SAVINGS and INSERT prompt, or
NO OPTIMAL.
UPDATE prompt has been pressed, the new OPT STEP point gives additional savings:
THERE ARE ONLY 2 CRZ FL S IN THE F-PLN:
The pilot may obtain the OPT position of the STEP point, as follows:
INSERT the initial cruise FL on the INIT A page.
ENSURE that the ZFW , ZFWCG and BLOCK fuel are inserted on the INIT B page.
WRITE the new CRZ FL in the STEP ALTS page, in the [1L] field.
Distance and time to optimum point and fuel/time saving are displayed.
CHECK the fuel and time savings and prediction on the [5R] field.
Savings are computed by comparing the entered step altitude, and the origin altitude of the
step.
INSERT, if suitable.
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
OTHER FUNCTIONS - STEP ALTS
No OPT STEP is available in the SEC F-PLN.
MESSAGES
Messages may be displayed in the DIST/TIME field:
‐ “ABOVE MAX”, if the inserted step altitude exceeds the REC MAX ALT.
The “STEP ABOVE MAX FL” scratchpad message is associated to the “ABOVE MAX”
message.
‐ “IGNORED”
This message is displayed in the following cases:
• Step climb is located prior to the top of climb, or after the top of descent.
• Step end is at less than 50 NM from the top of descent. An optimum step point, < 200 NM
from top of descent, cannot be inserted
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - STEP ALTS
‐ “STEP AHEAD”, when the distance to the step point is less than 20 NM . A “STEP AHEAD”
scratchpad message is also displayed.
The following message may be displayed in the scratchpad:
‐ “NOT ALLOWED”, if:
‐ Four steps already exist in the F-PLN, and an additionnal entry is attempted.
‐ Any attempt to enter a step at the FROM waypoint, or at a pseudo waypoint is done.
‐ Two consecutive steps are entered at the same waypoint (e.g. step climb after step
descent).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-22_20-60-100 P 8/8
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - REQUIRED TIME OF ARRIVAL (RTA)
GENERAL
Ident.: DSC-22_20-60-110-00006021.0001001 / 01 OCT 12
Applicable to: ALL
A time constraint (RTA) may be assigned at any waypoint of the F-PLN, downpath of the origin and
the FROM waypoint. It can be an ”AT”, “AT OR BEFORE”, or “AT OR AFTER” constraint.
The FMS computes a new managed speed profile from the aircraft position to the constrained
waypoint, in order to match the 30 s difference (ΔT) between the time predicted at the constrained
waypoint and the RTA. This modified managed speed profile can be checked using the speed
prediction, displayed for each waypoint of the F-PLN page.
The RTA function uses a speed range between Green Dot speed and VMO - 10 (or MMO - 0.02).
When the constrained waypoint is sequenced, the ECON SPD/MACH is resumed unless the
constrained waypoint is located in a descent segment.
Note:
The FM does not compute a new managed speed profile when a RTA is entered in the
descent profile while the aircraft is in cruise within 40 NM from the top of descent.
The time constraint is inserted on the RTA page. A time constraint may be inserted at any waypoint
of the primary or secondary flight plan.
If an engine-out condition is detected, the time constraint is automatically deleted and RTA
DELETED message on scratchpad.
If the aircraft enters a holding pattern, the downpath time constraint is deleted.
Once inserted in the F-PLN , the RTA is displayed in magenta on the F-PLN page, as long as no
predictions are available.
Once the predictions are available, the time constraint is replaced by the new predicted time at the
associated waypoint, and highlighted by a star: (*)
‐ The (*) is magenta, if the time constraint is matched with the 30 s criteria.
‐ The (*) is amber, if the time constraint is missed.
Time constraint matching criteria:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-22_20-60-110 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
OTHER FUNCTIONS - REQUIRED TIME OF ARRIVAL (RTA)
ΔT is the time difference between the time predicted at the constrained waypoint and the
RTA.
TIME CSTR ENTRY
PRESS the F-PLN key.
SELECT vertical revision at the revised waypoint.
SELECT the RTA key.
ENTER a waypoint at which a time constraint is to be defined.
WRITE the time constraint (+/–HHMMSS) into the scratchpad and ENTER
The display automatically reverts to the F-PLN A page.
Note:
‐ The TIME CSTR can be directly cleared on the F-PLN A page, using the CLR key.
‐ The time constraint is automatically deleted in the following cases:
• Engine out, or
• When entering a holding pattern, or
• In case of Go-Around, or
• A time constraint is entered at another waypoint, while another time constraint
already exists.
A scratchpad “RTA DELETED” message is displayed.
ESTIMATED TAKEOFF TIME (ETT)
Ident.: DSC-22_20-60-110-00009523.0001001 / 23 JUN 15
Applicable to: ALL
The Estimated Takeoff Time (ETT) may be entered by the pilot during the preflight phase at the
origin airport. This time is used as the initialization time for predictions.
The entry is accepted in the preflight phase, if the ETT is greater than the clock time.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-22_20-60-110 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - REQUIRED TIME OF ARRIVAL (RTA)
FLIGHT CREW
OPERATING MANUAL
PROCEDURE
PRESS the F-PLN key
SELECT a vertical revision at origin
SELECT the RTA page
WRITE the ETT into the scratchpad, and ENTER in the ETT field.
The display automatically reverts to the F-PLN A page.
Note:
‐ If the current time exceeds the ETT entry, the CLK IS TAKE OFF TIME message is
displayed ; the ETT is replaced by the clock time.
‐ At takeoff, the takeoff time is automatically updated using the actual clock time.
‐ An ETT entry is automatically deleted, if the origin airport is modified, or if the clock is
inoperative.
‐ If a time constraint is entered at a waypoint in the F-PLN , the takeoff time required to
match the constraint is automatically computed by the FM. This result is displayed in
magenta as ETT at the origin.
USE OF TIME/ETT CONSTRAINT
During preflight
:
After Takeoff
:
‐ If an ETT has been entered, time predictions are based on the
entered value (or clock time, if greater).
‐ If both an ETT and a time constraint have been entered, time
predictions are based on the entered ETT value (or clock time, if
greater). The managed speed profile is computed to match the time
constraint, as closely as possible, using a pseudo cost index value.
(Not displayed).
‐ If only a time constraint has been entered:
• Optimum speeds are computed to determine the ETT, so as to
satisfy the time constraint.
• If necessary, flight time (based on optimum speeds) plus clock time
(current) is greater than the time constraint ; optimum speeds are
modified to match the time constraint as closely as possible.
The predictions are based on the current time.
Speeds are adjusted to satisfy the time constraint.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-22_20-60-110 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - REQUIRED TIME OF ARRIVAL (RTA)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_20-60-110 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - EQUITIME POINT
FLIGHT CREW
OPERATING MANUAL
EQUITIME POINT
Ident.: DSC-22_20-60-120-00006015.0001001 / 16 MAR 11
Applicable to: ALL
The equitime point page displays the ETP , computed along the F-PLN route between
two referenced positions (airports, waypoints or navaids), defined by the pilot (Refer to
DSC-22_20-50-10-25 Equi - Time Point Pagefor the page description).
When first accessing the page, the FMS proposes origin and destination airfields, as defaulted
positions.
The pilot may overwrite these two positions and insert the wind in their vicinity at the applicable CRZ
FL.
The FMS then computes the resulting ETP , using the managed or selected speed, and blending the
forecasted winds along the F-PLN route with the inserted winds.
The FMS provides:
‐ TIME and DIST from the aircraft position (or origin on ground) to the ETP
‐ The BRG /DIST from the ETP to the defined positions
‐ TIME overhead each position, assuming the aircraft flies from the present position to the defined
position via the ETP
‐ (ETP ) pseudo waypoint is displayed on the ND along the F-PLN
‐ ETP location in relation to the subsequent waypoint.
EQUITIME POINT ENTRY
Ident.: DSC-22_20-60-120-00009536.0001001 / 01 OCT 12
Applicable to: ALL
PRESS the DATA key.
SELECT the EQUI-TIME POINT prompt.
The EQUI-TIME POINT page is displayed. The origin and destination airports are used by default.
ENTER the REF POINT 1 in the [1L] field.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - EQUITIME POINT
ENTER the associated wind in the [2L] field.
The wind to be inserted is the wind in the vicinity of the reference point at the CRZ FL.
ENTER the REF POINT 2 in the [3L] field.
ENTER the associated wind in the [4L] field.
The system displays the ETP location with regards to the next waypoint of the active flight plan
following the ETP in the [5R] field, and the A/C TO (ETP) predictions in the [6R] field.
Note:
‐ The ETP pseudo-waypoint is not displayed on the MCDU F-PLN page. In order to easily
locate it, or when closing the applicable ETP , the TIME MARKER may be used; this
allows the crew to visualize it in advance on the F-PLN page or, to prepare the next
applicable ETP on the Equi-time Point page
‐ The ETP is computed using speed according to the current mode (managed or selected).
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
GENERAL
Ident.: DSC-22_20-60-130-00012906.0011001 / 24 FEB 14
Applicable to: ALL
The MCDU NAV B/UP allows to link a MCDU to its associated IRS in order to allow the flight crew to
monitor the navigation and to be provided with some basic flight planning functions in case of FM 1 +
2 failure.
CAUTION
The MCDU NAV B/UP is to be used only in case of FM 1 + 2 failure. It can be
selected temporarily in case of FM1 or 2 only failure, in order to ensure that the
function is available on the failed side.
When in MCDU NAV B/UP on both sides, one FG at least must be available to
engage AP and A/THR.
The MCDU NAV B/UP function provides:
‐ Aircraft position using onside IRS or IRS 3
‐ Aircraft position using GPIRS position
‐ F-PLN as memorized in the MCDU
‐ F-PLN display on ND
‐ F-PLN automatic sequencing
‐ Limited lateral revisions
‐ Mag (True) bearing depending on the pilot selection, from aircraft position to the TO WPT and
associated distance
‐ True track between waypoints
‐ Time estimates computed with current GS from onside IRS
‐ Total time and distance to destination
The following features are not provided:
‐ No DATA BASE available:
• No autotuning, NAVAID S must be selected on RMP
• No radio position
• No EFIS CTL PANEL options
• No LDG ELEV (must be manually selected on overhead panel).
‐ No performance data:
• No CLB /DES /APP NAV/FINAL modes
• No SPEED MANAGED
• No automatic SPD/MACH change over.
‐ Most of predictions are lost:
• No EFOB
• No XTRA
• No ETA at DEST.
‐ No multiple lateral F-PLN
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FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
FLIGHT CREW
OPERATING MANUAL
‐ No AP/FD managed modes
‐ No crosstalk between MCDU s: F-PLN revisions have to be achieved on both MCDUs.
BACK UP NAV SELECTION
Applicable to: ALL
Ident.: DSC-22_20-60-130-A-00012907.0011001 / 16 FEB 11
FM F-PLN DOWNLOAD IN MCDU
While BACK UP NAV is not active, the FM downloads permanently a condensed form of the
F-PLN in the MCDU.
Downloaded information include:
‐ Waypoint position
‐ Waypoint identifier
‐ Leg type
‐ Discontinuity
‐ Overfly
‐ Turn direction.
Heading legs, course to fix legs, ..., computed INTCPT positions, pseudo waypoints, ..., cannot be
downloaded.
They are replaced by discontinuities.
Maximum of 150 waypoints are downloaded.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-22_20-60-130 P 2/12
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
Ident.: DSC-22_20-60-130-A-00012908.0011001 / 14 MAY 12
EXAMPLE OF DOWNLOADED F-PLN
In that procedure, all the legs are coded as CF (Course to Fix) legs. This explains all the
discontinuities resulting in the B/UP F-PLN.
These discontinuities may be cleared.
When the second FM fails
REENGAGE and SELECT the required AP and A/THR modes (if disconnected).
SELECT the NAV B/UP prompt on both MCDU.
SELECT NAV on both RMP
Tune the required navaids
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-22_20-60-130 P 3/12
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-22_20-60-130 P 4/12
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
‐ Only MCDU MENU
• F-PLN key
• PROG key
• DIR key
‐ B/UP F-PLN page
• B/UP PROG page
• B/UP IRS 1, 2, 3 pages are available when BACK UP NAV is selected.
‐ B/U GPS (if GPS is installed).
BACK UP NAV OPERATION
Applicable to: ALL
Ident.: DSC-22_20-60-130-B-00012909.0011001 / 16 FEB 11
AP AND A/THR
One FG at least must be available to allow the engagement of AP /FD and A/THR . All FM
managed modes are lost as well as managed speed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_20-60-130 P 5/12
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
As a consequence:
‐ LAT F-PLN is flown in HDG /TRK modes
‐ VERT F-PLN is flown in OPEN/V/S /FPA modes
‐ SPD TARGET is manually SELECTED on the FCU
‐ SPD /MACH crossover is manually SELECTED on the FCU.
It is recommended to use the TRK /FPA modes:
SELECT the required TRK on FCU at waypoint sequencing (as no AP /FD coupling exists in NAV
B/UP). F-PLN sequencing is automatic.
MONITOR the track of the next leg prior reaching the TO waypoint (track between TO and next
waypoints is true track).
ADJUST the track to follow the F-PLN with X-TRK = 0
USE OP DES or FPA to descend as suitable.
FPA allows easy altitudes predictions:
DNM = ▵(FL )/FPA°
Ident.: DSC-22_20-60-130-B-00012910.0011001 / 16 FEB 11
NAVIGATION MONITORING
The navigation accuracy check must be achieved periodically using the same principle as with FM
navigation:
COMPARE computed data with raw data
SELECT ON RMP the applicable navaid
PRESS the [PROG] key
B/UP PROG page is displayed
WRITE in the scratchpad then ENTER the navaid LAT /LONG
SELECT associated navaid needle on the EFIS control panel.
COMPARE computed BRG /DIST with RAW DATA on ND
‐ If the crosscheck is POSITIVE the ND may be used in ROSE NAV /MAP modes with raw data
‐ If the crosscheck is NEGATIVE the ND must be used in ROSE VOR /ROSE ILS modes.
Note:
B/UP IRS and B/UP GPS pages may also be used to check the position.
Ident.: DSC-22_20-60-130-B-00012911.0011001 / 16 FEB 11
FLIGHT PLANNING
The following revisions may be achieved:
‐ WPT insertion/deletion
‐ OVERFLY insertion/deletion
GLG A318/A319/A320/A321 For A/C: HC-CRU
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
‐ DIR TO a waypoint
‐ CLR waypoints/discontinuities.
Waypoint identifiers are either published waypoint identifiers if present in the MCDU active F-PLN ,
or coded LAT /LONG identifiers resulting from flight crew entries.
All flight planning functions are directly applied on active F-PLN without LAT REV page.
Ident.: DSC-22_20-60-130-B-00012912.0011001 / 23 JUN 15
WAYPOINT INSERTION
Waypoint insertion into the F-PLN is performed via the B/UP F-PLN page by selecting the line
key adjacent to the desired point of insertion, whenever a pre-existing waypoint identifier or valid
IDENT /LAT /LONG or LAT /LONG entry is displayed in the scratchpad.
Any waypoint entry which causes the number of legs in the route to exceed the maximum allowed
results in the “F-PLN FULL” message.
Note:
‐ If the inserted waypoint is entered only with LAT /LONG, its identifier would be :
N48E001
‐ If the flight crew writes a waypoint IDENT /LAT /LONG with an IDENT already used in
the F-PLN, a message “NOT ALLOWED" is displayed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
Ident.: DSC-22_20-60-130-B-00012913.0011001 / 16 FEB 11
WAYPOINT DELETION
Waypoint and discontinuity may be deleted from the B/UP F-PLN page by using the CLR key.
Ident.: DSC-22_20-60-130-B-00012914.0011001 / 16 FEB 11
OVERFLY INSERTION/DELETION
Same as for the FM F-PLN.
Ident.: DSC-22_20-60-130-B-00012915.0011001 / 23 JUN 15
DIRECT TO A WAYPOINT
The DIR TO function operates as for the normal F-PLN, except that RADIAL INTERCEPT and
ABEAM functions are not available.
PRESS the DIR key.
WRITE LAT /LONG (or IDENT /LAT /LONG) on the scratchpad then INSERT in [1L].
SELECT the correct track on the FCU in order for the aircraft to turn toward the new TO waypoint.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
In this example, the entered DIR TO waypoint is a LAT /LONG waypoint.
Due to the fact that this new waypoint is not identical to any waypoint in the F-PLN, a direct leg to
that waypoint is created and followed by a discontinuity.
When the DIR TO function is completed, the B/UP F-PLN page is displayed with the DIR TO
waypoint as the TO waypoint and the T-P waypoint as the FROM waypoint.
If a DIR TO function is achieved for a waypoint that belongs to the B/UP F-PLN , no F-PLN
discontinuity is created.
Note:
‐ In case of a DIR TO waypoint associated with an OVERFLY condition, the OVERFLY
is kept.
Ident.: DSC-22_20-60-130-B-00012916.0011001 / 14 MAY 12
CLR WAYPOINT/DISCONTINUITY
CLR as for normal operation.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_20-60-130-B-00012917.0011001 / 23 DEC 14
APPROACHES
‐ ND display selection rule
As per normal operation, it depends upon the result of NAV ACCY CROSS CHECK.
Furthermore it depends also whether the F-PLN is complete, including the approach.
F-PLN
Complete with
appropriate approach
Incomplete
NAV ACCY CHECK
Positive
Negative
Positive or Negative
PF
ND
PM
ARC or ROSE NAV
Ref navaid Raw data
ARC or ROSE NAV or
ROSE VOR /ILS
ROSE VOR /ILS
Ref Navaid Raw Data
ROSE VOR /ILS
Ident.: DSC-22_20-60-130-B-00012918.0011001 / 16 FEB 11
END OF DESCENT
ADJUST manually the landing elevation on the overhead panel.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
SET the MDA on the standby altimeter.
Ident.: DSC-22_20-60-130-B-00012919.0011001 / 23 JUN 15
NON ILS APPROACHES
SELECT on RMP the approach reference navaids.
The autopilot and flight director available modes are TRK -FPA and HDG/VS
The autothrust available speed target is selected speed.
Ident.: DSC-22_20-60-130-B-00012920.0011001 / 16 FEB 11
ILS APPROACHES
Only CAT 1 approaches may be flown since the DH indication is not available.
CHECK the ILS frequency and course on the RMP.
PUSH the LS pb on the EIS control panel.
The autopilot and flight director available modes are APP (LOC – G/S – LAND)
The autothrottle available speed target is selected speed
CHECK VAPP in the QRH.
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - MCDU BACK UP NAVIGATION
Intentionally left blank
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - DESCENT PROFILE OPTIMIZATION (IF INSTALLED)
DESCENT PROFILE OPTIMIZATION
Ident.: DSC-22_20-60-150-00019723.0001001 / 07 JUN 16
Applicable to: ALL
During the idle segment in descent, margins are added to the idle thrust to have more flexibility
to maintain the aircraft on the computed descent profile in case of external perturbations such as
important wind change.
The Descent Profile Optimization (DPO ) optimizes the computed vertical profile. It decreases
the idle thrust margins in descent and the speed margins in approach to reduce fuel burn in descent
phase.
With DPO , the computed vertical profile is steeper. The T/D is reached later. Before the final
approach, the deceleration level-off is shorter.
With DPO , along the idle segment, without altitude constraint, the descent profile computed by
the FMS is the same as the one flown in OPEN DES mode. Therefore, reverting in OPEN DES mode
during the descent does not change the descent rate.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OTHER FUNCTIONS - DESCENT PROFILE OPTIMIZATION (IF INSTALLED)
With DPO , the FMGS has less flexibility to maintain the aircraft on the computed vertical profile
in case of difference between wind entry and effective wind. Therefore, the accurate winds have to
be entered in the FMGS before descent.
During descent, the VDEV should be closely monitored. If the aircraft goes above the flight descent
profile, the flight crew may have to extend speed brakes to go back on the computed descent profile.
If ENG ANTI ICE or ENG ANTI ICE + WING ANTI ICE are used during descent (inducing an
increased idle thrust), the flight crew may have to extend speed brakes to stay on the computed
descent profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←A
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
AOC FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLAN INITIALIZATION THROUGH ACARS
Ident.: DSC-22_20-70-00000956.0007001 / 01 OCT 12
Applicable to: ALL
REQUEST FOR ACTIVE FLIGHT PLAN INITIALIZATION BEFORE ENGINE START
Before engine start, the crew may request a route for the active flight plan. When the route is
received, “AOC ACT F-PLN UPLINK” message is displayed on the MCDU indicating that the flight
plan has been received and automatically inserted.
After engine start, it is not possible to initialize directly the active flight plan since the received
flight plan is automatically routed into the secondary, and the MDCU displays “AOC SEC F-PLN
UPLINK”.
PROCEDURE
PRESS the INIT REQUEST * prompt.
The star (*) disappears, all data fields are dashed except:
‐ CO RTE , FLT NBR if previously displayed and
‐ Ddefault values.
The star is not displayed when the FMGS cannot communicate with the ACARS. No request
can be sent.
When an active flight plan exists, INIT REQUEST prompt is removed from the active INIT page
and no request can be sent for the active flight plan. If a flight plan is entered manually after the
request, the uplink message is routed to the secondary.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
AOC FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
REQUEST FOR SECONDARY FLIGHT PLAN
A request for a secondary flight plan can be initiated anytime. Any flight plan received after engine
start is automatically routed into the secondary flight plan.
When the flight plan is received, a message “AOC SEC F-PLN UPLINK” is displayed on the
MCDU scratchpad.
Before engine start, and if the SEC F-PLN is empty, any uplinked flight plan is automatically
inserted into the secondary flight plan, and no flight crew action is required.
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
AOC FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
After engine start, or if the SEC F-PLN is not empty, the flight crew must manually insert the
uplinked flight plan via INSERT UPLINK prompt.
PROCEDURE TO INSERT OR REJECT A SECONDARY FLIGHT PLAN
When the uplink message is received, the INIT REQUEST prompt of the INIT A page is
replaced by INSERT UPLINK (2R field). Pressing the 2R key will insert the flight plan into the
secondary. Clearing the prompt will reject it.
If a temporary flight plan or a DIR TO is in progress, the uplink insertion is not accepted until the
temporary flight plan or the DIR TO is completed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_20-70 P 3/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
AOC FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
TAKEOFF DATA
Applicable to: ALL
Ident.: DSC-22_20-70-A-00000957.0001001 / 15 FEB 11
GENERAL
The takeoff data may be requested in preflight or done phase for the active flight plan only.
It is always associated with the active flight plan message.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-22_20-70 P 4/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
AOC FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_20-70-A-00000959.0001001 / 23 JUN 15
PROCEDURE TO INSERT UPLINK TAKEOFF DATA
PRESS the 6L key “RECEIVED TO DATA” when the message TAKEOFF DATA UPLINK is
displayed.
This displays the uplink data on 2 different pages:
UPLINK MAX TO DATA
UPLINK FLX TO DATA
SELECT the data corresponding to the thrust to be used (MAX or FLEX) by pressing [4R].
SELECT the active runway data by slewing the pages (1/4... 4/4).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-22_20-70 P 5/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
AOC FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
PRESS the [6R] key “INSERT UPLINK”.
UPLINK MAX TO DATA and UPLINK FLX TO DATA pages are not modifiable.
If the takeoff data displayed on this page are not relevant to the active runway entered
in the flight plan , the INSERT UPLINK prompt is not displayed.
When the takeoff data have been inserted , the PERF TO page is amended of the new
data.
WIND DATA
Applicable to: ALL
Ident.: DSC-22_20-70-B-00000961.0001001 / 01 OCT 12
REQUEST FOR WIND DATA
To send a wind request, press the “WIND REQUEST” selection key of any wind pages. This
request is automatically sent to the ground for one or more flight phases and for the selected flight
plan (primary or secondary). The content of the wind request message is not dependent on the
selected wind page (CLIMB, CRUISE or DESCENT) but on the flight phase in progress.
‐ For active flight plan or secondary flight plan that is a “COPY ACTIVE”, a wind request sent by
the crew:
• during preflight or takeoff phase, initiates a demand for climb, cruise, descent and alternate
winds.
• during climb and cruise phase, initiates a demand for cruise, descent and alternate winds.
• during descent/approach and go around, no wind request is possible.
‐ For secondary flight plan that is not a “COPY ACTIVE” there is no restriction linked to flight
phase.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_20-70 P 6/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
AOC FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
Before engine start, and if data has not been entered in any WIND page for the flight plan,
the uplinked wind data is automatically inserted into the flight plan, and no flight crew action is
required.
If the uplinked wind message is received after engine start, or if data has been entered in any
WIND page of the flight plan, the flight crew must manually insert the uplinked wind data via the
INSERT UPLINK prompt.
When the amber star following the “WIND REQUEST” is not displayed, the FM is not able to
communicate with the ACARS and the pilot cannot send any request.
Ident.: DSC-22_20-70-B-00000962.0020001 / 14 MAY 12
PROCEDURE TO INSERT WIND DATA
When the uplink message is received, the 2R field is modified, the amber “WIND REQUEST” is
replaced by the blue “INSERT UPLINK*”. This prompt, when pressed, enables the flight crew to
insert the uplink wind data, phase by phase.
To access, review, insert or delete the uplink wind data of other phases, the crew uses “NEXT
PHASE” or “PREV PHASE” key.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-22_20-70 P 7/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
AOC FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
If the crew is not satisfied with the uplink winds, the flight crew will delete the winds, phase
by phase clearing the “INSERT UPLINK” prompt. This will delete all the uplinked winds of the
selected flight phase.
CLIMB WIND PAGE
When a request is pending, the history WIND page cannot be accessed.
When the climb phase is active, the crew cannot request neither modify the climb winds of the
active flight plan or secondary flight plan if it is a copy active.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-22_20-70 P 8/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
AOC FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
CRUISE WIND PAGE
A wind request sent during cruise phase will apply for downpath waypoints of the cruise,
descent, approach and alternate phases.
‐ If the uplink message contains more data and waypoints than the flight plan, the winds at
extra waypoints are not considered and automatically discarded. This is transparent to the
pilot
‐ Clearing the INSERT UPLINK* prompt deletes all uplink wind data of the cruise phase.
Cruise page reverts to the previous data.
Note:
During cruise, whenever uplink wind data is received and not inserted or cancelled on
the CRUISE WIND page, access to the DIR TO function is not possible. The “WIND
UPLINK EXISTS” message is displayed on the MCDU scratchpad. Insert or cancel the
uplinked wind message first and then access the DIR TO function.
DESCENT WIND PAGE
The procedures to insert, review or delete descent winds during preflight, climb or cruise phase
are described in the above wind general procedure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-22_20-70 P 9/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
AOC FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
If the alternate wind is not available, dashes are displayed in the field.
In descent, approach or go around phases, the pilot cannot request or modify the descent winds
of the active flight plan or secondary flight plan if it is a “COPY ACTIVE”.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
DSC-22_20-70 P 10/10
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PRINT FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
PRINT FUNCTION
Ident.: DSC-22_20-80-00000964.0009001 / 18 MAR 11
Applicable to: ALL
The PRINT function allows various reports to be printed either automatically (when linked to
ACARS or ATSU ) or manually.
The manual PRINT function allows printing of FM-generated flight reports and additional data:
F-PLN
INITialization data
T.O.
Data
WIND
Data
PREFLIGHT
REPORT
IN FLIGHT
REPORT
POSTFLIGHT
REPORT
A detailed description of the PRINT FUNCTION pages is provided in Refer to DSC-22_20-50-10-25
Print Function Pages.
The print function is available if ACARS or ATSU are available or not.
The various flight reports contain most of the prediction information required by the flight crew to
monitor the progress of the flight. The resulting documents can therefore be used as realistic master
documents, based on the latest data provided by the flight crew to the computer, in terms of ATC
clearances and weather information.
PRINT FUNCTION ACCESS
Ident.: DSC-22_20-80-00000965.0004001 / 01 OCT 12
Applicable to: ALL
The PRINT FUNCTION page is accessed:
‐ From the DATA INDEX A PAGE, or
‐ From the AOC FUNCTION page (if ACARS ).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_20-80 P 1/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PRINT FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
Note:
For an automatic printing, “time” is the time of the reception of the message. For a manual
printing, “time” is the time of the print request.
ON GROUND BEFORE ENGINE START
Ident.: DSC-22_20-80-00000966.0001001 / 23 JUN 15
Applicable to: ALL
When the overall F-PLN data (lateral, vertical including winds, steps, constraints) and the ZFW and
ZFWCG values have been inserted:
SELECT the FUEL PLANNING prompt [3R],
If the computed BLOCK fuel does not correspond to the actual block fuel required for the
flight:
ENTER the actual block required for the flight in the [2R] field,
PRINT the PREFLIGHT report.
The flight crew may then use the PREFLIGHT report to monitor the progress of the flight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_20-80 P 2/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PRINT FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
Note:
Before printing the PREFLIGHT report, the flight crew must check that the F-PLN is
complete (all F-PLN discontinuities must be cleared) and that all the F-PLN elements
(including winds, steps, constraints, alternate airport) have been inserted, in order to
obtain an accurate PREFLIGHT report.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
DSC-22_20-80 P 3/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PRINT FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
EXAMPLE (FM PREFLIGHT REPORT)
Ident.: DSC-22_20-80-00000967.0001001 / 18 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
DSC-22_20-80 P 4/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PRINT FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
IN FLIGHT
Ident.: DSC-22_20-80-00000968.0007001 / 18 MAR 11
Applicable to: ALL
Once the aircraft has reached the CRZ FL once, all the latest ATC clearances have been inserted in
the FM, when all the WINDS/STEPS have been properly updated:
ACCESS the PRINT FUNCTION page
PRINT the INFLIGHT REPORT
The inflight report provides the list of all the overflown F-PLN waypoints (HISTORY VALUES)
with their associated data (Time, ALT, Fuel, ...), and the predictions to all the downpath waypoints
(PREDICTED VALUES).
This new document replaces the PREFLIGHT report, since it carries all the latest expected F-PLN
changes. It is the new applicable master document used to monitor the progress of the flight.
The inflight report will be printed after each important F-PLN modification.
Note:
If the selected Fuel Unit option is pounds, the HISTORY FOB values may be incorrectly
printed in tons on the INFLIGHT REPORT. The CURRENT and PREDICTED FOB values,
however, are correctly printed in pounds.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
DSC-22_20-80 P 5/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PRINT FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
EXAMPLE (FM INFLIGHT REPORT)
Ident.: DSC-22_20-80-00000969.0001001 / 18 MAR 11
Applicable to: ALL
Note:
In case of a major failure such as an engine out, a new print will be done when time
permits.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
DSC-22_20-80 P 6/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PRINT FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
REACHING THE GATE AFTER LANDING
Ident.: DSC-22_20-80-00000970.0007001 / 18 MAR 11
Applicable to: ALL
The POSTFLIGHT REPORT gives a complete list of all the overflown waypoints during the flight
(HISTORY VALUES).
Furthermore it provides:
‐ FUEL/TIME summary
‐ IRS Drift and G/S
When at the gate, after engine shutdown:
‐ ACCESS the PRINT FUNCTION page
‐ PRINT the POSTFLIGHT REPORT
Note:
If the selected Fuel Unit option is pounds, the HISTORY FOB values may be incorrectly
printed in tons on the POSTFLIGHT REPORT.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
DSC-22_20-80 P 7/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
PRINT FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
EXAMPLE (FM POSTFLIGHT REPORT)
Ident.: DSC-22_20-80-00000971.0001001 / 18 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
DSC-22_20-80 P 8/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ABNORMAL OPERATIONS - FMGC RESET
AUTOMATIC FMGC RESET AND RESYNCHRONIZATION
Applicable to: ALL
Ident.: DSC-22_20-90-10-A-00012661.0001001 / 07 MAR 13
FM RESET
When the FM software cannot work properly or receives instructions to perform impossible
operations, it automatically resets itself. A resynchronization with the other FM always follows.
When the reset is a minor one, the system will recover by itself. One single reset lasts 2 to 3 s
maximum followed by 25 s of resynchronization.
When the reset is a major one:
‐ Resets recur at short intervals (several in 2 or 3 min)
‐ The memories are cleared, leading to the loss of F-PLN , GW , CI , CRZ FL , MCDU -entered
speeds and NAVAIDs and to database switching.
Note:
If three dual FM resets occur in 2 min, pilot-entered data is lost. If a dual reset is
identified, it is recommended that the flight crew does not perform again the last MCDU
actions for 1 min (in order to avoid a potential second dual reset, leading to the loss of
pilot-entered data).
Ident.: DSC-22_20-90-10-A-00012662.0001001 / 10 JAN 11
FM RESYNCHRONIZATION
An FM resynchronization automatically occurs after an FM reset but it may occur independently
each time self comparisons between FM 1 and FM2 reveal discrepancies.
One single resynchronization lasts approximately 25 s.
If 5 several resynchronizations occur within 5 min, independent mode commences.
Ident.: DSC-22_20-90-10-A-00012663.0001001 / 29 SEP 15
FMGC STATUS DURING A RESET/RESYNCHRONIZATION
While a RESET/RESYNCH occurs:
‐ The ND shows “MAP NOT AVAIL”
‐ The MCDU reverts to the A/C STATUS page, with “PLEASE WAIT” displayed in the scratchpad
‐ Autotuning of Navaids (VOR , DME , ADF) are lost on the failed side
‐ AP and managed modes may be transiently lost (reversion to HDG /V/S or TRK/FPA)
‐ If the pilot presses a key while the scratchpad is showing “PLEASE WAIT”, there is no change
at MCDU level. This is normal, and the crew should not respond by pulling the MCDU circuit
breaker.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-22_20-90-10 P 1/6
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ABNORMAL OPERATIONS - FMGC RESET
Ident.: DSC-22_20-90-10-A-00012664.0002001 / 10 JAN 11
SINGLE RESET OR DUAL RESET WITH AUTORECOVERY
If the RESET/RESYNCH succeeds, all functions are recovered.
Note:
When an FMGC is recovered, its FD if previously engaged, is also recovered and its
status is displayed on the FMA.
PROCEDURE
RESELECT the convenient MCDU page.
REENGAGE managed modes and the AP.
WAIT 1 min after the “PLEASE-WAIT” message has disappeared, before engaging the AP /FD
of the failed FMGC.
If both “MAP NOT AVAIL” and “SET OFFSIDE RNG/MODE” remain displayed on one ND , or if
“OFFSIDE FM CONTROL” remains displayed, temporarily SELECT a different mode or range
on the corresponding EIS control panel.
Ident.: DSC-22_20-90-10-A-00012665.0002001 / 16 NOV 11
SINGLE LATCH
If five successive resets occur, the failing FMGC will latch, and single mode operation will start.
While failed, the following occurs:
‐ On the ND usually associated with the failed FMGC:
If the ND s are not both in the same mode or range, the associated ND displays “MAP NOT
AVAIL” and “SET OFFSIDE RNG/MODE”. If the ND s are in the same mode and range, the
associated ND displays the “OFFSIDE FM CONTROL” amber message
‐ The MCDU reverts to the MENU PAGE and shows an “FMGC TIME OUT” prompt
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_20-90-10 P 2/6
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ABNORMAL OPERATIONS - FMGC RESET
‐ If the AP and FD were previously engaged on the failed side, the AP and FD disengage and
the right-hand column of the FMA shows that the operating FD is offside. The ECAM displays
the “AP OFF” warning, and the master warning light and audio remind the pilot of the AP
disengagement.
‐ All functions are restored on the operative side.
PROCEDURE
Select the same range and mode on both ND s to give the failed ND side something to display.
Select any function key on the affected FMGC MCDU. (The page will display “OPP FMGC IN
PROGRESS”).
Both MCDU s are now driven by the other FMGC , and only one AP /FD is available. The
system works in SINGLE Mode.
Perform a manual reset of the failed FMGC, when convenient.
Ident.: DSC-22_20-90-10-A-00012666.0012001 / 10 JAN 11
DUAL RESET WITH LOSS OF DATA AND AUTORECOVERY
Three successive dual resets without result erases all pilot-entered data (F-PLN , GW , CRZ FL ,
CI...).
When FMGS recovery is obtained:
‐ Database cycle may have switched
‐ The FM position bias is lost. The FM position returns to the MIX IRS position
‐ Autotuning the VOR /DME is restored, based on the aircraft’s IRS position
‐ FMGS tuning of the ILS and ADF is not possible
‐ Lateral and vertical managed mode cannot reengage
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_20-90-10 P 3/6
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ABNORMAL OPERATIONS - FMGC RESET
‐ The “CAB PR LDG ELEV FAULT” ECAM message is displayed
‐ A map display may be lost on one ND.
PROCEDURE
When the system has recovered:
SELECT the initial database.
SELECT DIR TO the required downpath waypoint.
SELECT LAT REV at the downpath waypoint, and redefine the DESTINATION.
SELECT the FUEL PRED page, and enter GW.
SELECT the PROG page, and enter CRZ FL.
SELECT the PERF page, and enter CI.
CHECK or reengage (as appropriate) the relevant speed/Mach target and vertical mode.
Redefine the flight plan for the remainder of the flight, as the opportunity presents itself.
If both “MAP NOT AVAIL” and “SET OFFSIDE RNG/MODE” remain displayed on one ND , or if
“OFFSIDE FM CONTROL” remains displayed, temporarily SELECT a different mode or range
on the corresponding EFIS control panel.
PERFORM a NAV accuracy check, when possible.
A manual FM position update should be considered, if MIX IRS and actual positions differ by
more than 20 NM.
Ident.: DSC-22_20-90-10-A-00012668.0013001 / 17 MAR 17
DUAL LATCH
‐
‐
‐
‐
‐
Both FMGC s are inoperative. FM and FG capability are lost
Both ND s display “MAP NOT AVAILABLE”. NAVAID tuning is not performed
AP /FD , A/THR are lost
FMGC (TIME OUT) subsystem page is displayed on both MCDUs
The following messages are displayed on the ECAM:
“CAB PR LDG ELEV FAULT”
“AUTO FLT AP OFF”, if AP was engaged
“AUTO FLT A/THR OFF”, if A/THR was engaged.
PROCEDURE
FLY raw data.
TUNE necessary NAVAID s using the RMPs.
PERFORM a manual reset of both FMGCs.
If successful, refer to dual reset with loss of data and auto recovery:
Note:
A recovery will result in the loss of all pilot-entered data.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_20-90-10 P 4/6
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
ABNORMAL OPERATIONS - FMGC RESET
FLIGHT CREW
OPERATING MANUAL
If unsuccessful:
FLY raw data.
Select the NAV B/UP prompt on both MCDU DATA pages.
(Refer to DSC-22_20-60-130 General HOW TO USE, concerning navigation backup
operation).
SET the landing elevation of the destination on the overhead panel.
Note for all FMGC automatic resets
‐ A single or double FM auto-reset does not affect an ILS approach below 700 ft AGL . ILS
frequency is locked and AP /FDs remain engaged
‐ Above 700 ft , the loss of ILS tuning due to a dual reset will cause a loss of LOC and G/S ,
and the disengagement of AP s and FDs
‐ During a non ILS approach, if the master FMGC fails, AP /FD and managed modes are lost
and FDs engage in basic modes.
MANUAL FMGC RESET
Applicable to: ALL
Ident.: DSC-22_20-90-10-B-00012669.0001001 / 10 JAN 11
On rare occasions, the FMGC may require manual resetting.
If this occurs in flight, reset one FMGC at a time.
Ident.: DSC-22_20-90-10-B-00020857.0001001 / 17 MAR 17
Refer to System Reset Table - AUTO FLT
for the manual reset procedure of the FMGC.
Ident.: DSC-22_20-90-10-B-00012671.0001001 / 17 MAR 17
MANUAL RESET OF BOTH FMGC
When the aircraft is on ground with the engines stopped, the flight crew may attempt a double and
simultaneous CB reset when a single CB reset has failed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B
DSC-22_20-90-10 P 5/6
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
ABNORMAL OPERATIONS - FMGC RESET
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_20-90-10 P 6/6
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
ABNORMAL OPERATIONS - "CHECK
GW" OR "CHECK WEIGHT" MESSAGE
FLIGHT CREW
OPERATING MANUAL
"CHECK WEIGHT" MESSAGE
Ident.: DSC-22_20-90-20-00012677.0001001 / 17 MAR 17
Applicable to: ALL
DESCRIPTION
The “CHECK WEIGHT” message appears on the MCDU when the Gross Weight (GW ) computed
by the FMGC and the GW computed by the FAC disagree by more than 7 t (16 055 lb).
PROCEDURE
When this message appears:
FMS FOB .............................................................................................................................. CHECK
CALL UP the MCDU FUEL PRED page and compare the FOB to the FOB from the Computerized
F-PLN. Correct it if necessary.
FMS ZFW value..................................................................................................................... CHECK
CALL UP the MCDU FUEL PRED page and compare the ZFW to the ZFW on the loadsheet.
If the FMS ZFW on the MCDU is not correct:
FMS ZFW ..............................................................................................CORRECT/RE-INSERT
The entry of a correct ZFW will clear the MCDU message.
If the FMS ZFW on the MCDU is correct:
VLS , F , S , GREEN DOT (PFD).......................................................................... DISREGARD
If the FMS GW is correct, the characteristic speeds computed by the FAC (displayed on PFD)
may not be correct.
QRH OPERATING SPEEDS................................................................................................ USE
Refer to QRH/OPS Operating Speeds
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-22_20-90-20 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
ABNORMAL OPERATIONS - "CHECK
GW" OR "CHECK WEIGHT" MESSAGE
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_20-90-20 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
MISALIGNMENT OF FMS F-PLN LEGS FOR ILS APPROACHES
Ident.: DSC-22_20-100-20-00013650.0001001 / 23 JUN 15
Applicable to: ALL
For the F-PLN legs belonging to an ILS approach, the FMS incorrectly uses its own Magnetic
Variation table instead of the Magnetic Variation of the ILS associated to the approach (coded in the
Navigation Data Base). This misbehaviour occurs when the Navaid used for the ILS approach is a
DME.
In some cases, it may happen that magnetic variation of the airport differs by a few degrees from the
ILS navaid. Thus, the FMS F-PLN does not match with the actual beam of the ILS beam.
When the ILS approach is coded with successive legs, these legs may also appear as not matching
with intermediate approach waypoint.
For all approaches affected by this behaviour, the FMS will display an incorrect trajectory on ND for
the LS approach. The guidance would also be wrong if the approach legs are flown in NAV instead of
LOC mode.
INCORRECT MANAGEMENT OF ETA ENTRY ON PREDICTIVE GPS PAGE
Ident.: DSC-22_20-100-20-00013652.0001001 / 22 MAY 12
Applicable to: ALL
During pre-flight, when a destination airport exists but the FMS does not compute predictions,
amber boxes are displayed in the MCDU field ETA of the predicitve GPS page. When the flight crew
manually enters an ETA, the value should be displayed in large cyan font.
With the current H2 standard, the FMS does not take into account the manual entry of an ETA (field
1R) for the destination (DEST, field 1L).
The FMS validates the manual entry only when an ETA is already computed by the FMS , when
predictions are available (necessary conditions to have some predictions are : entry of a GW , CRZ
FL , CI and F-PLN).
This anomaly does not impact the ETA of the WPT field (3L and 3R). An ETA can be entered in the
field 3L even if no predictions are computed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_20-100-20 P 1/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
FLIGHT NUMBER ERASED UPON AOC FLIGHT PLAN UPLINK
Ident.: DSC-22_20-100-20-00013653.0001001 / 16 MAR 11
Applicable to: ALL
When a Flight Plan (F-PLN ) uplink is performed, if the uplinked F-PLN is inserted as the active
F-PLN but does not contain a Flight Number, the previously entered Flight Number is erased. In such
a case, the flight crew needs to re-enter the correct Flight Number on the INIT A page.
LOSS OF FMS POSITION FURTHER TO IRS LOSS
Ident.: DSC-22_20-100-20-00013654.0001001 / 23 JUN 15
Applicable to: ALL
The loss or the failure of an Inertial Reference System (IRS ) could result in the loss of the FMS
position with the following cockpit effects :
‐ MAP NOT AVAIL GPS , PRIMARY LOST displayed on ND
‐ The DIR TO page is unavailable on both MCDU
‐ During approach, transient ATHR thrust variations at autopilot disconnection (Only applicable in
case of IR 1 FAULT).
Technical explanation :
The FMS needs valid data from the IRS in order to compute a position.
The FMS checks the IRS data with a specific parameter coming from the Flight Guidance (FG)
part of the FMGC . When an IRS is lost or off (dispatched inoperative), the onside FG erroneously
indicates to the FMS that the IRS DATA is still valid.
As a result, the FMS position is lost on the same side than the IRS inoperative (IRS 1 for FMS 1 and
IRS for FMS2). The manual switching on IRS 3 (ATT HDG on CAPT 3 or F/O 3) does not enable to
recover the data.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to D →
DSC-22_20-100-20 P 2/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
PROCEDURE:
In case of an IR x FAULT ECAM warning in flight with the above mentioned cockpit effects, apply
the following procedure :
De-activate (do not perform a reset) the FMS on the same side than the IRS inoperative :
‐ For IR 1 FAULT : pull FMGC 1 CB B2 (VU 49)
‐ For IR 2 FAULT : pull FMGC 2 CB M17 (VU 121)
ERRONEOUS FUEL PREDICTION IN THE CASE OF
DESCENT WITH TWO ALTITUDE CONSTRAINTS
Ident.: DSC-22_20-100-20-00013655.0001001 / 16 MAR 11
Applicable to: ALL
DESCRIPTION:
If the flight plan has two altitude constraints for the descent, the flight crew may notice erroneous
FMS fuel predictions.
EXPLANATION
If the flight plan has two altitude constraints for the descent, the FMS may define a geometric
segment between both altitude constraints. If there is a deceleration required within the
geometric segment, the FMS may consider that the geometric segment is too steep to fly without
speedbrakes. In this case, the FMS tags the entire geometric segment as a speedbrake segment :
The FMS assumes that during the entire segment half of the speedbrakes are extended, even for
the parts where no deceleration is planned. As a consequence, the FMS will predict an increased
thrust for the entire geometric segment. This may lead to erroneous fuel predictions. (a long
geometric segment (e.g. above 100 NM) may lead to an error of 1.5 t for the fuel prediction at
destination).
Note:
When flying the geometric segment, the predictions become better as the aircraft
approaches the end of the geometric segment, and turn back to normal when the aircraft
has sequenced the second altitude constraint.
PROCEDURE:
If the flight crew suspects this behavior in preflight, or during the flight, they can delete and enter
again one altitude constraint in descent and compare the fuel predictions of the flight plan with and
without the geometric segment. This allows the flight crew to evaluate the impact of the geometric
segment on the fuel predictions.
It is not recommended to permanently delete altitude constraints that are stored in the navigation
database.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E
DSC-22_20-100-20 P 3/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
UNEXPECTED SWITCH OF SPEED TARGET WHEN RTA IS USED
Ident.: DSC-22_20-100-20-00013659.0001001 / 16 NOV 11
Applicable to: ALL
An anomaly could be experienced when the RTA (Requested Time of Arrival) function is used.
The MCDU and the PFD could suddenly display an erroneous speed target at the transition altitude
when a RTA is entered and if the flight crew performs an action (Vapp entry or altitude constraint
modification) that causes a F-PLN profile recomputation.
This scenario could also occur if the flight crew has inserted a RTA and then deleted this RTA (the
FMS may erroneously retain the RTA target).
Some cases could happen while the aircraft is in descent (DES mode) in managed speed. This
speed target change is significant at high altitude if the RTA speed target is lower than the speed
target used before the beginning of the descent.
PROCEDURE
If an erroneous speed target is displayed at high altitude, the flight crew can manually select a
speed to continue the descent.
UNDUE AP DISCONNECTION OR REVERSION TO V/S DURING CLIMB AND DESCENT
Ident.: DSC-22_20-100-20-00014436.0017001 / 23 JUN 15
Applicable to: ALL
An AP disconnection or a reversion to the V/S mode may occur when the aircraft reaches an altitude
constraint in the CLB or DES mode. The following are two situations in which this behavior may
occur.
Situation 1: The aircraft is above the vertical profile.
When the aircraft is not on the vertical profile, the FMS makes assumptions in order to compute the
FMS predictions. For example, if the aircraft flies in selected speed, the FMS considers an immediate
return to managed speed.
These assumptions can result in FMS predictions that are not consistent with the real trajectory of
the aircraft. Therefore, the FMS may not anticipate the need to level off, when the FCU selected
altitude is above the altitude constraint in climb or below the altitude constraint in descent.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F to G →
DSC-22_20-100-20 P 4/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
However, the FMS requests the ALT CST* mode, when the aircraft reaches the altitude constraint, in
order to level off and comply with the altitude constraint.
Due to problem of communication between the FMS and the FG , the FMGC may unduly revert to
the V/S mode. The FWC triggers a triple-click aural warning , and the aircraft goes beyond the
altitude constraint.
Situation 2: The aircraft levels off at an altitude constraint in descent.
When the aircraft reaches an altitude constraint with the DES mode engaged and the FCU selected
altitude below the altitude constraint, the FG engages the ALT CST * mode. The FG also arms the
DES mode, in order to resume the descent beyond the waypoint with the altitude constraint.
In very rare cases, the FMS does not see that the FG arms the DES mode:
‐ If the FINAL APP mode is armed, the FMGC may unduly:
‐ Disconnect the AP, or
‐ Disconnect the AP and revert to the V/S mode, or
‐ Revert to the V/S mode.
‐ If the FINAL APP mode is not armed, the FMGC may unduly revert to the V/S mode.
In both of the above-mentioned cases, the FWC triggers a triple-click aural warning , and the
aircraft goes beyond the altitude constraint.
If the AP disconnects, the FWC triggers a cavalry-charge aural warning.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
DSC-22_20-100-20 P 5/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
OPERATIONAL RECOMMENDATIONS
Understand your FMA at all times.
If the AP disconnects, or if the FMGC reverts to the V/S mode:
Adjust the vertical speed or level off in order to comply with the altitude constraint.
VOR/DME AND VOR/TACAN NOT AUTOMATICALLY TUNED
Ident.: DSC-22_20-100-20-00014440.0001001 / 04 MAY 12
Applicable to: ALL
In case there is no NAVAID in the flight plan, nor any recommended NAVAID coded in the inserted
procedure, the FMS may not automatically tune the expected Terminal or Low Altitude VOR /DME or
VOR /TACAN.
The FMS may not automatically tune the expected NAVAID , if the aircraft is above 12 000 ft for a
Terminal VOR /DME or VOR /TACAN , and above 18 000 ft for a Low Altitude NAVAID.
As a consequence, the ND and the MCDU RAD NAV page may not display the NAVAID information.
OPERATIONAL RECOMMENDATIONS
If the flight crew encounters the misbehavior during the flight, the flight crew can manually tune the
expected VOR /DME or VOR /TACAN to recover the display on the ND.
As a manual tuning overrides any automatic tuning, the flight crew must clear the manual tuning,
when the NAVAID is no longer required, in order to revert to the automatic NAVAID tuning.
OPTIMUM TARGET SPEEDS NOT UPDATED FOLLOWING
THE AUTOMATIC DELETION OF A STEP CLIMB
Ident.: DSC-22_20-100-20-00014756.0001001 / 18 DEC 12
Applicable to: ALL
During the FMS climb phase, if the flight crew selects an altitude on the FCU that is above the Cruise
Flight Level (CRZ FL ) displayed on the PROG page, the altitude selected on the FCU becomes the
new CRZ FL.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← G to I →
DSC-22_20-100-20 P 6/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
If this new CRZ FL is at or above the altitude of a Step Climb of the flight plan, the FMS automatically
deletes the Step Climb. The FMS displays the "STEP DELETED" message.
As the optimum target speeds (ECON CLIMB speed/Mach and ECON CRUISE speed/Mach) depend
on the CRZ FL , the FMS should immediately update the ECON CLIMB speed/Mach and the ECON
CRUISE speed/Mach.
Due to a FMS misbehavior, the FMS may not correctly manage the automatic deletion of the Step
Climb when the CRZ FL is automatically set to the altitude selected on the FCU . The FMS may not
update the ECON CLIMB speed/Mach and the ECON CRUISE speed/Mach accordingly.
If the ECON CRUISE speed/Mach was not correctly updated, the FMS updates the ECON CRUISE
speed/Mach when the aircraft reaches the new CRZ FL . However the FMS updates the ECON
CRUISE speed/Mach with a rate of 0.01 Mach/min, in order to avoid a sudden increase of the
speed target. Therefore the aircraft may take several minutes to reach the new ECON CRUISE
speed/Mach.
OPERATIONAL RECOMMENDATIONS
If the flight crew suspects this misbehavior during the flight:
REENTER the Cruise Flight Level (CRZ FL ) on the PROG page, or the Cost Index (CI ) on the
PERF page, in order to activate an immediate update of the optimum target speeds (ECON CLIMB
speed/Mach and ECON CRUISE speed/Mach).
ERRONEOUS LATERAL GUIDANCE IN NAV MODE
WITH LOC MODE ARMED DURING APPROACH
Ident.: DSC-22_20-100-20-00015035.0001001 / 03 DEC 13
Applicable to: ALL
During approach, the FMS may guide the aircraft along a specific track instead of along the
F-PLN with NAV mode green on the FMA , because of the LOC Convergence function (Refer to
DSC-22_30-80-30-10 Precision Approach Modes - APPR Mode ).
The logics of the LOC Convergence function is as follows:
If NAV mode is engaged, and LOC mode is armed,
and
The aircraft is within 20 NM of the destination runway,
and
The difference between the aircraft track and the QFU is less than 20 °.
The aircraft is guided with a converging track of 20 ° from the LOC axis.
The NAV mode remains engaged. However the aircraft no longer follows the F-PLN, but
converges towards the LOC axis.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← I to J →
DSC-22_20-100-20 P 7/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
If the difference between the aircraft track and the QFU becomes more than 20 ° when the
LOC Convergence function is active:
The FMS deactivates the LOC Convergence function, and the aircraft follows back the F-PLN.
It may lead to slight oscillations, since the FMS may successively activate and deactivate the
LOC Convergence function.
OPERATIONAL RECOMMENDATIONS
If the flight crew considers that the LOC Convergence function may affect the guidance
along the F-PLN trajectory in NAV mode:
On the intercept trajectory for the LOC axis, the flight crew should push the APPR pb (or the
LOC pb-sw) when appropriate.
If the flight crew detects that the aircraft does not follow the intended trajectory:
The flight crew should revert to HDG/TRK mode, and intercept the LOC axis with the
HDG/TRK mode engaged and the LOC mode armed.
UNDUE REDUCTION OF THE SPEED TARGET IN CASE OF DIR
TO/ABEAM WHILE FLYING A CONSTANT MACH SEGMENT
Ident.: DSC-22_20-100-20-00015532.0003001 / 18 MAR 14
Applicable to: ALL
The FMS may erroneously command a Mach target of 0, when the following conditions are met:
‐ The aircraft is flying a Constant Mach Segment (CMS), and
‐ The TO waypoint is the end of the CMS, and
‐ The aircraft is close to the TO waypoint, i.e. about 1 NM, and
‐ The flight crew performs a DIR TO/ABEAM to a waypoint that is not part of the CMS.
In that case, the FMS does not create the abeam of the TO waypoint (end of the CMS), since it is too
close from the aircraft.
In addition, the FMS erroneously keeps the CMS until the abeam of the next waypoint, and defines
0 as Mach target on the CMS . The FMS correctly computes the speed target once the abeam of the
next waypoint is sequenced.
OPERATIONAL RECOMMENDATIONS
The flight crew should manually clear the CMS on the MCDU VERT REV page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← J to K
DSC-22_20-100-20 P 8/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
LOSS OF FUEL AND TIME PREDICTIONS DURING TAKEOFF DATA INSERTION
Ident.: DSC-22_20-100-20-00015602.0001001 / 05 AUG 14
Applicable to: ALL
The flight crew may lose fuel and time prediction when the altitude of the first constraint is less than
50 ft below either the THR RED ALT or the ACC ALT , the update of fuel and time computation
predictions may last a long time. The flight crew may think that the predictions are lost (the DEST
EFOB and TRIP FUEL are also dashed on the FUEL PRED page).
The flight crew may encounter the situation described above, if one of the following occurs:
‐ The first altitude constraint of the SID is less than 50 ft below either the THR RED ALT or the ACC
ALT.
‐ The flight crew inserts a THR RED ALT or an ACC ALT less than 50 ft above the first altitude
constraint of the F-PLN.
‐ The flight crew modifies the F-PLN to insert an AT or an AT OR BELOW altitude constraint less
than 50 ft below the THR RED ALT or the ACC ALT.
OPERATIONAL RECOMMENDATION:
The flight crew can recover the fuel and time predictions if the flight crew sets the THR RED ALT or
ACC ALT value on the PERF TAKEOFF page to the same value as the first altitude constraint of the
F-PLN.
ERRONEOUS TRAJECTORY DURING PROCEDURES WITH A
TURN DIRECTION ON A LEG WITH AN ALTITUDE TERMINATION
Ident.: DSC-22_20-100-20-00015748.0001001 / 09 SEP 14
Applicable to: ALL
In some very specific operational conditions that depend on the coding in the Navigation Database
of the procedure, and on various performance conditions (aircraft weight, flaps, thrust setting,
temperature, wind...), the FMS may compute an erroneous trajectory on some Standard Instrument
Departures (SID), and on some Missed Approach procedures.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
L to M →
DSC-22_20-100-20 P 9/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
The SIDs and the Missed Approach procedures that may be affected are coded in the Navigation
Database with a leg that has a turn direction and an altitude termination. The leg can be one of the
following:
‐ A Course-to-an-Altitude (CA) leg that defines a course to follow to an altitude
‐ A Fix-to-an-Altitude (FA) leg that defines a track to follow from a waypoint to an altitude
‐ A Heading-to-an-Altitude (VA) leg that defines a heading to follow to an altitude
‐ A Holding-to-an-Altitude (HA) leg that defines a holding pattern to an altitude
The turn direction (left or right) that is coded on a leg indicates that the aircraft has to execute a turn
in the specified direction to intercept the leg.
In some very specific operational conditions (aircraft weight, wind...), the FMS may predict that the
aircraft will reach the altitude that terminates the leg, before the initiation of the leg. In that case, the
FMS ignores the leg, and the associated turn direction.
The FMS computes a new trajectory to directly join the next leg. The trajectory may not be consistent
with the published trajectory.
Example:
‐ Leg 1: a Course-to-Fix (CF) leg that defines a track (360 °) to a waypoint (WPT1)
‐ Leg 2 : a Course-to-an-Altitude (CA) leg that defines a track (130 °) to intercept an altitude
(3 000 ft). The leg is coded in the Navigation Database with a turn direction (left). The end of the
leg depends on the aircraft performance. The turn direction is indicated by an arrow on the line of
leg 1 on the MCDU
‐ Leg 3: a CF leg that defines a track (120 °) to a waypoint (WPT2)
Depending on the aircraft performance, the FMS may predict that the aircraft will reach 3 000 ft
before WPT1. In that case, the FMS ignores the leg 2 (CA leg) because the aircraft is already above
the altitude that ends leg 2, before the beginning of leg 2. The FMS also ignores the turn direction
that is coded on the leg.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←M→
DSC-22_20-100-20 P 10/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
As a result, the FMS computes again the trajectory from the end of leg 1, directly to leg 3. As shown
on the above illustration, this trajectory includes a right turn, instead of a left turn, because it induces
the shortest course change to intercept leg 3 (CF leg).
If the NAV mode is engaged, the aircraft follows this erroneous trajectory.
OPERATIONAL RECOMMENDATIONS
The flight crew should pay particular attention to the check of the flight plan during the Cockpit
Preparation, and during the Descent Preparation.
CAUTION
Even if the flight plan is correct during the Cockpit Preparation or during the
Descent Preparation, the FMS may compute and display an erroneous trajectory
when the FMS updates its predictions after takeoff or after go-around initiation.
If the flight crew detects that the lateral flight plan does not agree with the published trajectory, the
flight crew should revert to the HDG /TRK mode, and monitor NAVAID raw data as appropriate.
The flight crew should reengage the NAV mode when the lateral flight plan is consistent with the
published trajectory.
ERRONEOUS VERTICAL PROFILE DURING LOC B/C APPROACHES
WITH A MAP LOCATED BEFORE THE RUNWAY THRESHOLD
Ident.: DSC-22_20-100-20-00019782.0001001 / 25 JUL 16
Applicable to: ALL
DESCRIPTION
When the flight crew selects a LOC Back Course (LOC B/C ) approach in the arrival page of the
MCDU , if the Missed Approach Point (MAP ) is located before the runway threshold, the FMS
builds the final approach vertical flight path assuming that there is an altitude constraint at the
MAP , equal to the runway (RWY ) threshold elevation plus 50 ft, disregarding the actual coded
MAP altitude.
As a result, the FMS computes an erroneous vertical flight path for the final approach, an
erroneous crossing altitude at the MAP , and displays an erroneous vertical deviation indication
(V/DEV symbol on the PFD and V/DEV value on MCDU PROG page), when flying the approach.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← M to N →
DSC-22_20-100-20 P 11/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - FMS2
HONEYWELL TEMPORARY ABNORMAL BEHAVIORS
Therefore, the flight crew must fly the LOC B/C approaches in selected vertical guidance mode
(FPA or V/S mode), and they must disregard the V/DEV displayed on the PFD and MCDU PROG
page.
PROCEDURE
For LOC B/C approaches, check the position of the MAP on the approach chart:
If the MAP is located at the runway threshold:
V/DEV symbol can be used to assist the flight crew in flying the vertical flight path in selected
mode. Crosscheck the final descent with the published chart using altitude versus distance, as
per Standard Operating Procedures (SOPs).
If the MAP is located before the runway threshold:
DISREGARD the V/DEV symbol, and crosscheck the final descent using the altitude versus
the distance to the MAP.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←N
DSC-22_20-100-20 P 12/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
TEMPORARY ABNORMAL BEHAVIORS - ALL
FMS TEMPORARY ABNORMAL BEHAVIORS
FLIGHT CREW
OPERATING MANUAL
ERRONEOUS PREDICTIONS
Ident.: DSC-22_20-100-40-00012672.0001001 / 17 MAR 17
Applicable to: ALL
The FMGS may display temporary erroneous predictions that can affect such data as ECON
speed/Mach, optimum flight level, fuel or time predictions.
PROCEDURE
If erroneous predictions are observed:
ON GROUND, OR IN FLIGHT
Check the cruise temperature (sign and value), the gross weight, and the cruise flight level.
REENTER the same cost index to restart a computation (In descent or approach, a cost index
change does not restart a computation), or
MAKE a COPY ACTIVE, then activate the secondary, or
MAKE a DIR TO the “TO” waypoint.
SPURIOUS ENGINE OUT INDICATION
Ident.: DSC-22_20-100-40-00012673.0001001 / 17 MAR 17
Applicable to: ALL
PROCEDURE
If a spurious engine-out is detected:
PRESS the EO CLR prompt of the MCDU PERF page
RE-ENGAGE previous vertical mode
RE-ENTER preselected speeds (if any). No other consequences are to be expected.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-22_20-100-40 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT MANAGEMENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS - ALL
FMS TEMPORARY ABNORMAL BEHAVIORS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_20-100-40 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
Intentionally left blank
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_30-10 General
General.....................................................................................................................................................................A
Mode Reversions..................................................................................................................................................... B
Guidance Modes......................................................................................................................................................C
Mode Selection........................................................................................................................................................ D
Lateral Modes.......................................................................................................................................................... E
Vertical Modes......................................................................................................................................................... F
Interaction between AP/FD and A/THR Modes...................................................................................................... G
DSC-22_30-20 Flight Director
General.....................................................................................................................................................................A
Flight Director (FD) Engagement............................................................................................................................ B
Flight Director (FD) Disengagement....................................................................................................................... C
Automatic FD Removal........................................................................................................................................... D
FD Warnings............................................................................................................................................................ E
DSC-22_30-30 Autopilot (AP)
General.....................................................................................................................................................................A
AP Engagement.......................................................................................................................................................B
AP Disengagement..................................................................................................................................................C
AP Warnings............................................................................................................................................................D
Autoland Warning.................................................................................................................................................... E
DSC-22_30-40 Speed/Mach Control
General.....................................................................................................................................................................A
Managed Speed/Mach Target................................................................................................................................. B
Selected Speed/Mach Target..................................................................................................................................C
Auto SPD.................................................................................................................................................................D
Speed/Mach Switching............................................................................................................................................ E
Managed Speed Target Memorization.................................................................................................................... F
Speed/Mach FCU Window Synchronization........................................................................................................... G
DSC-22_30-50 AP/FD Modes General
AP/FD Modes General............................................................................................................................................ A
DSC-22_30-60 AP/FD Lateral Modes
Heading or Track: HDG - TRK................................................................................................................................A
HDG/TRK Preset..................................................................................................................................................... B
Navigation (NAV)..................................................................................................................................................... C
Localizer Mode through the LOC Pushbutton.........................................................................................................D
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-PLP-TOC P 1/6
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_30-70 AP/FD Vertical Modes
DSC-22_30-70-10 Principles
Continued from the previous page
General.....................................................................................................................................................................A
Principles..................................................................................................................................................................B
DSC-22_30-70-20 Climb Mode
General.....................................................................................................................................................................A
Arming Conditions....................................................................................................................................................B
Disarming Conditions...............................................................................................................................................C
Engagement Conditions.......................................................................................................................................... D
Disengagement Conditions......................................................................................................................................E
Guidance.................................................................................................................................................................. F
DSC-22_30-70-30 Open Climb Mode
General.....................................................................................................................................................................A
Engagement Conditions...........................................................................................................................................B
Disengagement Conditions......................................................................................................................................C
Guidance..................................................................................................................................................................D
DSC-22_30-70-50 Descent Mode
General.....................................................................................................................................................................A
Arming Conditions....................................................................................................................................................B
Disarming Conditions...............................................................................................................................................C
Engagement Conditions.......................................................................................................................................... D
Disengagement Conditions......................................................................................................................................E
Repressurization Segment.......................................................................................................................................F
Descent Speed Profile............................................................................................................................................ G
Guidance in DES Mode.......................................................................................................................................... H
DES Mode Profile..................................................................................................................................................... I
DSC-22_30-70-60 Open Descent Mode
General.....................................................................................................................................................................A
Engagement Conditions...........................................................................................................................................B
Disengagement Conditions......................................................................................................................................C
Guidance..................................................................................................................................................................D
DSC-22_30-70-65 Altitude Acquire Mode
General.....................................................................................................................................................................A
Engagement Conditions...........................................................................................................................................B
Disengagement Conditions......................................................................................................................................C
Guidance..................................................................................................................................................................D
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-PLP-TOC P 2/6
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_30-70-70 Altitude Hold Mode
Continued from the previous page
General.....................................................................................................................................................................A
Arming Conditions....................................................................................................................................................B
Engagement Conditions.......................................................................................................................................... C
Disengagement Conditions......................................................................................................................................D
Guidance.................................................................................................................................................................. E
Soft Altitude Mode (Cruise)..................................................................................................................................... F
DSC-22_30-70-80 Vertical Speed Mode - Flight Path Angle Mode (V/S - FPA)
General.....................................................................................................................................................................A
Engagement Conditions...........................................................................................................................................B
Disengagement Conditions......................................................................................................................................C
Guidance..................................................................................................................................................................D
DSC-22_30-70-90 Expedite
General.....................................................................................................................................................................A
Engagement Conditions...........................................................................................................................................B
Disengagement Conditions......................................................................................................................................C
Guidance..................................................................................................................................................................D
DSC-22_30-75 Mode Reversions
General.....................................................................................................................................................................A
Interaction between Lateral Modes, Vertical Modes, and Managed Speed Profile.................................................B
Mode Reversion due to FCU Altitude Change....................................................................................................... C
Reversion with Global Speed Protection................................................................................................................ D
Mode Reversions (Summary)..................................................................................................................................E
DSC-22_30-80 AP/FD Common Modes
DSC-22_30-80-10 General
General.....................................................................................................................................................................A
DSC-22_30-80-20 Takeoff
General.....................................................................................................................................................................A
SRS (Speed Reference System).............................................................................................................................B
Runway (RWY)........................................................................................................................................................ C
DSC-22_30-80-30 Approach
DSC-22_30-80-30-05 General
General.....................................................................................................................................................................A
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-PLP-TOC P 3/6
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_30-80-30-10 Precision Approach
Continued from the previous page
Precision Approach Modes......................................................................................................................................A
Speed Control.......................................................................................................................................................... B
Typical ILS Approach.............................................................................................................................................. C
Autoland Warning Light........................................................................................................................................... D
Landing Capabilities.................................................................................................................................................E
DSC-22_30-80-30-20 Non Precision Approach
General.....................................................................................................................................................................A
Selection...................................................................................................................................................................B
Arming Conditions................................................................................................................................................... C
Disarming Conditions...............................................................................................................................................D
Engagement Conditions...........................................................................................................................................E
Disengagement Conditions...................................................................................................................................... F
Guidance..................................................................................................................................................................G
DSC-22_30-80-40 Go Around (GA)
General.....................................................................................................................................................................A
Engagement Conditions...........................................................................................................................................B
Disengagement Conditions......................................................................................................................................C
Guidance..................................................................................................................................................................D
DSC-22_30-90 Autothrust
General.....................................................................................................................................................................A
Thrust Levers........................................................................................................................................................... B
A/THR Arming Conditions....................................................................................................................................... C
A/THR Activation..................................................................................................................................................... D
A/THR Disconnection...............................................................................................................................................E
Thrust Lock Function............................................................................................................................................... F
A/THR Disconnection Caution................................................................................................................................ G
A/THR Modes.......................................................................................................................................................... H
SPEED Mode in Approach Phase............................................................................................................................I
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-PLP-TOC P 4/6
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_30-100 Flight Mode Annunciator (FMA)
Continued from the previous page
Flight Mode Annunciator (FMA).............................................................................................................................. A
Autothrust Annunciations (FMA Column 1).............................................................................................................B
AP/FD Vertical Modes (FMA Column 2).................................................................................................................C
AP/FD Lateral Modes (FMA Column 3)..................................................................................................................D
AP/FD Common Modes (FMA Columns 2 and 3) ................................................................................................. E
Approach Capabilities (FMA Column 4).................................................................................................................. F
AP/FD - A/THR Engagement Status (FMA Column 5)...........................................................................................G
Special Messages (FMA Columns 2 and 3)........................................................................................................... H
DSC-22_30-110 Temporary Abnormal Behaviors
CAT 3 Dual Inoperative...........................................................................................................................................A
Left Turn Not Expected while in HDG or TRK Mode..............................................................................................B
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FCOM
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05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
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FCOM
DSC-22_30-PLP-TOC P 6/6
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-10-00011031.0001001 / 17 AUG 10
Applicable to: ALL
The Flight Guidance (FG ) part of the FMGS controls:
‐ The Flight Director (FD)
‐ The Autopilot (AP)
‐ The Autothrust (A/THR).
MODE REVERSIONS
Ident.: DSC-22_30-10-00011032.0001001 / 17 AUG 10
Applicable to: ALL
There are several types of mode reversions. Each one observes a specific logic that is described in
the "Mode Reversions" section. (Refer to DSC-22_30-75 General).
GUIDANCE MODES
Ident.: DSC-22_30-10-00011033.0002001 / 23 JUN 15
Applicable to: ALL
Two types of autopilot and flight director modes are available to guide the aircraft:
‐ Managed modes: When the aircraft is using managed targets, the Flight Management and
Guidance System (FMGS ) guides it along lateral and vertical flight paths and speed profiles
computed by the Flight Management function (FM ) from data in the MCDU . FM manages the
guidance targets.
‐ Selected modes: When the flight crew is using selected targets, the FMGS guides the aircraft
along lateral and vertical flight paths and speed profiles to meet targets that the flight crew has
selected manually on the FCU. The flight crew selects the guidance targets.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C →
DSC-22_30-10 P 1/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
GUIDANCE
LATERAL
VERTICAL
SPEED
MANAGED modes
NAV, APP NAV
LOC *, LOC
RWY
RWY TRK
GA TRK
ROLL OUT
SRS (TO and GA)
CLB , DES
ALT CST, ALT CST*
ALT CRZ
G/S *, G/S
FINAL, FINAL APP
FLARE
FMGC REFERENCE
(ECON , Auto SPD , SPD LIM)
EXPEDITE
SELECTED modes
HDG -TRK
OP CLB , OP DES
V/S , FPA
ALT *, ALT
EXPEDITE
FCU REFERENCE
MODE SELECTION
Ident.: DSC-22_30-10-00011034.0001001 / 23 JUN 15
Applicable to: ALL
MANAGED MODES
‐ At takeoff, the managed modes engage automatically when the flight crew sets the thrust levers
at the TO or FLX detent.
‐ During flight, the flight crew can arm or engage the managed modes (if the aircraft meets
engagement conditions) by pushing in the appropriate knobs on the Flight Control Unit (FCU).
‐ The flight crew pushes the DIR TO key on the MCDU to insert a DIR TO leg. It engages or
maintains the NAV mode.
‐ The flight crew pushes the APPR pb on the FCU to arm or engage the localizer and glide slope
or “APP NAV-FINAL”, depending upon the approach type insert in the flight plan.
‐ The LOC pb arms or engages only the localizer mode.
SELECTED MODES
The flight crew can engage the selected modes by pulling out the appropriate FCU selection
knobs.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
DSC-22_30-10 P 2/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
LATERAL MODES
Ident.: DSC-22_30-10-00011035.0003001 / 23 JUN 15
Applicable to: ALL
MODE
RWY
TYPE
MANAGED
RWY TRK
MANAGED
NAV
MANAGED
HDG -TRK
SELECTED
GUIDANCE
Mode used at takeoff to
guide the aircraft along the
runway centerline, using
LOC.
Mode used to guide the
aircraft along the track the
aircraft was following at
mode engagement.
Mode used to guide the
aircraft along the lateral
F-PLN. Available above 30 ft
after takeoff.
Mode used to guide the
aircraft on a heading or a
track selected by the flight
crew. The target value
is displayed in the FCU
window.
REMARK
Triggered by the thrust levers
at FLX or TOGA position.
Automatically armed at
takeoff, unless HDG /TRK is
preset.
In that case, RWY TRK
engages after takeoff.
Note:
HDG /TRK is
called "basic
mode" because
it is a backup
mode for certain
situations:
‐ F-PLN
discontinuity
entry
‐ AP
engagement
with no FD
‐ Loss of F-PLN
‐ MCDU NAV
BACK UP.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
DSC-22_30-10 P 3/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
MODE
LOC*
LOC
APP NAV
TYPE
MANAGED
GUIDANCE
Mode used to guide the
aircraft on the lateral
approach path (LOC or
F-PLN approach path).
Continued from the previous page
REMARK
Selected by pressing APPR
pb on the FCU ; the mode
that engages depends upon
the selected approach in the
F-PLN.
Note:
LAND
MANAGED
GA TRK
MANAGED
ROLL OUT
MANAGED
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Common mode engaged
below 400 ft RA during an
automatic ILS approach.
Mode used to guide the
aircraft along the track the
aircraft was following at
mode engagement.
Mode used to guide the
aircraft on the runway,
following an automatic
landing.
←E
For LOC only
approach, do not
select the FCU's
APPR pb, but
rather the LOC
pb.
Engaged only if LOC mode
and G/S mode are already
engaged.
Triggered by the thrust levers
at TOGA with Slats/Flaps in
at least CONF 1.
FD rollout symbol is
displayed on the PFD at
touchdown.
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
VERTICAL MODES
Ident.: DSC-22_30-10-00011036.0002001 / 23 JUN 15
Applicable to: ALL
MODE
SRS
TYPE
MANAGED
CLB
MANAGED
DES
MANAGED
OP CLB
OP DES
SELECTED
EXPEDITE
SELECTED
ALT CST*
ALT CST
MANAGED
ALT*
ALT
ALT CRZ
SELECTED
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
GUIDANCE
Mode used at takeoff or
go-around to maintain SRS
speed (V2 , V2+10, VAPP...).
REMARK
Triggered by the thrust levers
at FLX or TOGA position.
Disengages automatically at
ACC ALT or when another
VERT mode is engaged.
Mode used to climb towards The speed target may be
FCU selected altitude
either selected or managed.
along VERT F-PLN taking
If managed, SPD CSTR ,
into account ALT CSTR .
SPD LIM and HOLD SPD are
Available only if NAV mode taken into account.
ALT mode is always armed ;
engaged. The A/THR is in
thrust mode (CLB).
displayed in magenta if the
next level off is predicted at
Mode used to descend
an ALT CSTR , and in blue if
towards FCU selected
altitude along the computed the next level off is predicted
at the FCU selected altitude.
descent path taking into
account ALT CSTR .
Available only if NAV mode
engaged.
The A/THR may be in
THRUST or SPD mode.
Mode used to climb/descent The speed target may be
directly to the FCU selected either selected or managed.
altitude. These modes
ALT mode is systematically
disregard all ALT CSTR . The armed and blue. Altitude
A/THR is in THRUST mode target is blue on PFD.
(CLB/IDLE).
Mode used to increase the Used to expedite a climb or
vertical speed by selecting
descent towards a specific
green dot in climb or
level.
0.80/340 kt in descent.
Mode automatically engaged CLB /DES mode are
when reaching an ALT CSTR systematically armed (blue).
before the FCU selected
altitude.
Mode used to maintain
Soft ALT mode engages
a level flight at the FCU
when FCU selected altitude
selected altitude.
= CRZ FL.
Soft ALT is part of the
managed guidance.
Continued on the following page
F→
DSC-22_30-10 P 5/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
MODE
TYPE
SELECTED
G/S*
G/S
FINAL
MANAGED
FLARE
MANAGED
V/S -FPA
Continued from the previous page
GUIDANCE
REMARK
Mode used to guide the
Altitude target is blue on PFD
aircraft along a vertical speed . V/S -FPA is a basic mode.
or a selected flight path
(Refer to DSC-22_30-10
angle.
Lateral Modes).
Mode used to guide the
Selected by depressing the
aircraft along the final
APPR pb on the FCU . The
approach path (G/S or non mode engaged depends
upon the selected approach
ILS)
in the F-PLN . Linked to
APPR common mode (APPR
pb).
Common mode which
Engages below 50 ft RA as a
provides the alignment to
function of the current vertical
the runway center line on the speed.
yaw axis and the flare on the
pitch axis.
INTERACTION BETWEEN AP/FD AND A/THR MODES
Ident.: DSC-22_30-10-00011037.0002001 / 23 JUN 15
Applicable to: ALL
The AP and FD pitch modes can control a target SPD /MACH or a vertical trajectory, and the A/THR
mode can control a fixed thrust or a target SPD /MACH. However, the AP /FD and the A/THR cannot
both control a target SPD/MACH simultaneously.
Therefore the AP /FD pitch modes and A/THR mode are coordinated as follows:
‐ If an AP /FD pitch mode controls a vertical trajectory, the A/THR mode controls the target
SPD/MACH.
‐ If an AP /FD pitch mode controls a target SPD or MACH, the A/THR mode controls the thrust.
‐ If no AP /FD pitch mode is engaged, the A/THR mode reverts to controlling the SPD/MACH mode.
In other words, the selection of an AP /FD pitch mode determines which mode the A/THR controls.
AP /FD pitch modes
V/S - FPA
DES (geometric path)
ALT *, ALT
ALT CRZ *, ALT CRZ
ALT CST*, ALT CST
G/S *, G/S
FINAL, FINAL APP
AP /FD OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G →
A/THR modes
SPEED/MACH MODE
Continued on the following page
DSC-22_30-10 P 6/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Continued from the previous page
A/THR modes
AP /FD pitch modes
CLB /DES (idle path)
OP CLB /OP DES
EXP CLB/EXP DES
SRS
FLARE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
THR (CLB, IDLE) MODE
RETARD (IDLE)
←G
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT DIRECTOR
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-20-00012468.0001001 / 14 MAY 12
Applicable to: ALL
The Flight Director (FD ) displays guidance commands from the Flight Management and Guidance
Computer (FMGC ) on the Primary Flight Display (PFD).
The flight crew may manually fly the aircraft, following FMGC guidance commands, or crosscheck
the FMGC orders when the autopilot is engaged.
In normal operations, FD 1 displays FMGC 1 orders on the PFD 1 and FD 2 displays FMGC 2 orders
on the PFD2.
The FD s use their respective onside FMGCs.
On the PFD:
1. The FD pitch and roll crossbars show pitch and roll demands.
2. Below 30 ft during landing and takeoff, when a localizer is available, the vertical bar is replaced by
a yaw bar that gives lateral orders.
3. The Flight Path Director (FPD ) symbol relates to the Flight Path Vector (FPV).
The HDG V/S – TRK FPA pb on the FCU enables the flight crew to select either type of reference
and display.
The FD pb on the Electronic Flight Instrument System (EFIS ) control panel allows the FD bars to be
displayed or removed.
FD BARS (HDG V/S SELECTED ON THE FCU)
‐ The pitch bar is displayed if a vertical mode is engaged. It gives pitch orders for the vertical
guidance
‐ The roll bar is displayed if a lateral mode is engaged. It gives roll orders for lateral guidance.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-22_30-20 P 1/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT DIRECTOR
FLIGHT CREW
OPERATING MANUAL
FLIGHT PATH DIRECTOR (TRK FPA SELECTED ON THE FCU)
The display is an alternate way of transmitting flight director commands.
‐ The Flight Path Vector (FPV) symbol illustrates the track and flight path angle actually being
flown
‐ The Flight Path Director (FPD ) symbol shows the flight crew how to intercept the required
vertical and lateral flight trajectory. When the flight crew superimposes the FPV and the FPD
symbols, the aircraft is flying the required trajectory.
YAW BAR
The yaw bar is displayed in RWY mode on takeoff and in FLARE and ROLL OUT modes at
landing.
FLIGHT DIRECTOR (FD) ENGAGEMENT
Ident.: DSC-22_30-20-00012469.0008001 / 01 OCT 12
Applicable to: ALL
The FD s are engaged automatically when the FMGC powers up.
GROUND ENGAGEMENT
‐ The "1FD 2" symbol appears on both PFDs
‐ No FD bars appear on the PFD s. (The PFD displays FD orders when a mode is active on the
corresponding axis)
‐ The FCU windows display dashes.
MANUAL FLIGHT ENGAGEMENT
The two FD s engage in the HDG V/S or TRK FPA modes (basic modes).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-22_30-20 P 2/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT DIRECTOR
FLIGHT CREW
OPERATING MANUAL
AUTOMATIC FLIGHT ENGAGEMENT
FD bars are automatically restored in SRS /GA TRK modes at go-around engagement. If FPV
/FPD was previously selected, it reverts to FD bars.
FLIGHT DIRECTOR (FD) DISENGAGEMENT
Ident.: DSC-22_30-20-00012470.0006001 / 19 DEC 12
Applicable to: ALL
The flight crew may disengage one or two FD s manually, or FDs may disengage automatically if
there is a failure.
MANUAL DISENGAGEMENT
One FD OFF:
‐ The FD bars no longer appear on the associated PFD.
‐ The corresponding FD is disengaged.
Both FDs OFF:
‐ The FD bars disappear from both PFDs.
‐ If no AP was engaged, lateral and vertical modes disengage. The A/THR, if active, automatically
reverts to (or remains in) SPEED/MACH mode.
‐ If one AP was engaged when FD s are switched OFF, this AP remains engaged in the active
modes but the FDs are no longer displayed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_30-20 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT DIRECTOR
FLIGHT CREW
OPERATING MANUAL
AUTOMATIC DISENGAGEMENT
If one FD fails or one FMGC is not valid, both PFD s display the remaining FD.
AUTOMATIC DISENGAGEMENT DUE TO SPEED PROTECTION
When AP s are not engaged and the flight crew does not follow the FD bars to maintain the
commanded trajectory in climb with CLB or OP CLB (or EXP CLB ) engaged or in descent
with DES or OP DES (or EXP DES ) engaged, the FDs will disengage at the activation of the
automatic speed mode protection.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-22_30-20 P 4/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT DIRECTOR
FLIGHT CREW
OPERATING MANUAL
Refer to DSC-22_30-75 Reversion with Global Speed Protection - Automatic Speed Mode
Protection in Climb.
AUTOMATIC FD REMOVAL
Ident.: DSC-22_30-20-00012472.0001001 / 28 JAN 14
Applicable to: ALL
‐ The FD pitch bar is removed when no vertical mode is engaged or when ROLL OUT mode is
engaged.
‐ The FD roll bar is removed when no lateral mode is engaged or when the RWY or ROLL OUT
mode is engaged.
‐ Both FDs are removed when the aircraft pitch exceeds 25 ° up or 13 ° down, or bank angle
exceeds 45 °.
FD WARNINGS
Ident.: DSC-22_30-20-00012473.0001001 / 16 MAR 11
Applicable to: ALL
FD bar WARNINGS
Pitch FD bar (or FPV) flashes 10 s and then remains steady
Pitch FD bar (or FPV) flashes permanently
Roll FD bar (or FPV) flashes 10 s and then remains steady
Roll FD bar (or FPV) flashes permanently
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
CONDITIONS
‐ If the ALT * mode is lost further to FCU altitude reference
change of more than 250 ft.
‐ When in APPR mode (G/S *, G/S , LAND, FINAL), FD
reverts to V/S mode (flight crew action or loss of vertical
approach mode).
‐ One AP or one FD is engaged while both AP /FD were
previously OFF.
Transmission of the GLIDE data is interrupted when in G/S ,
G/S * or LAND modes above 100 ft RA.
‐ When in APPR mode (LOC *, LOC , LAND, APP NAV
), FD reverts to HDG mode (flight crew action or loss of
lateral approach mode).
‐ One AP or one FD is engaged while both AP /FD were
previously OFF.
Transmission of the LOC data is interrupted when in LOC ,
LOC * or LAND modes above 15 ft RA.
← C to E
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT DIRECTOR
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOPILOT (AP)
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-30-00011816.0001001 / 17 AUG 10
Applicable to: ALL
The AP:
‐ Stabilizes the aircraft around its center of gravity
‐ Acquires and tracks a flight path
‐ Flies the aircraft to an automatic landing or go-around.
The AP commands the:
‐ Position of the flight control surfaces for pitch, roll and yaw
‐ Nose wheel position.
AP ENGAGEMENT
Ident.: DSC-22_30-30-00011817.0014001 / 16 MAR 11
Applicable to: ALL
The flight crew can engage AP 1 or AP 2 by pressing the corresponding pushbutton on the FCU if
the aircraft has been airborne for at least 5 s.
When one AP is engaged, the corresponding FCU pushbutton comes on and AP 1 (or 2) is displayed
on the FMAs.
In BACK–UP NAV , AP can be engaged in selected modes if the FG part is available.
‐ One AP can be engaged on ground if the engines are not running. It disengages when one engine
is started.
‐ Two AP s may be engaged at a time (AP 1 active, AP2 in standby), when the localizer/glide-slope
or roll out or go-around mode is armed or engaged.
Only one AP can be engaged at a time in all other cases.
‐ If one AP pb is set to ON with both FD s OFF, the AP engages in HDG V/S or TRK FPA mode,
depending upon which mode the flight crew has selected on the FCU.
‐ If one AP pb is set to ON with at least one FD already ON, the AP engages in the current active
FD modes.
‐ At takeoff, the AP cannot be engaged below 100 ft.
AP engagement increases the break out force on the sidestick controllers and on the rudder pedals.
AP engagement is indicated by the lighting of the corresponding FCU pushbutton and by the
appearance of AP 1 (or 2) on the PFD ’s FMA.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-22_30-30 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOPILOT (AP)
FLIGHT CREW
OPERATING MANUAL
AP DISENGAGEMENT
Ident.: DSC-22_30-30-00011818.0008001 / 04 NOV 13
Applicable to: ALL
AP1 or 2 disengages when:
‐ The flight crew presses the takeover pb on the sidestick, or
‐ The flight crew presses the corresponding AP pb on the FCU, or
‐ The flight crew pushes on the sidestick harder than a defined threshold, or moves on the rudder
pedals beyond a defined threshold, or
‐ The flight crew moves the pitch trim wheel beyond a defined threshold, or
‐ The other AP is engaged, except when localizer/glideslope modes are armed or engaged, or when
the rollout or go-around mode is engaged, or
‐ Both thrust levers are set above the MCT detent and the aircraft is on ground, or
‐ In a non-precision approach, the aircraft reaches the Missed Approach Point (MAP ) with FINAL
APP mode engaged, or
‐ One of the engagement conditions is lost.
In addition, in normal law with all protections available, the AP will disengage when:
‐ High speed protection activates, or
‐ Angle-of-attack protection activates:
• From the liftoff to 100 ft RA during the landing, when α prot +1 ° is reached, or
• Below 100 ft RA during the landing, when α MAX is reached, or
‐ Pitch attitude exceeds 25 ° up, or 13 ° down, or bank angle exceeds 45 °, or
‐ A rudder pedal deflection is more than 10 ° out of trim.
The standard manner for the flight crew to disengage the AP is to press the takeover pb on the
sidestick.
When the AP is OFF, the associated pushbutton on the FCU goes off, and AP 1 (or AP 2) disappears
from the FMA.
AP WARNINGS
Ident.: DSC-22_30-30-00011819.0001001 / 17 AUG 10
Applicable to: ALL
When the AP is disengaged, the system warns the flight crew:
‐ If the flight crew disengages it with the takeover pb on the sidestick, the warnings are temporary
‐ If the disengagement results from a failure, from the flight crew pushing the pushbutton on the
FCU, or from a force on the sidestick, the visual and audio warnings are continual.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D →
DSC-22_30-30 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOPILOT (AP)
FLIGHT CREW
OPERATING MANUAL
AP DISENGAGEMENT
TAKEOVER pb
BY OTHER MEANS
on SIDESTICK
MASTER
WARNING light
Flashing red during 3 s maximum
AP OFF red message
9 s maximum
Cavalry charge
0.5 s minimum
1.5 s maximum
ECAM
CONSEQUENCE
AUDIO
CLR pb on
ECAM CONTROL
PANEL
Extinguished
‐ Extinguishes Master Warning
light
MASTER
‐ Erases ECAM warning
WARNING light ‐ Stops audio if pressed within
1.5 s
ACTION
CLR pb on
ECAM CONTROL
PANEL
No effect
‐ Extinguishes Master Warning
light
‐ Erases ECAM warning
‐ Stops audio if pressed within
1.5 s
TAKEOVER pb
ECAM STATUS MESSAGE
NO
Flashing red
AUTO FLT AP OFF red warning
Continuous cavalry charge
1.5 s minimum
Illuminated
‐ Extinguishes Master Warning
light
‐ Stops audio after 1.5 s
‐ Extinguishes CLR pb
‐ Erases ECAM message
‐ Calls status
‐ Extinguishes Master Warning
light
‐ Stops audio after 1.5 s
YES
AUTOLAND WARNING
Ident.: DSC-22_30-30-00011820.0001001 / 09 APR 15
Applicable to: ALL
Below 200 ft RA, an Autoland red light flashes in case of failures that require the interruption of an
automatic landing.
Refer to DSC-22_30-80-30-10 Autoland Warning Light for the detailed conditions triggering the
Autoland warning.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E
DSC-22_30-30 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOPILOT (AP)
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-30 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
SPEED/MACH CONTROL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-40-00011893.0001001 / 17 AUG 10
Applicable to: ALL
In flight, either the AP /FD pitch control, or autothrust may acquire and hold a target speed or Mach
number, depending on the engaged modes.
Speed control is:
‐ Managed when the target comes from the FMGS
‐ Selected when the target comes from the SPD /MACH FCU window.
MANAGED SPEED/MACH TARGET
Ident.: DSC-22_30-40-00011894.0001001 / 01 DEC 14
Applicable to: ALL
When the speed target is managed, the SPD /MACH window of the FCU shows dashes, and the
corresponding dot is lighted. The PFD speed scale shows the speed target in magenta.
ENGAGEMENT CONDITIONS
The SPD target is managed, whenever AP or FD is engaged, and one of the following occurs:
‐ The flight crew pushes in the SPD/MACH knob
‐ EXPEDITE mode is engaged
‐ V2 is inserted in the MCDU
‐ The speed reference system (SRS) is engaged (takeoff or go-around mode).
Note:
At takeoff, SRS will not engage if V2 is not available.
DISENGAGEMENT CONDITIONS
Managed speed disengages any time the flight crew selects a speed target on the FCU, or if the
speed was preselected.
SPEED PROFILE
The form of the managed SPD profile depends on the lateral NAV mode.
If NAV mode is engaged, the SPD profile takes into account all the constraints linked to
the flight plan.
The SPD profile is:
V2 - SPD LIM - SPD CSTR (if applicable) - ECON CLB SPD /MACH - ECON CRZ MACH
- ECON or preset DES MACH/SPD -SPD LIM - SPD CSTR (if applicable) - HOLD SPD (if
applicable) - VAPP.
If NAV mode is not engaged, the SPD/MACH constraints are not considered.
The SPD profile is:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_30-40 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
SPEED/MACH CONTROL
FLIGHT CREW
OPERATING MANUAL
V2 - SPD LIM - ECON CLB SPD /MACH - ECON CRZ MACH - ECON or preset DES
MACH/SPD - SPD LIM - VAPP.
Note:
1. When both AP /FD s are OFF, A/THR reverts to selected SPEED mode, except when
the approach phase is activated on MCDU where both managed and selected SPD
are available.
2. When expedite mode is engaged, the system disregards SPD LIM and SPD CSTR no
matter what lateral mode is engaged.
3. The managed speed/Mach target may be set below maneuvering speed but as long as
the speed target is managed, the FMGS limits the aircraft to the maneuvering speed of
the current slats/flaps configuration (VAPP , F , S, Green Dot).
4. If the managed speed/Mach target is set above VMAX (VFE , VMO , MMO ), the
FMGS automatically limits the speed to VMAX.
5. If a SPD/MACH constraint has already been taken into account, it remains applied
(until a more restrictive constraint applies).
MINI GROUND SPEED
In approach phase, the managed speed target is the Mini Ground Speed target computed by the
Flight Guidance (FG ) part of the FMGS. Refer to DSC-22_30-90 General for details.
SELECTED SPEED/MACH TARGET
Ident.: DSC-22_30-40-00011895.0002001 / 17 AUG 10
Applicable to: ALL
To use a selected speed/Mach target, the flight crew uses the knob on the FCU to set the target
speed, which is then displayed in the FCU window. It is also displayed in blue on the PFD speed
scale.
Note:
The selected speed/Mach target may be set beyond VLS or VMAX , but when autothrust is
active, the guidance limits the speed to VLS or VMAX.
Selected speed has priority over managed speed. The only automatic change-over from selected to
managed speed target may occur at go-around mode engagement.
In flight, if the situation calls for managed speed, both the PFD and the MCDU display a message
proposing a manual change to managed speed (for example, SET MANAGED SPEED, SET HOLD
SPEED, or SET GREEN DOT SPEED).
ENGAGEMENT CONDITIONS
The aircraft has a selected speed target under any one of the following conditions:
‐ The flight crew pulls out the SPD/MACH knob (5 s after lift-off)
‐ Both AP /FD s are OFF (except in APPR phase)
‐ The FM speed target is lost (except in SRS , G/S, LAND, and GO AROUND modes)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_30-40 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
SPEED/MACH CONTROL
FLIGHT CREW
OPERATING MANUAL
‐ The MCDU has a preselected speed for the next phase, and the aircraft transitions into that
phase
‐ The FMGC is powered up in flight.
DISENGAGEMENT CONDITIONS
The selected speed target disengages:
‐ When the managed SPD engages
‐ When the aircraft is on ground at engine start.
Note:
With engines running, the flight crew can select a speed on the FCU only after takeoff.
AUTO SPD
Ident.: DSC-22_30-40-00011896.0001001 / 17 AUG 10
Applicable to: ALL
The flight crew may insert the AUTO SPD (speed or Mach) on the PERF DES page to replace the
ECON DES SPD.
In this case, the managed speed profile takes into account the selected value. The top of descent
and the descent path are computed on AUTO SPD assumption.
SPEED/MACH SWITCHING
Ident.: DSC-22_30-40-00011897.0001001 / 16 MAR 11
Applicable to: ALL
In managed speed, at the crossover altitude, the FMGC automatically changes the managed speed
target to the corresponding MACH target. The FCU displays the Mach number corresponding to the
speed at the switching altitude.
Note:
When the speed is selected, the flight crew has to perform the switching manually by
pressing the SPD/MACH pb on the FCU . The FCU then displays the aircraft Mach number.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to E →
DSC-22_30-40 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SPEED/MACH CONTROL
When the target speed is managed, the FMGC commands the switchover automatically as a function
of the ECON MACH value.
MANAGED SPEED TARGET MEMORIZATION
Ident.: DSC-22_30-40-00011898.0001001 / 13 JAN 14
Applicable to: ALL
A dual FM failure has different consequences when it occurs in different phases of the flight.
The system handles target speed and SPD mode as follows:
‐ During approach with LOC and G/S engaged and radio height < 700 ft, the target speed is set to
VAPP as previously memorized, and managed SPD target is maintained.
‐ At go-around, the target speed becomes the memorized go-around speed, which is the higher of
VAPP or the speed when go-around was initiated. Managed SPD target is maintained.
‐ In all other cases, managed target speed reverts to selected, the value being the speed at the
moment of the failure.
SPEED/MACH FCU WINDOW SYNCHRONIZATION
Ident.: DSC-22_30-40-00011899.0001001 / 17 AUG 10
Applicable to: ALL
When the target SPD is managed, the SPD /MACH display of the FCU shows dashes.
However, the window displays the target SPD or MACH in the following situations:
‐ The flight crew turns the SPD/MACH knob.
If the flight crew does not pull the knob within 10 s after turning it, the selection reverts to dashes.
‐ The flight crew manually engages a selected SPD target.
‐ If the flight crew has manually preselected a speed or Mach number for the next phase on the
MCDU PERF page, that preselected SPD /MACH engages when the aircraft enters that phase
and the FCU window then displays as the target the preselected speed or Mach.
‐ If the FMGS is powered up in flight, the synchronized speed/Mach value is the current aircraft
speed or Mach number.
‐ If no V2 is entered at takeoff, the V/S mode engages 5 s after lift-off (no speed reference system).
The FCU speed target is the speed at V/S mode engagement. (A/THR becomes active when the
thrust levers are set in the active range).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to G
DSC-22_30-40 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD MODES GENERAL
FLIGHT CREW
OPERATING MANUAL
AP/FD MODES GENERAL
Ident.: DSC-22_30-50-00011767.0007001 / 23 JUN 15
Applicable to: ALL
The FMGS has guidance parameters for both AP /FD lateral and vertical modes.
The AP /FD lateral modes are:
RWY, RWY TRK Runway, Runway track mode
NAV
Nav mode
HDG, TRK
Heading, track mode. Also called basic modes
APP NAV
Approach Nav mode
LOC*, LOC
Loc capture, Loc track mode
LAND
Land mode. Managed submode that includes LOC and G/S modes below
400 ft RA
FINAL APP
Final approach mode. Managed submode that includes APP NAV and FINAL
modes during non precision approach
ROLL OUT
Roll out mode (Autoland)
GA TRK
Go-around track mode
The AP /FD vertical modes are:
SRS
SRS mode used for takeoff and go-around
CLB
Climb mode
DES
Descent mode
OP CLB
Open Climb mode
OP DES
Open Descent mode
EXP CLB
Expedite mode in climb
EXP DES
Expedite mode in descent
V/S or FPA
Vertical Speed mode or Flight Path Angle mode. Also called basic modes
ALT*
Altitude capture
ALT
Altitude Hold mode
ALT CST*
Altitude constraint capture
ALT CST
Altitude constraint hold mode
ALT CRZ
Altitude hold of the cruise flight level
G/S*
Glide slope capture
G/S
Glide slope mode
FINAL
Final mode (Non precision approach)
FLARE
Flare mode (Autoland)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-22_30-50 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD MODES GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-50 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD LATERAL MODES
FLIGHT CREW
OPERATING MANUAL
HEADING OR TRACK: HDG - TRK
Ident.: DSC-22_30-60-00012328.0001001 / 17 AUG 10
Applicable to: ALL
These modes guide the aircraft laterally along a heading or track selected by the flight crew. The
HDG /TRK window of the FCU displays the target heading or track. The flight crew uses the HDG
V/S -TRK FPA pb to select heading or track.
ENGAGEMENT CONDITIONS
HDG or TRK is engaged when one of the following conditions is met:
‐ The flight crew pulls out the HDG/TRK knob (not sooner than 5 s after lift-off)
‐ NAV is disengaged, either by the loss of the lateral flight plan or by the flight crew entering a
flight plan discontinuity
‐ FINAL mode (armed or engaged) is lost when the aircraft is in APP NAV mode
‐ LOC or LOC* mode is lost
‐ The flight crew engages the AP /FD with no other mode already engaged (basic mode of AP
/FD engagement)
‐ LOC mode is armed when APP NAV FINAL were previously engaged.
DISENGAGEMENT CONDITIONS
The engagement of any other lateral mode disengages HDG or TRK.
SYNCHRONIZING THE HDG /TRK WINDOW OF THE FCU
The lateral window of the FCU displays a heading or a track value when:
‐ The HDG /TRK mode is engaged. The displayed value is the current HDG /TRK or the manually
selected value of the target
‐ The flight crew turns the HDG/TRK knob. The value in the window first synchronizes with the
current HDG /TRK , then displays the manual selection. It remains displayed for 10 s or 45 s
depending upon FCU standard, then vanishes if the flight crew does not pull the knob (except in
HDG preset)
‐ A HDG /TRK is preset (Refer to DSC-22_30-60 HDG/TRK Preset)
‐ AP /FD is lost. The value becomes that of the aircraft current heading or track.
Note:
If HDG is switched to TRK (or vice versa), the value displayed in the window switches
from heading to track (or vice versa).
HDG/TRK PRESET
Ident.: DSC-22_30-60-00012329.0001001 / 17 AUG 10
Applicable to: ALL
The system has a HDG /TRK preset function for takeoff and go-around.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_30-60 P 1/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD LATERAL MODES
If the flight crew chooses not to fly the flight plan after takeoff or go-around, they may preset a HDG
or a TRK on the FCU by turning the HDG/TRK knob. The value they set remains displayed in the
FCU HDG /TRK window until they pull the knob.
OPERATION AT TAKEOFF
HDG /TRK preset is available before takeoff and up to 30 ft RA . Turning the HDG/TRK knob
before 30 ft sets the desired HDG /TRK. As a consequence:
‐ NAV is disarmed
‐ At 30 ft, RWY TRK is annunciated until the HDG/TRK knob is pulled.
OPERATION AT GO-AROUND
Whenever the LOC *, LOC , LAND, FINAL APP, or GA modes are engaged, the HDG preset is
available. If the flight crew rotates the HDG/TRK knob to set the value, it will remain displayed in
the window. Pull out the HDG/TRK knob to activate the mode and turn the aircraft to the preset
value.
CANCELLATION
The flight crew can cancel a preset HDG /TRK by:
‐ Engaging the NAV mode using the DIR TO
‐ Pushing in the HDG/TRK knob (arming NAV mode)
‐ Disengaging AP /FD.
NAVIGATION (NAV)
Ident.: DSC-22_30-60-00012330.0002001 / 23 JUN 15
Applicable to: ALL
NAV mode is a managed mode that steers the aircraft laterally along the flight plan defined in the
FMGS . It is designed to have a zero cross-track error. The flight crew can arm or engage the NAV
mode if the MCDU contains a lateral flight plan.
ARMING CONDITIONS
Satisfying one of the following conditions arms NAV:
‐ The aircraft is on ground with no HDG /TRK preset and no other lateral mode except runway
mode
‐ The flight crew pushes in the HDG/TRK knob, unless the LOC mode is engaged
‐ The flight crew presses the APPR pb, if a non-ILS approach is selected.
DISARMING CONDITIONS
NAV mode disarms if one of the following occurs:
‐ The flight crew pulls out the HDG/TRK knob
‐ The flight crew selects a preset HDG /TRK (TO or GA)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_30-60 P 2/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
‐
‐
‐
‐
AP/FD LATERAL MODES
The flight crew arms the LOC mode by pressing the LOC pb
The flight crew selects GA mode
LAND mode has engaged
The flight crew presses the APPR pb, if an XLS approach is selected.
ENGAGEMENT CONDITIONS
NAV mode engages:
‐ Automatically at 30 ft RA after takeoff (if armed on the ground)
‐ When the flight crew orders “DIR TO " (except below 700 ft RA in LOC mode)
‐ When the flight crew pushes in the HDG/TRK knob when the aircraft is close to (within ∼1 NM
of) the active flight plan leg
‐ Automatically in flight when NAV is armed and the aircraft reaches the capture zone for the
active flight plan leg.
CAUTION
Note:
When NAV is armed, it will automatically engage if:
‐ The aircraft track line intercepts the flight plan before the TO waypoint, and
‐ The intercept waypoint (INTCP) is displayed on the ND, and
‐ The aircraft reaches the active flight plan leg.
The TO waypoint is displayed in white on ND s and MCDUs.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-22_30-60 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD LATERAL MODES
DISENGAGEMENT CONDITIONS
The NAV mode disengages when:
‐ Any other lateral mode is engaged
‐ The flight plan is lost or the aircraft enters a flight plan discontinuity.
INTERACTIONS WITH VERTICAL MODES
When NAV mode is engaged, the vertical managed modes CLB or DES or FINAL take into
account altitude and speed constraints linked to waypoints on the lateral flight plan. If NAV mode
is disengaged, the vertical managed modes are not available and all downpath altitude and speed
constraints are ignored.
LOCALIZER MODE THROUGH THE LOC PUSHBUTTON
Ident.: DSC-22_30-60-00012331.0001001 / 17 AUG 10
Applicable to: ALL
This mode captures and tracks a localizer beam independently of the glide path beam. Flight crew
use it to fly localizer-only approaches or to initiate an ILS approach when intercepting the glide slope
from above.
ARMING CONDITIONS
The flight crew arms the LOC mode by pressing the LOC pb, provided that:
‐ An ILS is tuned (frequency and runway course)
‐ The aircraft is above 400 ft RA
‐ TO or GA mode is not engaged.
DISARMING CONDITIONS
LOC mode is disarmed by:
‐ Pressing the LOC pb when LOC is armed
‐ Arming the NAV mode
‐ Engaging the GA mode.
Note:
Engaging NAV mode by selecting DIR TO does not disarm the LOC mode.
ENGAGEMENT CONDITIONS
The LOC mode engages automatically when capture conditions are met.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
DSC-22_30-60 P 4/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD LATERAL MODES
FLIGHT CREW
OPERATING MANUAL
DISENGAGEMENT CONDITIONS
The LOC mode disengages:
‐ When another lateral mode is engaged
‐ When the flight crew presses the LOC pb again (engaging the HDG /TRK mode on the current
HDG /TRK).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
DSC-22_30-60 P 5/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD LATERAL MODES
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-60 P 6/6
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - PRINCIPLES
GENERAL
Ident.: DSC-22_30-70-10-00010507.0001001 / 17 AUG 10
Applicable to: ALL
Vertical modes guide the aircraft in the vertical plan.
PRINCIPLES
Ident.: DSC-22_30-70-10-00010508.0001001 / 17 AUG 10
Applicable to: ALL
To leave an FCU selected altitude for another target altitude, the flight crew must turn the Altitude
(ALT) knob in order to display the new target altitude and either:
‐ Pull out the ALT knob to engage the OPEN CLB /DES mode, or
‐ Push in the ALT knob to engage the CLB /DES mode, or
‐ Select a target vertical speed (V/S ) and pull out the V/S or FPA knob to engage V/S mode, or
‐ Select EXPEDITE .
This arms ALT mode.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-22_30-70-10 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - PRINCIPLES
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-70-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - CLIMB MODE
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-70-20-00010509.0001001 / 01 OCT 12
Applicable to: ALL
CLB mode guides the aircraft in a managed climb, at either a managed or a selected target speed, to
an FCU selected altitude, taking into account altitude constraints at waypoints.
The system also considers speed constraints if the target speed is managed. The vertical flight path
may include several segments:
The flight crew can arm the CLB mode during the takeoff, go-around, climb, and cruise phases and
engage it during the climb and cruise phases.
ARMING CONDITIONS
Ident.: DSC-22_30-70-20-00010510.0001001 / 17 AUG 10
Applicable to: ALL
The CLB mode is armed:
‐ On ground or when SRS mode is engaged (TO or GA) if the following conditions are met:
• No other vertical mode is engaged
• The ACCEL ALT (defined on the PERF TO or GA MCDU pages) is below the FCU selected
altitude and the lowest altitude constraint.
‐ In flight, when the climb or go-around phase is active, and the following conditions are met:
• The lateral NAV mode is engaged
• The FCU selected altitude is above the aircraft’s present altitude and the aircraft captures or
flies an altitude constraint.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-22_30-70-20 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - CLIMB MODE
FLIGHT CREW
OPERATING MANUAL
DISARMING CONDITIONS
Ident.: DSC-22_30-70-20-00010511.0002001 / 23 JUN 15
Applicable to: ALL
The CLB mode is disarmed, if one of the following conditions is met:
‐ Another vertical mode is engaged
‐ The FCU selected altitude is lower than the present aircraft level
‐ The FCU selected altitude is set at the altitude constraint while ALT CST* or ALT CST mode is
engaged
‐ The aircraft transitions to DES or APPR phase
‐ Arming requirements are no longer met
‐ Vertical flight path validity is lost, or NAV mode is lost while ALT CST* or ALT CST mode is
engaged.
ENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-20-00010512.0001001 / 17 AUG 10
Applicable to: ALL
The CLB mode can be engaged, if the following conditions are all met:
‐ The aircraft has been in flight for more than 5 s
‐ The selected FCU level is above the present aircraft level
‐ The descent, approach, or go-around phase is not active
‐ NAV mode is engaged
‐ Glideslope (G/S) mode is not engaged.
CLB mode automatically engages when the aircraft reaches ACC ALT , or sequences a waypoint
with an altitude constraint while the CLB mode is armed.
CLB mode manually engages when the flight crew pushes in the ALT knob, with the CLB mode not
armed and the current altitude is not an effective altitude constraint of the flight plan.
Note:
When CLB mode is engaged:
‐ The V/S (FPA ) window of the FCU shows dashes
‐ The managed LVL/CH dot on the FCU lights up
‐ The Flight Mode Annunciator displays “CLB” in Column 2.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D
DSC-22_30-70-20 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - CLIMB MODE
FLIGHT CREW
OPERATING MANUAL
DISENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-20-00010513.0002001 / 17 AUG 10
Applicable to: ALL
The CLB mode disengages, if one of the following conditions is met:
‐ NAV mode is lost or disengaged (OP CLB engages). In this case, the reversion to OP CLB is
accompanied by a triple click aural warning
‐ Another vertical mode engages
‐ The flight crew selects an altitude on the FCU that is lower than the present aircraft altitude.
V/S (FPA ) engages on the current V/S (FPA).
GUIDANCE
Ident.: DSC-22_30-70-20-00010514.0002001 / 01 OCT 12
Applicable to: ALL
Climb mode gives the aircraft managed vertical guidance to the FCU selected altitude. It meets
altitude constraints at waypoints either with managed speed incorporating speed constraints or with
selected speed as target speed. The AP /FD pitch controls the speed or Mach number target and the
A/THR is in thrust mode (CLB) corresponding to maximum climb thrust. The flight path may include
several segments.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E to F →
DSC-22_30-70-20 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - CLIMB MODE
‐ When CLB mode is engaged, the system arms ALT and displays the applicable target altitude on
the ALT scale.
• If the next predicted level-off is an ALT CSTR , ALT is magenta on the FMA and the ALT CSTR
is displayed in magenta on the altitude scale
• If the next predicted level-off is the FCU altitude, ALT is blue on the FMA and the FCU selected
altitude is displayed in blue on the altitude scale.
Note:
The system takes into account all constraints defined by the database or manually
entered by the flight crew. Nevertheless this mode has the following particularity: When
the aircraft is in CLB mode and the system predicts that it will miss an altitude constraint,
it will not modify the target speed in an attempt to meet it. In this case, the flight crew
may select an appropriate speed in order to meet the ALT CSTR.
‐ The guidance does not modify the target speed in order to satisfy an altitude constraint. Therefore
the constraint may not be met and may be predicted as missed
‐ When the aircraft levels off at the ALT CSTR , CLB mode arms automatically, then engages when
the aircraft passes the constrained waypoint (if the FCU altitude is above the constraint altitude).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
DSC-22_30-70-20 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - OPEN CLIMB MODE
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-70-30-00010515.0001001 / 17 AUG 10
Applicable to: ALL
The OPEN CLB mode is a selected mode. It uses the AP /FD pitch mode to maintain a SPD/MACH
(selected or managed) while the autothrust (if active) maintains maximum climb thrust.
ENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-30-00010516.0002001 / 16 MAR 11
Applicable to: ALL
The OPEN CLB mode can only be engaged, if all of the following conditions are met:
‐ The aircraft is in flight for more than 5 s
‐ The LAND mode is not engaged
‐ The FCU selected altitude is higher than the aircraft’s present altitude.
The OPEN CLB mode is engaged, if one of the following conditions occurs:
‐ The flight crew pulls out the ALT knob
‐ The flight crew pulls out the SPD/MACH knob, when TOGA mode or EXPED CLB is engaged
‐ Acceleration altitude is reached, with CLB armed, and NAV mode not engaged
‐ Guidance reverts to ensure speed protection
‐ NAV mode is lost (or disengaged), when previously in CLB mode. Reversion to OPEN CLB is
accompanied by a triple click aural warning (Refer to DSC-22_30-75 General).
Note:
When OPEN CLB is engaged:
‐ The FMA displays "OP CLB"
‐ The managed LVL/CH dot on the FCU goes out.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-22_30-70-30 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - OPEN CLIMB MODE
FLIGHT CREW
OPERATING MANUAL
DISENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-30-00010517.0001001 / 17 AUG 10
Applicable to: ALL
The OPEN CLB mode is disengaged by one of the following conditions:
‐ Engagement of any other vertical mode
‐ Reversion to V/S mode (Refer to DSC-22_30-75 General)
‐ Selection of a lower altitude than the current aircraft altitude. V/S (FPA ) engages on the current
V/S (FPA).
GUIDANCE
Ident.: DSC-22_30-70-30-00010518.0001001 / 01 OCT 12
Applicable to: ALL
When OPEN CLB is engaged, the target speed/Mach is maintained by adjusting the pitch with the
elevator, whereas thrust is maintained either by the A/THR, or manually by the flight crew. Speed
target may either be selected or managed.
The OPEN CLB mode disregards all altitude constraints up to the FCU selected altitude.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D →
DSC-22_30-70-30 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - OPEN CLIMB MODE
OPEN CLB MODES, MANAGED SPEED
Note:
If the change is less than 1 200 ft in OPEN CLB mode, the aircraft responds with a rate
of climb of 1 000 ft/min.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
DSC-22_30-70-30 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - OPEN CLIMB MODE
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-70-30 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - DESCENT MODE
GENERAL
Ident.: DSC-22_30-70-50-00010521.0001001 / 17 AUG 10
Applicable to: ALL
The DES mode guides the aircraft along the descent path computed by the FMGS . The system
computes this flight path backwards from the deceleration point up to the top of descent (T/D ),
with respect to the speed and altitude constraints at the deceleration point, the guidance begins the
deceleration to VAPP, to be reached at 1 000 ft above touchdown on the final descent path.
Internally, the computer divides the descent path into various segments, depending on the relative
positions of the constraints. It starts at top of descent (T/D) by setting up an “idle” segment that
takes the aircraft down to the first constraint, and follows this with “geometric” segments between
constraints.
The descent profile takes into account wind data and data from the lateral and vertical flight plans,
and it is based upon the managed descent speed profile. It does not take holding patterns into
consideration.
The descent profile has several segments:
‐ A repressurization segment. When necessary, this produces a repressurization rate for the cabin
during descent. It is a function of the destination airport altitude and the selected cabin rate
(defaulted to -350 ft/min but this can be modified)
‐ Idle path segment. The AP /FD controls the speed and the autothrust stays at idle thrust. The
guidance computes this profile from the top of descent or the end of the repressurization segment
to the first vertical constraint that cannot be flown at idle thrust
‐ Geometric path segments. The AP /FD controls the vertical path, and autothrust controls the
speed. These segments take the aircraft from the first constraint to the deceleration point.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-22_30-70-50 P 1/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - DESCENT MODE
FLIGHT CREW
OPERATING MANUAL
The descent mode is a managed mode that may be engaged during cruise. It can be armed or
engaged in descent and approach phases (except if the FCU selected altitude is higher than the
present aircraft altitude).
ARMING CONDITIONS
Ident.: DSC-22_30-70-50-00010522.0001001 / 17 AUG 10
Applicable to: ALL
The DES mode is armed when an ALT CSTR is captured and all the following conditions are met:
‐ FCU selected altitude is lower than present altitude
‐ NAV , LOC * or LOC mode is engaged
‐ Takeoff or go-around phase is not active
‐ Flight profile is available.
DISARMING CONDITIONS
Ident.: DSC-22_30-70-50-00010523.0002001 / 23 JUN 15
Applicable to: ALL
The DES mode is disarmed if one of the following conditions is met:
‐ Engagement of another vertical mode
‐ FCU selected altitude is set above the aircraft current altitude
‐ Loss of NAV , LOC *, or LOC mode
‐ Switching to the go-around phase
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to C →
DSC-22_30-70-50 P 2/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - DESCENT MODE
FLIGHT CREW
OPERATING MANUAL
‐ Loss of vertical flight path validity
‐ Setting the FCU selected altitude at an altitude constraint while ALT CST* was engaged. (ALT *
engages and DES mode disarms).
ENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-50-00010524.0002001 / 23 JUN 15
Applicable to: ALL
The DES mode can be engaged, when the following conditions are met:
‐ The FCU selected altitude is lower than present altitude
‐ NAV , LOC *, or LOC mode is engaged
‐ Takeoff, climb, or go-around phase is not active
‐ Vertical flight path is valid
‐ TO , G/S , LAND, FINAL or GA mode is not engaged, and:
• The aircraft sequences a waypoint with an ALT CSTR , and DES mode is armed. The DES
mode engages automatically, or
• The flight crew presses the ALT knob, while ALT CST* or ALT CST is not engaged, or
• The flight crew presses the ALT knob, while ALT * or ALT is engaged, but the current altitude is
not an effective altitude constraint of the F-PLN.
Note:
When DES mode is engaged:
‐ The V/S - FPA window of the FCU shows dashes
‐ The managed LVL/CH dot on the FCU lights up.
DISENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-50-00010525.0002001 / 17 AUG 10
Applicable to: ALL
The DES mode is disengaged, if one of the following conditions is met:
‐ The NAV mode is lost or disengaged and the V/S or FPA mode engages. A triple click aural
warning will sound
‐ Another vertical mode engages
‐ The flight crew selects an altitude on the FCU that is higher than the aircraft present altitude and
the V/S (FPA ) engages on current V/S (FPA ). Same triple click logic, as for the OP DES case
‐ NAV mode is lost due to a discontinuity in the descent profile. AP /FD reverts to basic mode, and a
triple click aural warning sounds. The vertical mode is boxed in white for 10 s.
Refer to DSC-22_30-75 General.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to E
DSC-22_30-70-50 P 3/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - DESCENT MODE
FLIGHT CREW
OPERATING MANUAL
REPRESSURIZATION SEGMENT
Ident.: DSC-22_30-70-50-00010559.0002001 / 14 MAY 12
Applicable to: ALL
The top of descent (T/D) may be updated if the flight crew modifies the cabin rate of descent (default
rate is -350 ft/min).
If the flight crew enters a lower cabin rate, the system computes a repressurization segment that
takes into account the additional time needed for repressurization.
DESCENT SPEED PROFILE
Ident.: DSC-22_30-70-50-00012563.0002001 / 14 MAY 12
Applicable to: ALL
The descent speed profile is usually the ECON SPD profile, amended by any speed constraints and
speed limit contained in the flight plan.
Before the descent phase is active, if flight crew does not intend to fly the ECON speed/Mach profile,
a different speed or Mach can be entered to amend the speed profile.
It is obtained by entering a Mach number and/or a speed in the MANAGED field of the PERF DES
MCDU page (3L key).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F to G →
DSC-22_30-70-50 P 4/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - DESCENT MODE
FLIGHT CREW
OPERATING MANUAL
If the flight crew reverts to the SELECTED speed/MACH mode during descent, the profile is not
modified and the aircraft flies the same profile at the FCU selected speed/MACH value.
Basic managed SPD /MACH profile in DES mode is:
‐ ECON MACH, or SELECTED Mach
‐ ECON SPD, or SELECTED Speed
‐ SPD CSTR (if any)
‐ SPD LIMIT
‐ Green Dot/S /F /VAPP
‐ VAPP TARGET.
GUIDANCE IN DES MODE
Applicable to: ALL
Ident.: DSC-22_30-70-50-A-00010575.0001001 / 17 AUG 10
DESCENT INITIATION
The aircraft will not start its descent automatically when reaching the top of descent (T/D). In order
to initiate the descent, the flight crew sets the clearance altitude by turning the ALT knob then
pushes the ALT knob.
The aircraft will descend immediately:
‐ If the top of descent is not reached, the aircraft descends at a constant V/S converging on the
descent path
‐ If the aircraft is at or beyond the T/D, it descends at idle thrust.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← G to H →
DSC-22_30-70-50 P 5/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - DESCENT MODE
Ident.: DSC-22_30-70-50-A-00010563.0005001 / 01 OCT 12
DURING THE DESCENT
The flight crew will see a vertical deviation symbol (VDEV ) along the ALT scale on the PFD and a
VDEV value on the PROG page, so that the aircraft’s vertical position can be monitored versus the
calculated descent profile.
The aircraft may deviate from the DES profile while DES mode is engaged if:
‐ Unexpected wind conditions are encountered
‐ Anti-icing is turned on
‐ The lateral flight plan is changed.
When the speed is managed, a target speed range displayed on the PFD defines acceptable
speed variations around the nominal descent speed target.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H→
DSC-22_30-70-50 P 6/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - DESCENT MODE
Ident.: DSC-22_30-70-50-A-00010565.0001001 / 19 DEC 12
FMA DISPLAY
When DES mode is engaged, the system arms ALT and displays the applicable target altitude on
the PFD altitude scale.
‐ If the next predicted level-off is an altitude constraint, ALT is magenta on the FMA second line
and the PFD displays the altitude constraint magenta above the altitude scale.
When the aircraft flies at the altitude constraint (ALT CSTR ), the system arms DES blue.
When the aircraft meets the constraint, DES engages again automatically.
‐ If the next predicted level-off is the FCU altitude, ALT is blue on the FMA and the PFD displays
the FCU selected altitude in blue.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H
DSC-22_30-70-50 P 7/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - DESCENT MODE
FLIGHT CREW
OPERATING MANUAL
DES MODE PROFILE
Applicable to: ALL
Ident.: DSC-22_30-70-50-B-00010567.0005001 / 01 OCT 12
GENERAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I→
DSC-22_30-70-50 P 8/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - DESCENT MODE
Ident.: DSC-22_30-70-50-B-00010568.0005001 / 17 AUG 10
INTERCEPT POINT
Associated with the VDEV displayed on PFD , the ND shows an intercept point ( ) on the flight
plan. It indicates the position where the system predicts that the aircraft will intercept the descent
profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
DSC-22_30-70-50 P 9/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - DESCENT MODE
Ident.: DSC-22_30-70-50-B-00010569.0002001 / 01 OCT 12
AIRCRAFT ABOVE THE DESCENT PROFILE
If the aircraft is above the descent profile, the speed will increase toward the upper limit of the
managed speed range. If the speed reaches the upper limit, the aircraft will maintain the speed but
will deviate from the profile (autothrust at idle).
The navigation display presents a pseudo waypoint (intercept point) along the flight plan that
assumes the aircraft will return to the profile using:
‐ Idle thrust
‐ 1/2 speedbrake extension
‐ ECON speed plus a margin (until intercepting the profile).
If necessary, the message “AIRBRAKES” (old FMGC standard) or “MORE DRAG” comes up on
the PFD and the MCDU, and remains there as long as more drag (speedbrakes) is still required.
The flight crew should respond to this message by deploying half speedbrakes.
Whenever the intercept point is predicted to be close to a constrained waypoint, the PFD and
MCDU display an “AIRBRAKES” or “MORE DRAG” message depending upon the FMGS
standard.
Note:
With DES mode engaged, the speedbrakes extension will not necessarily increase the
descent rate. It increases only if the aircraft is above path.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
DSC-22_30-70-50 P 10/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - DESCENT MODE
Ident.: DSC-22_30-70-50-B-00010570.0002001 / 17 AUG 10
AIRCRAFT BELOW THE DESCENT PROFILE
If the aircraft is below the descent profile, its speed will be maintained at target speed until it
reaches the descent profile. The lower margin becomes effective when the aircraft is on the
descent profile but has to loose speed in order to stay on it.
The intercept point on the navigation display is based on the following assumptions:
If the aircraft is flying at an altitude that is higher than both the descent speed limit
altitude and the destination elevation +5 000 ft:
The FMGS maintains the V/S at -1 000 ft/min and the target speed, until the aircraft reaches
the altitude constraint, or intercepts the descent profile.
If the aircraft is flying at an altitude that is lower than either the descent speed limit
altitude, or the destination elevation +5 000 ft:
The FMGS maintains the V/S at -500 ft/min and the target speed, until the aircraft reaches the
altitude constraint or intercepts the descent profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
DSC-22_30-70-50 P 11/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - DESCENT MODE
Ident.: DSC-22_30-70-50-B-00010572.0001001 / 17 AUG 10
LEVELING OFF AT A CONSTRAINT
If the aircraft levels off at an ALT CSTR , the DES mode arms and remains armed until the
aircraft passes the constraint, then reengages (if the FCU altitude is set below the altitude of the
constraint).
If the FCU selected altitude is that of a constraint, the flight crew may continue the descent below
that altitude by turning the ALT knob and pushing it in. This arms the DES mode, which reengages
when the aircraft passes the constraint waypoint.
Ident.: DSC-22_30-70-50-B-00010573.0002001 / 17 AUG 10
GUIDANCE IN A HOLD
Just before the aircraft enters a holding pattern, the speed target becomes the holding speed.
In the holding pattern, the DES mode commands V/S = -1 000 ft/min while A/THR maintains the
holding speed. The aircraft will level off at the next altitude constraint if it is reached during the
hold.
The current vertical deviation VDEV is based on the altitude at which the aircraft is supposed to
cross the exit fix in order to be properly positioned on the descent profile.
Until the flight crew exits the hold, the FMGS in DES mode will maintain V/S = -1 000 ft/min
considering downpath vertical constraint. This means that the aircraft will not descent below the
next altitude constraint, neither the FCU selected altitude. If the aircraft reaches the next altitude
constraint it will level off and ALT CST mode will engage.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
DSC-22_30-70-50 P 12/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - DESCENT MODE
Ident.: DSC-22_30-70-50-B-00010574.0001001 / 01 OCT 12
TOO STEEP PATH
A descent segment is called “too steep path” when FM predicts that the descent segment between
two constraint waypoints is impossible to fly at the planned descent speed with half speedbrakes
extended.
When this occurs, the MCDU displays no predictions between the upper and the lower points of
the too steep path. Relevant message “TOO STEEP PATH” is displayed on MCDU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
DSC-22_30-70-50 P 13/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - DESCENT MODE
When the aircraft reaches the beginning of the too steep path segment, the FM recomputes the
VDEV using an idle segment from the end of the too steep path segment.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I
DSC-22_30-70-50 P 14/14
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - OPEN DESCENT MODE
GENERAL
Ident.: DSC-22_30-70-60-00010576.0001001 / 17 AUG 10
Applicable to: ALL
The OPEN DES mode is a selected mode. It maintains a SPD /MACH (selected or managed) with
the AP /FD pitch mode while autothrust (if active) maintains IDLE thrust.
It is not to be used for final approach.
ENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-60-00010577.0002001 / 17 AUG 10
Applicable to: ALL
The OPEN DES mode can be engaged only if the following conditions are met:
‐ The aircraft has been in flight for more than 5 s
‐ LAND mode is not engaged
‐ The FCU selected altitude is lower than present altitude.
The OPEN DES mode is engaged by one of the following:
‐ Pulling out the ALT knob
‐ Selecting a manual speed when EXP mode is engaged.
Note:
When OP DES is engaged:
‐ The FMA displays “OP DES”
‐ The managed LVL/CH dot on the FCU goes out
‐ The system arms the ALT mode.
DISENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-60-00010578.0003001 / 17 AUG 10
Applicable to: ALL
The OPEN DES mode is disengaged by one of the following conditions:
‐ Manual engagement of another vertical mode
‐ Selection of an altitude higher than present altitude. V/S (FPA ) engages on current V/S (FPA ).
The vertical mode is boxed white. If within 5 s after the reversion to V/S , the flight crew does not
confirm the altitude target change by another expected action, a triple click aural warning sounds,
and the V/S (FPA) is boxed white and flashes for 10 s.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C
DSC-22_30-70-60 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - OPEN DESCENT MODE
GUIDANCE
Ident.: DSC-22_30-70-60-00010579.0002001 / 16 MAR 11
Applicable to: ALL
When OPEN DES is engaged, pitch control maintains the target speed/Mach number, and autothrust
maintains idle thrust (or the flight crew maintains it manually). The speed target may be either
selected or managed.
The OPEN DES mode disregards all altitude constraints.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
DSC-22_30-70-60 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - ALTITUDE ACQUIRE MODE
GENERAL
Ident.: DSC-22_30-70-65-00010580.0002001 / 07 APR 17
Applicable to: ALL
ALT * mode guides the aircraft to acquire the FCU selected altitude.
ALT CST* guides the aircraft to acquire an altitude constraint provided by Flight Management. Once
the aircraft has reached the altitude, the altitude mode (ALT or ALT CST) engages.
ENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-65-00010581.0002001 / 23 JUN 15
Applicable to: ALL
The mode engages when the aircraft reaches the altitude capture zone, defined by the aircraft
vertical speed (among other parameters).
Note:
ALT * and ALT CST* cannot be engaged below 400 ft, if either the takeoff or the go-around
mode is engaged.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-22_30-70-65 P 1/4
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - ALTITUDE ACQUIRE MODE
DISENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-65-00010582.0008001 / 19 DEC 12
Applicable to: ALL
The mode is disengaged by one of the following conditions:
‐ Engagement of V/S mode on current vertical speed by turning the FCU ALT knob by more than
250 ft.
If within 5 s after reversion to V/S (FPA) the flight crew does not confirm the altitude target change
by:
• Pulling the ALT knob, or
• Setting a new V/S (FPA) target, or
• Pushing the V/S or FPA knob on the FCU,
then, a triple click aural warning sounds, and the V/S (FPA) is boxed white for additional 10 s.
‐ Engagement of another vertical mode provided the FCU altitude has been changed by more than
250 ft.
GUIDANCE
Ident.: DSC-22_30-70-65-00010583.0006001 / 07 APR 17
Applicable to: ALL
The ALT * and ALT CST* mode have internal V/S guidance that is a direct function of the difference
between present altitude and the altitude target.
The system switches automatically to ALT (altitude hold) when the altitude deviation becomes less
than 20 ft.
ALT * and ALT CST* modes have internal protections that decreases the vertical speed when VLS or
VMAX is reached (VLS or VMAX becomes the priority target).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D →
DSC-22_30-70-65 P 2/4
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
AP/FD VERTICAL MODES - ALTITUDE ACQUIRE MODE
‐ If the baro setting is changed during ALT * mode, this may lead to an FCU target
overshoot due to the change of the current value of the altitude. However ALT * mode
will allow the FCU altitude to be regained.
‐ For aircraft equipped with QFE option, a switching from STD to QFE (or vice versa) in
ALT CST* mode, will change the target value and a reversion to V/S may occur if the
target value is modified of 250 ft or more.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
DSC-22_30-70-65 P 3/4
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - ALTITUDE ACQUIRE MODE
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-70-65 P 4/4
12 APR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - ALTITUDE HOLD MODE
GENERAL
Ident.: DSC-22_30-70-70-00010584.0001001 / 17 AUG 10
Applicable to: ALL
The ALT mode maintains a target altitude. This target altitude is either the FCU selected altitude or
an altitude constraint delivered by Flight Management.
ARMING CONDITIONS
Ident.: DSC-22_30-70-70-00010585.0001001 / 17 AUG 10
Applicable to: ALL
The ALT mode arms automatically whenever the aircraft climbs or descends toward the target
altitude.
Note:
The ALT mode arms only if the difference between the current altitude and the FCU
selected altitude is at least 250 ft.
When ALT is armed, the FMA displays the ALT message on its second line:
‐ Blue when the target altitude is the FCU selected altitude
‐ Magenta if the target altitude is an altitude constraint.
ENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-70-00010586.0002001 / 17 AUG 10
Applicable to: ALL
The ALT mode is engaged automatically when the difference between present altitude and the target
altitude becomes less than 20 ft with ALT* engaged.
Note:
The ALT mode is displayed on the FMA when the V/S knob is pushed in or is pulled out
with V/S -FPA target set to zero but V/S mode is still active. In other words, if V/S knob is
dialled up or down, the aircraft will climb or descend without any pulling action.
DISENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-70-00010587.0001001 / 17 AUG 10
Applicable to: ALL
The ALT mode disengages when any other vertical mode engages.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to D
DSC-22_30-70-70 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - ALTITUDE HOLD MODE
GUIDANCE
Ident.: DSC-22_30-70-70-00010588.0002001 / 23 JUN 15
Applicable to: ALL
‐ The altitude that ALT mode holds is the altitude it memorized when engaged. It is not affected by a
change of reference in the ALT window or by a change in the barometric correction.
‐ When ALT is engaged, the FMA displays ALT in green (FCU altitude hold) or ALT CST in green if
it is an altitude constraint.
‐ If the AP is engaged while FD is already engaged in ALT mode at the FCU selected altitude, the
autopilot:
• Acquires and holds the FCU altitude if present altitude is within 250 ft of it, or
• Commands a level-off if present altitude is more than 250 ft from the FCU altitude.
SOFT ALTITUDE MODE (CRUISE)
Ident.: DSC-22_30-70-70-00010589.0002001 / 19 DEC 12
Applicable to: ALL
The soft altitude mode engages when the aircraft reaches the FCU altitude set as the cruise flight
level (entered in the F-PLN or on PROG page).
The soft altitude mode corrects minor deviations from the Mach target by allowing a ±50 ft variation
from the CRZ FL. This feature improves fuel efficiency and passenger comfort and minimizes the
changes in thrust.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E to F →
DSC-22_30-70-70 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - ALTITUDE HOLD MODE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
DSC-22_30-70-70 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - ALTITUDE HOLD MODE
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-70-70 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - VERTICAL SPEED
MODE - FLIGHT PATH ANGLE MODE (V/S - FPA)
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-70-80-00010611.0004001 / 19 DEC 12
Applicable to: ALL
The V/S - FPA mode is a selected mode. It acquires and holds the vertical speed or the flight path
angle displayed in the V/S - FPA window of the FCU.
The HDG V/S -TRK FPA pb on the FCU allows the flight crew to select either type of reference to be
used for guidance and for display on the PFD.
ENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-80-00010612.0003001 / 17 AUG 10
Applicable to: ALL
The flight crew can engage the mode manually as follows:
‐ Pull out the V/S or FPA knob (at least 5 s after lift-off) or push it in for an immediate level off
(V/S=0)
‐ Engage the AP and/or FD if AP and FD are not engaged (basic mode of AP /FD engagement)
‐ Select a different altitude (more than 250 ft from present altitude) when in ALT* mode
‐ Select a higher altitude than present altitude when in DES , OP DES modes or EXP DES
mode
‐ Select a lower altitude than present altitude when in CLB , OP CLB modes or EXP CLB mode.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_30-70-80 P 1/2
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - VERTICAL SPEED
MODE - FLIGHT PATH ANGLE MODE (V/S - FPA)
FLIGHT CREW
OPERATING MANUAL
The mode engages automatically:
‐ 5 s after lift-off, if no other vertical mode is engaged
‐ Upon loss of G/S * or G/S mode
‐ Upon loss of FINAL mode
‐ Upon loss of LOC * or LOC mode
‐ Upon loss of NAV mode when DES mode is engaged
‐ Upon loss of vertical flight path in DES mode.
DISENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-80-00010592.0002001 / 17 AUG 10
Applicable to: ALL
The flight crew can disengage the V/S mode manually by:
‐ Pulling or pushing the Altitude knob, or
‐ Pushing the EXPED pb , or
‐ Initiating a go-around.
It disengages automatically:
‐ When the aircraft reaches the FCU altitude, or
‐ Upon G/S* engagement.
GUIDANCE
Ident.: DSC-22_30-70-80-00010593.0009001 / 04 JUL 17
Applicable to: ALL
The FMGC pitch mode guides the aircraft to the target V/S or FPA . The corresponding A/THR mode
is SPEED or MACH. The FMA displays V/S (FPA).
The V/S (FPA ) guidance has priority over the speed guidance. If the selected target V/S or FPA is
too high (relative to the current thrust condition and speed), the FMGC will steer the aircraft to the
target V/S or FPA, but the aircraft will also accelerate or decelerate.
When the speed reaches its authorized limit, V/S or FPA automatically decreases to maintain the
minimum (or maximum) speed limit.
Note:
If the flight crew sets V/S = 0 or pushes the V/S or FPA knob to level off, it automatically
sets V/S or FPA target to zero and the aircraft levels off and maintains its altitude.
Note:
If AP is engaged while a V/S is selected with only FD ON, the V/S will synchronise on the
current aircraft V/S.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to D
DSC-22_30-70-80 P 2/2
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD VERTICAL MODES - EXPEDITE
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-70-90-00010223.0001001 / 17 AUG 10
Applicable to: ALL
Expedite mode is an OPEN mode used in climb or descent to reach the desired altitude with the
maximum vertical gradient.
ENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-90-00010594.0001001 / 17 AUG 10
Applicable to: ALL
The flight crew can engage EXPEDITE if:
‐ The aircraft has been in flight for more than 5 s
‐ Managed speed is available.
The flight crew engages EXPEDITE manually by pushing the EXPED pb on the FCU:
‐ If the FCU selected altitude is higher than present altitude, EXP CLB mode engages
‐ If the FCU selected altitude is lower than present altitude, EXP DES mode engages.
DISENGAGEMENT CONDITIONS
Ident.: DSC-22_30-70-90-00010595.0003001 / 17 AUG 10
Applicable to: ALL
The flight crew can disengage EXPEDITE manually by:
‐ Pulling out the V/S or FPA knob to engage the V/S or FPA mode
‐ Pulling out the ALT knob to engage OP CLB or OP DES
‐ Pulling out the SPD/MACH knob to activate the selected speed target and engage OP CLB or OP
DES. A white box appears around the longitudinal mode and flashes for 10 s. A triple click sounds
‐ Pushing in the ALT knob to engage the CLB or DES mode, provided that the engagement
conditions are met
‐ Selecting a higher altitude than present altitude when in EXP DES. If this action is not followed by
another expected flight crew action within 5 s, a triple click sounds. A steady white box appears
around the longitudinal mode, then flashes for 10 s after the triple click
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C →
DSC-22_30-70-90 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD VERTICAL MODES - EXPEDITE
‐ Selecting a lower altitude than present altitude when in EXP CLB. If this action is not followed by
another expected flight crew action within 5 s, a triple click sounds. A steady white box appears
around the longitudinal mode, then flashes for 10 s after the triple click
‐ Activating a reversion to V/S to protect the aircraft from exceeding VLS or VMAX. A white box
appears around the longitudinal mode and flashes for 10 s. A triple click sounds.
Note:
In FD mode only, it the flight crew does not follow the FD orders, a reversion to V/S
occurs when reaching VMAX + 4 in EXP CLB or VLS - 2 in EXP DES (VLS - 17 with
speedbrakes). Refer to DSC-22_30-75 General.
EXPEDITE disengages automatically with ALT* engagement.
GUIDANCE
Ident.: DSC-22_30-70-90-00010610.0002001 / 19 DEC 12
Applicable to: ALL
When the aircraft is in EXP CLB , the target speed is Green Dot, which is maintained with pitch
control. Autothrust, if active, sets the thrust at CLB THRUST automatically.
When the aircraft is in EXP DES, the target speed is 340 kt or M 0.8 which is maintained with pitch
control. Autothrust, if active, sets the thrust at IDLE automatically.
When EXPEDITE is engaged, the system disregards SPD CSTR , ALT CSTR , and SPD LIM.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
DSC-22_30-70-90 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-75-00010633.0001001 / 17 MAR 17
Applicable to: ALL
Mode reversions are automatic mode changes that unexpectedly occur, but are designed to ensure
coherent AP , FD and A/THR operations, in conjunction with flight crew input (or when entering a
F-PLN discontinuity).
Due to the unexpected nature of their occurrence, the FMA should be closely monitored for mode
reversions.
INTERACTION BETWEEN LATERAL MODES,
VERTICAL MODES, AND MANAGED SPEED PROFILE
Ident.: DSC-22_30-75-00012054.0006001 / 17 MAR 17
Applicable to: ALL
When NAV mode is engaged:
The FMGS guides the aircraft along the flight plan and considers the constraints attached to the
F-PLN waypoints. As a result:
‐ Managed CLB and DES modes are available
‐ The managed speed profile includes: V2 - SPD CSTR (if applicable) - SPD LIM - ECON CLB
SPD /MACH - ECON CRZ MACH - ECON DES (MANAGED SPD ) - SPD /MACH - SPD
CSTR - SPD LIM - HOLD SPD - VAPP /GS MIN.
It is valid for all vertical modes, except EXPEDITE .
When NAV mode is not engaged:
The FMGS considers that the flight plan is not followed, and ignores all speed and altitude
constraints linked to the F-PLN waypoints. As a result:
‐ The managed vertical CLB and DES modes are not available
‐ The managed SPD profile disregards the speed constraints and includes: V2 - SPD LIM ECON CLB - ECON CRZ - ECON DES (MANAGED SPD ) - SPD LIM - VAPP /GS MIN target.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_30-75 P 1/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
MODE REVERSIONS
As a consequence, when NAV mode disengages (manual or automatic):
‐ CLB mode, when engaged, reverts to OPEN CLB. The lateral mode is boxed white for 10 s. The
vertical mode is boxed white.
If within 5 s, the disengagement of the NAV mode is not confirmed by one of the following flight
crew actions:
• FCU altitude change
• Level-off
• Selection of the V/S mode
then, a triple click aural warning sounds. In addition, a white box flashes around the vertical mode
for additional 10 s.
‐ DES mode, when engaged, reverts to V/S mode on current value.
If within 5 s, the disengagement of the NAV mode is not confirmed by one of the following flight
crew actions:
• FCU altitude change
• Level-off
• Selection of the V/S mode
then, a triple click aural warning sounds. In addition, a white box flashes around the vertical mode
for additional 10 s.
This reversion to V/S (FPA ) mode on the current V/S target does not modify the pitch behavior of
the aircraft. It is the flight crew's responsibility to adapt pitch, if necessary.
‐ Speed and altitude constraints are disregarded (but speed limit is retained).
MODE REVERSION DUE TO FCU ALTITUDE CHANGE
Ident.: DSC-22_30-75-00012053.0006001 / 01 OCT 12
Applicable to: ALL
When an OPEN mode is engaged, the aircraft climbs or descends towards the altitude set on the
FCU . If the flight crew sets the FCU altitude to a target not compatible with the active open mode, a
mode reversion occurs and V/S (or FPA ) engages on current V/S (or FPA).
This reversion applies to CLB , OP CLB , DES , OP DES, EXP DES , EXP CLB .
Example: Reversion from OP CLB to V/S:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_30-75 P 2/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
With ALT * engaged, the target altitude is changed by any value greater than 250 ft, V/S (or FPA )
engages on currents V/S (or FPA). Refer to DSC-22_30-75 Mode Reversions (Summary).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-22_30-75 P 3/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
If within 5 s after the reversion to V/S (FPA), the flight crew does not confirm the altitude target
change by:
‐ Pulling the ALT knob, or
‐ Setting a new V/S (or FPA) target, or
‐ Pushing the V/S or FPA knob on the FCU,
then, a triple click sounds, and the V/S (FPA) is boxed white for additional 10 s.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
DSC-22_30-75 P 4/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
REVERSION WITH GLOBAL SPEED PROTECTION
Applicable to: ALL
Ident.: DSC-22_30-75-A-00012055.0010001 / 19 DEC 12
AUTOMATIC SPEED MODE PROTECTION IN CLIMB
FD s are engaged in an OPEN mode in climb with AP not engaged.
If FD s are engaged in CLIMB or OPEN CLIMB mode or EXP CLB and the flight crew does
not follow the FD bars to maintain the commanded climb (pitch too low and autothrust in maximum
climb thrust), the aircraft accelerates.
Both FD s disengage when VMAX +4 is reached (VMAX being VMO , VLE or VFE ). If the A/THR
is active, it reverts to SPEED mode and reduces the thrust to recover the speed target.
A triple click aural warning sounds.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
DSC-22_30-75 P 5/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_30-75-A-00012056.0010001 / 01 OCT 12
AUTOMATIC SPEED PROTECTION IN V/S (OR FPA) MODE IN CLIMB
When climbing with V/S mode engaged: If the selected V/S value is excessive (with regards
to thrust and speed), the FMGS maintains the V/S target, but the airspeed decreases. When
reaching VLS (or VLS -5, if the speed target is VLS ), the AP temporarily abandons the V/S target,
and automatically decreases the vertical speed to maintain VLS . The same applies if FPA mode is
used with an excessive FPA target.
V/S mode remains engaged.
On the FMA , the V/S target is boxed with a flashing amber rectangle, and the V/S value pulses.
Besides, an aural triple click is generated.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-22_30-75 P 6/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
Note:
When flying with FD bars only (AP OFF), the FMGS adjusts the pitch bar so that VLS is
maintained. However, no triple click is generated and the V/S target display on the FMA
remains unchanged.
Ident.: DSC-22_30-75-A-00012057.0010001 / 01 OCT 12
AUTOMATIC SPEED MODE PROTECTION IN DESCENT
FD s are engaged in an OPEN mode in descent with the AP not engaged.
If the FD s are engaged in DES , or OP DES mode, or EXP DES and, if the flight crew does
not follow the FD bars to maintain the commanded pitch, the aircraft decelerates (insufficient
descent rate and idle thrust).
If the airspeed reaches VLS -2, both FD s disengage. (If speedbrakes are extended, the FD s
disengage between VLS -2 and VLS-19, depending on the position of the speedbrakes).
The A/THR , if active, reverts to SPEED mode upon FDs disengagement, and increases thrust to
recover the speed target.
A triple-click aural warning sounds.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-22_30-75 P 7/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_30-75-A-00012058.0010001 / 01 OCT 12
AUTOMATIC SPEED PROTECTION IN V/S (OR FPA) MODE IN DESCENT
When descending with V/S mode engaged: If the selected V/S value is excessive (with regards to
thrust and speed), the FMGS maintains the V/S target, but the airspeed increases. When reaching
VMAX (VMO or VLE in clean, or VFE +4 kt), the AP temporarily abandons the V/S target, and
automatically decreases the vertical speed to maintain VMAX.
The same applies if FPA mode is used with an excessive FPA target.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-22_30-75 P 8/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
V/S mode remains engaged.
On the FMA , the V/S target is boxed with a flashing amber rectangle, and the V/S values pulses.
Besides, an aural triple click is generated.
Note:
When flying with FD bars only (AP OFF), the FMGS adjusts the pitch bar so that VMAX
is maintained. However, no triple click is generated and the V/S target display on the
FMA remains unchanged.
MODE REVERSIONS (SUMMARY)
Ident.: DSC-22_30-75-00012052.0005001 / 23 JUN 15
Applicable to: ALL
There are only 2 types of vertical mode reversions on aircraft equipped with global speed protection.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
DSC-22_30-75 P 9/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
REVERSION DUE TO A CHANGE OF THE FCU SELECTED ALTITUDE
Vertical Mode Engaged
CLB - OP CLB
EXP CLB
DES - OP DES
EXP DES
ALT* ACTIVE
FCU Altitude Selection Change
Vertical Mode Switches to
Below aircraft altitude
Above aircraft altitude
V/S on current V/S
Any change
REVERSION DUE TO THE LOSS OF NAV MODE (MANUAL OR AUTOMATIC)
CONDITIONS
CLB engaged
DES engaged
EVENT
CONSEQUENCE
OP CLB engages
V/S engages
Loss of NAV mode
SPEED PROTECTION WHEN FD ORDERS ARE NOT FOLLOWED BY THE FLIGHT CREW (AP
NOT ENGAGED)
CONDITIONS
‐ FD engaged only (no AP), and
‐ OP DES or EXP DES or DES
engaged
‐ A/THR active (IDLE thrust)
‐ FD engaged only (no AP), and
‐ OP CLB or EXP CLB or CLB
engaged
‐ A/THR active (CLIMB thrust)
EVENT
IAS = VLS-2
(if speedbrakes are extended between
VLS -2 and VLS-19)
IAS = VMAX+4
VMAX = VFE or VLE or VMO /MMO
CONSEQUENCE
FD bars disappear.
If A/THR active, automatic
engagement of SPEED mode on
the A/THR.
Thrust increases to recover the
speed target.
FD bars disappear.
If A/THR active, automatic
engagement of SPEED mode on
the A/THR.
Thrust decreases to recover the
speed target.
SPEED PROTECTION DUE TO EXCESSIVE V/S
CONDITIONS
Excessive V/S or FPA selected in climb
‐ Excessive V/S or FPA selected in
descent, and
‐ Clean configuration
‐ Excessive V/S or FPA < 0 selected in
descent, and
‐ Configuration other than clean
EVENT
IAS = VLS (or VLS -5, if
target = VLS)
IAS = VMAX
CONSEQUENCE
The selected V/S (or FPA ) target is temporarily
abandoned to maintain VLS in climb or VMAX in
descent.
IAS = VMAX
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
DSC-22_30-75 P 10/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
ENHANCED MODE REVERSION ALERTNESS
The following sequences, or mode reversions, are highlighted by a triple click:
‐ V/S selection in ALT*
‐ SPD selection in SRS
‐ CLB (or EXP CLB ) to OP CLB, upon lateral flight crew action while climbing toward a
constraint
‐ ALT * to V/S , upon ALT target change
‐ FD disengagement in OPEN modes
‐ Alerting FMA display when V/S -(FPA) target is not held
‐ CLB to OP CLB reversion, upon profile loss
‐ Automatic FD re-engagement in basic mode
‐ DES to V/S upon flight plan loss
‐ FINAL DES to V/S , upon NAV loss
‐ Reversion to V/S when selected ALT crosses the current altitude
‐ NAV to HDG , upon NAV loss.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
DSC-22_30-75 P 11/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
MODE REVERSIONS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-75 P 12/12
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-80-10-00011875.0001001 / 17 AUG 10
Applicable to: ALL
These modes are called “common” because they are related to both the lateral and the vertical axes.
The AP /FD common modes are:
‐ On takeoff: Runway/Runway track associated to SRS vertical modes
‐ In approach: ILS approach (LAND) or non-ILS approach (APP NAV FINAL)
‐ In go around: Go around track associated to SRS vertical modes.
These modes are engaged simultaneously on both axes.
COMMON MODES
VERTICAL
TAKEOFF
SRS
G/S*
G/S
ILS
APPROACH
APPROACH
MODES
GO AROUND
(GA)
NON-ILS
APPROACH
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
LATERAL
LAND, FLARE,
ROLL OUT
RWY
RWY TRK
LOC*
LOC
FINAL
APP NAV
SRS
GA TRK
DSC-22_30-80-10 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-80-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - TAKEOFF
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-80-20-00012253.0001001 / 17 AUG 10
Applicable to: ALL
Takeoff mode combines the SRS (Speed Reference System) vertical mode with the RWY lateral
mode. Both are simultaneously engaged, but may be disengaged separately.
Takeoff mode is available:
‐ During the takeoff run and initial climb for FD bars guidance
‐ 5 s after lift-off for AP use.
SRS (SPEED REFERENCE SYSTEM)
Applicable to: ALL
Ident.: DSC-22_30-80-20-A-00012260.0001001 / 17 AUG 10
GENERAL
The SRS mode controls pitch to steer the aircraft along a path in the vertical plan at a speed
defined by the SRS guidance law.
Ident.: DSC-22_30-80-20-A-00012256.0001001 / 23 JUN 15
ENGAGEMENT CONDITIONS
The SRS mode engages automatically when the thrust levers are set to the TOGA or FLX/MCT
detent, providing:
‐ V2 has been inserted in the MCDU PERF TAKEOFF page
‐ The slats are extended
‐ The aircraft has been on ground for at least 30 s.
Ident.: DSC-22_30-80-20-A-00012258.0002001 / 23 JUN 15
DISENGAGEMENT CONDITIONS
The SRS mode disengages:
‐ Automatically, at the acceleration altitude (ACC ALT ), or if ALT * or ALT CST* mode engages
(above 400 ft RA)
‐ If the flight crew engages another vertical mode
‐ If the flight crew selects a speed while in SRS mode: SRS reverts to OP CLB mode, and a
triple-click aural warning is heard.
Note:
In Engine Out conditions, the SRS mode does not automatically disengage at EO ACC
ALT. Refer to DSC-22_20-60-40 General.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_30-80-20 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - TAKEOFF
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_30-80-20-A-00012259.0011001 / 16 MAR 11
GUIDANCE
In SRS mode, the aircraft maintains a speed target equal to V2 +10 kt in normal engine
configuration. When the FMGS detects an engine failure, the speed target becomes the highest of
V2 or current speed, limited by V2+15 kt.
The SRS guidance law also includes:
‐ Attitude protection to reduce aircraft nose-up effect during takeoff (18 ° or 22.5 ° maximum in
case of windshear)
‐ Flight path angle protection that ensures a minimum vertical speed of 120 ft/min
‐ A speed protection limiting the target speed to V2+15 kt.
Note:
If during takeoff the flight crew inadvertently sets an altitude on the FCU below the
current altitude, the aircraft will remain in SRS mode until the flight crew takes some
other action.
RUNWAY (RWY)
Applicable to: ALL
Ident.: DSC-22_30-80-20-B-00012255.0001001 / 17 AUG 10
GENERAL
The RUNWAY mode has two submodes:
‐ RWY mode, which gives lateral guidance orders during takeoff roll and initial climb out (up to
30 ft RA ) if a LOC signal is available
‐ RWY TRK mode, which gives lateral guidance on the track the aircraft was flying at mode
engagement (at 30 ft RA).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_30-80-20 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD COMMON MODES - TAKEOFF
Ident.: DSC-22_30-80-20-B-00012323.0001001 / 17 AUG 10
ENGAGEMENT CONDITIONS
The RWY engagement conditions are:
‐ The conditions required for SRS mode engagement:
• V2 is inserted in the MCDU PERF TAKEOFF page
• Slats are extended
• The aircraft has been on ground for at least 30 s.
‐ The aircraft is receiving a LOC signal and LOC deviation is less than 1/2 dot
‐ The aircraft heading is within 20 ° of the ILS related course
‐ The ILS course is identical to the runway heading of the origin airport as selected for the active
flight plan, if any.
The RWY TRK mode engages automatically at 30 ft (RA ) if NAV mode does not engage (NAV not
armed prior to takeoff).
Ident.: DSC-22_30-80-20-B-00012324.0001001 / 17 AUG 10
DISENGAGEMENT CONDITIONS
RWY mode disengages if:
‐ The LOC signal is lost below 30 ft RA or the aircraft heading and the runway heading differ by
more than 20 °.
‐ Another lateral mode is engaged.
Note:
If the takeoff runway has no ILS , RWY mode is not available and the PFD does not
display the yaw bar nor "RWY " on FMA.
Ident.: DSC-22_30-80-20-B-00012325.0002001 / 16 MAR 11
GUIDANCE
The RWY mode uses the LOC signal to guide the aircraft on the runway centerline while the
aircraft is on the ground. The PFD displays the FD yaw bar and the FMA displays "RWY".
The RWY TRK mode guides the aircraft on the track the aircraft was flying at mode engagement.
The FD displays the conventional guidance bar and the FMA displays “RWY TRK”.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-22_30-80-20 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AP/FD COMMON MODES - TAKEOFF
←C
DSC-22_30-80-20 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD COMMON MODES - APPROACH
General
GENERAL
Ident.: DSC-22_30-80-30-05-00012378.0008001 / 01 OCT 12
Applicable to: ALL
The aircraft can fly different types of approaches:
‐ Precision approaches: ILS, MLS
‐ Non-precision approaches: VOR /DME , VOR , NDB (if ADF ), RNAV
‐ Non-precision approaches using a Localizer only: LOC.
The flight crew uses an ARRIVAL lateral revision to insert these approaches into the flight plan:
‐ For precision approaches, the flight crew uses the APPR pb on the FCU to arm or engage the
LOC and G/S guidance modes
‐ For non-precision approaches, the flight crew uses the APPR pb on the FCU to arm or engage
the APP NAV and FINAL guidance modes, except for LOC approaches, where the flight crew only
uses the LOC pb to arm or engage the LOC mode.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-22_30-80-30-05 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - APPROACH
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-80-30-05 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - APPROACH
FLIGHT CREW
OPERATING MANUAL
Precision Approach
PRECISION APPROACH MODES
Applicable to: ALL
Ident.: DSC-22_30-80-30-10-A-00012379.0003001 / 01 OCT 12
GENERAL
The ILS approach mode includes the following modes:
VERTICAL MODE
G/S* (capture)
G/S (track)
COMMON MODES:
LAND - FLARE - ROLL OUT
LATERAL MODE
LOC* (capture)
LOC (track)
The sequencing of these modes is automatic once the flight crew has pushed the APPR pb and
the conditions for engagement are met.
SELECTION
The ILS approach is selected when the APPR pb of the FCU is pressed and:
‐ An ILS approach or a runway only or no approach is inserted in the Flight Management flight
plan (ARRIVAL page), and an ILS frequency is set in on the MCDU, or
‐ Both radio management panels are set to NAV and each one has the ILS frequency and
course set in.
CHECK APPROACH SELECTION MESSAGE
If the flight crew inserts a non-ILS approach into the flight plan, and then uses the RAD NAV
page to tune an ILS manually, the MCDU displays “CHECK APPR SELECTION”. This message
is a reminder that the available APPR guidance modes are APP NAV and FINAL.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-22_30-80-30-10 P 1/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD COMMON MODES - APPROACH
Ident.: DSC-22_30-80-30-10-A-00012380.0067001 / 03 DEC 13
APPR MODE
ARMING CONDITIONS OF LOC AND G/S MODES
The flight crew arms the ILS APPR mode (LOC and G/S in blue on the FMA ) by pushing the
APPR pb on the FCU, provided that:
‐ An ILS approach is selected
‐ The aircraft is above 400 ft RA
‐ The ILS and RA are available
‐ Go-around or takeoff or final mode is not engaged
‐ ILS frequency and course are identically set on both receivers.
LOC and G/S blue are displayed on the FMA. Both modes will automatically engage when
conditions are met.
Second autopilot may be engaged.
Current landing capability is displayed on the FMA.
DISARMING CONDITIONS OF LOC AND G/S MODES
ILS APPR mode is disarmed, if the aircraft is above 400 ft and:
‐ When the flight crew presses the APPR pb, both the LOC and the G/S modes disarm.
The HDG /TRK mode engages if the LOC mode was engaged, and the V/S (FPA ) mode
engages if the G/S mode was engaged
‐ When the flight crew presses the LOC pb, only the G/S mode disarms.
The V/S (FPA ) mode engages, if the G/S mode was engaged
‐ When the flight crew pulls the HDG/TRK knob
‐ When the flight crew engages the go-around mode.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_30-80-30-10 P 2/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD COMMON MODES - APPROACH
ENGAGEMENT CONDITIONS OF LOC AND G/S MODES
When ILS capture conditions are fulfilled:
‐ LOC* mode engages, and
‐ G/S * mode engages. No radio altimeter validity is required with this FMGC standard for G/S
engagement. The FMA displays “LOC *”, or “G/S*”, or both, in green.
Nevertheless, the G/S* mode cannot engage, if:
‐ LOC* mode is not engaged, or
‐ The aircraft is above the glide path and its trajectory does not cross the ILS G/S beam.
When the aircraft is established on the LOC axis, the LOC mode engages.
When the aircraft is established on the G/S axis, the G/S mode engages.
The FMA displays “LOC ” and “G/S ” in green. The AP /FD guides the aircraft along the G/S
down to 30 ft, and along the LOC during the flare and rollout.
Note:
G/S * or G/S modes may be engaged above the operating range of the radio altimeters
(8 000 ft for TRT, and 5 000 ft for Collins and Honeywell radio altimeters). The landing
capability displayed on the FMA will reflect the lack of RA validity (CAT 1) until the
radio altimeters become active.
But, if the radio altimeters fail, or if the FMGS receives no radio altimeter data, LOC ,
G/S , and AP /FD s will disengage and FDs will re-engage on basic modes.
DISENGAGEMENT CONDITIONS OF LOC AND G/S MODES
If the aircraft is above 400 ft, the ILS APPR mode disengages when the flight crew:
‐ Presses the APPR pb, HDG V/S or TRK FPA engages
‐ Presses the LOC pb, the LOC mode remains engaged. The system reverts to V/S (FPA ), if
G/S was engaged
‐ Pulls out the HDG/TRK knob, HDG V/S or TRK FPA engages
‐ Engages the go-around mode
‐ When the LOC or G/S signal has been lost for 7 s or more above 200 ft RA . AP /FD s
disengage and FD s reengage in basic modes (HDG V/S or TRK FPA).
DISENGAGEMENT CONDITIONS OF G/S ONLY
‐ The flight crew pulls out the V/S or FPA knob. LOC mode remains engaged, but G/S mode
disengages and V/S or FPA engages.
‐ The flight crew pushes or pulls the ALT knob. LOC mode remains engaged, and the mode
selected by the flight crew engages, as a function of the FCU selected altitude.
LOC CONVERGENCE FUNCTION
The aim of the LOC Convergence function is to help the aircraft intercept and capture the LOC
axis.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_30-80-30-10 P 3/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD COMMON MODES - APPROACH
The aircraft is guided with a converging track of 20 ° from the LOC axis, when all the following
conditions are met:
‐ NAV mode is engaged, and LOC mode is armed
‐ The aircraft is within 20 NM of the destination runway
‐ The difference between the aircraft track and the QFU is less than 20 °.
ENHANCED LOC CAPTURE FUNCTION
The Enhanced LOC Capture function enhances the performance of the LOC capture and helps
the aircraft to capture the LOC beam without overshoot.
Pre-Capture of the LOC Beam
The pre-capture of the LOC beam aims to begin the LOC beam capture sooner.
LOC * mode may engage when LOC mode is armed and when the aircraft reaches the LOC
pre-capture zone. The LOC pre-capture zone is a geographical zone around LOC beam
where it is possible to guide the aircraft toward the LOC beam, with the help of FMS position
data. To ensure the capture of the LOC beam, the aircraft is guided with a 15 ° convergence
angle with respect to runway QFU.
The LOC* mode engagement in the pre-capture zone is possible, when :
‐ The LOC deviation is more than 2.3 dots
‐ The FMS is in GPS PRIMARY
‐ The difference between the track and the QFU is between 25 ° and 115 °
‐ The guidance roll order is such that LOC * will capture the LOC beam without overshoot.
When the LOC deviation becomes lower than 2.3 dots, LOC * mode no longer uses the FMS
position data for guidance, but the actual LOC beam deviation to complete the capture of the
axis.
Capture of the LOC Beam
Current conditions of LOC beam capture in the capture zone remain the same. This means
that if approach conditions of the aircraft (interception angle, speed) do not need activation of
the capture assistance, the LOC beam capture will occur as usual based on LOC deviation,
aircraft track and guidance roll order conditions.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_30-80-30-10 P 4/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
AP/FD COMMON MODES - APPROACH
On the PFD and on the ND , the flight crew will observe movement of the LOC
deviation toward the center of the scale, only when the LOC deviation is less than 2
dots. This occurs when the aircraft is in the capture zone.
When the ILS frequency or the ILS ident entered on the RAD NAV page differs from the ILS
of the destination runway entered in the Flight Plan :
‐ The aircraft loses the LOC capture assistance function
‐ The “RWY/LS MISMATCH” message is displayed on the scratchpad
‐ The flight crew should select HDG mode to perform the LOC capture.
Note:
There is no glideslope capture assistance. The flight crew shall ensure that the
aircraft flight path intercepts the G/S beam.
Ident.: DSC-22_30-80-30-10-A-00012381.0002001 / 17 AUG 10
LAND MODE
ENGAGEMENT CONDITIONS
LAND mode automatically engages when the LOC and G/S modes are engaged, and the
aircraft is below 400 ft RA . The FMA displays “LAND”, indicating that LOC and G/S are
locked. No action on the FCU will disengage LAND mode. FLARE and ROLL OUT modes will
successively engage.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-22_30-80-30-10 P 5/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD COMMON MODES - APPROACH
DISENGAGEMENT CONDITIONS
LAND mode disengages:
‐ Upon engagement of the go-around mode
‐ If the flight crew presses the APPR pb, when the aircraft has been on ground for at least 10 s
with the autopilot disconnected
‐ When both AP /FDs are disengaged.
Note:
When LAND is not displayed on the FMA , at/or slightly below 400 ft, the landing
capability degrades to CAT 1 and the triple click is generated. No autoland is
authorized with CAT 1 displayed on the FMA.
Ident.: DSC-22_30-80-30-10-A-00012382.0001001 / 17 AUG 10
FLARE MODE
Once the aircraft reaches approximately 40 ft RA (the precise value is a function of V/S):
‐ The FLARE mode engages
‐ The FMA displays “FLARE” in green.
At 30 ft RA , the AP /FD aligns the yaw axis with the runway centerline and the aircraft flares
on the pitch axis. If the autothrust is active, thrust is automatically reduced to IDLE (Refer to
DSC-22_30-90 A/THR Modes - RETARD Mode).
When both AP /FDs are disengaged, FLARE mode disengages.
After main landing gear touchdown, the autopilot (if engaged) sends a nose down order.
ALIGN SUB-MODE
ALIGN is a sub-mode of LAND mode that lines up the aircraft’s axis with the ILS course. It is not
displayed to the flight crew.
Ident.: DSC-22_30-80-30-10-A-00012383.0001001 / 17 AUG 10
ROLL OUT MODE
At touchdown, the ROLL OUT mode engages and guides the aircraft along the runway centerline.
The FMA displays “ROLL OUT” in green, and the PFD displays the yaw bar and no FD bars.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-22_30-80-30-10 P 6/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - APPROACH
FLIGHT CREW
OPERATING MANUAL
SPEED CONTROL
Ident.: DSC-22_30-80-30-10-00012384.0001001 / 17 AUG 10
Applicable to: ALL
The autothrust, when active, controls speed. The approach speed target (VAPP ) is either managed
by the FMGS or selected by the flight crew:
‐ When managed, the speed target is computed by the FMGS and may be modified by the flight
crew through the MCDU . At 700 ft RA , the current speed target value is memorized by the
autothrust, to ensure stabilized speed guidance, even if Flight Management fails. Below 700 ft, any
new VAPP or WIND entry in the MCDU has no effect on the speed target.
‐ When selected, the autothrust always targets the speed selected on the FCU.
TYPICAL ILS APPROACH
Ident.: DSC-22_30-80-30-10-00012385.0001001 / 16 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B to C
DSC-22_30-80-30-10 P 7/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - APPROACH
FLIGHT CREW
OPERATING MANUAL
AUTOLAND WARNING LIGHT
Ident.: DSC-22_30-80-30-10-00012386.0001001 / 03 JUN 14
Applicable to: ALL
The following situations, when occurring below 200 ft RA with the aircraft in LAND mode, trigger the
flashing Autoland red warning:
‐ Both AP s OFF below 200 ft RA.
‐ Excessive deviation in LOC (1/4 dot above 15 ft RA ) or GLIDE (1 dot above 100 ft RA ). In
addition, LOC and GLIDE scales flash on the PFD.
‐ Loss of LOC signal above 15 ft, or loss of GLIDE signal above 100 ft. The FD bars flash on the
PFD. The LAND mode remains engaged.
‐ The difference between both radio altimeter indications is greater than 15 ft.
LANDING CAPABILITIES
Ident.: DSC-22_30-80-30-10-00012387.0001001 / 17 AUG 10
Applicable to: ALL
Each FMGC computes its own automatic landing capability.
The FMA displays “CAT 1”, “CAT 2”, “CAT 3 SINGLE” or “CAT 3 DUAL” messages as soon as the
APPR pb is pushed in to arm ILS approach modes.
Refer to PRO-NOR-SRP-01-70 Initial Approach.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D to E
DSC-22_30-80-30-10 P 8/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - APPROACH
FLIGHT CREW
OPERATING MANUAL
Non Precision Approach
GENERAL
Ident.: DSC-22_30-80-30-20-00012388.0090001 / 01 OCT 12
Applicable to: ALL
This mode guides the aircraft laterally and vertically down to the minimum along the final descent
profile computed by the FMGS.
This mode is used to fly a non-ILS approach (VOR , VOR /DME , NDB (if ADF ), RNAV...) as
inserted into the flight plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-22_30-80-30-20 P 1/6
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD COMMON MODES - APPROACH
The non-ILS approach includes the following managed modes:
‐ APP NAV mode for lateral guidance
‐ FINAL mode for vertical guidance.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-22_30-80-30-20 P 2/6
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - APPROACH
FLIGHT CREW
OPERATING MANUAL
SELECTION
Ident.: DSC-22_30-80-30-20-00012389.0001001 / 17 AUG 10
Applicable to: ALL
A non-ILS approach (VOR , VOR /DME , NDB (if ADF ), RNAV) is selected if the active flight plan
calls for it (and it has been inserted in that flight plan).
ARMING CONDITIONS
Ident.: DSC-22_30-80-30-20-00012390.0001001 / 17 AUG 10
Applicable to: ALL
The flight crew arms the APP NAV and FINAL modes by pressing the APPR pb on the FCU, if all of
the following conditions are met:
‐ The aircraft is above 400 ft AGL
‐ The flight plan is valid (lateral and vertical profile)
‐ The active flight plan has selected a non-ILS approach
‐ GA mode is not engaged.
The FMA displays “FINAL” and “APP NAV” in blue.
If NAV mode was already engaged, APP NAV engages immediately.
DISARMING CONDITIONS
Ident.: DSC-22_30-80-30-20-00012391.0001001 / 17 AUG 10
Applicable to: ALL
FINAL and APP NAV modes are disarmed if the flight crew:
‐ Presses the APPR pb, or
‐ Presses the LOC pb arming the LOC mode, or
‐ Engages the GO AROUND mode.
ENGAGEMENT CONDITIONS
Ident.: DSC-22_30-80-30-20-00012392.0003001 / 08 AUG 17
Applicable to: ALL
APP NAV and NAV modes engage under the same conditions:
If NAV mode was engaged, APP NAV engages immediately. If HDG /TRK is engaged, APP NAV
engages when the intercept conditions are met (aircraft track line must intercept the flight plan active
leg).
APP NAV will not engage if the "TO" waypoint is not displayed in white on the ND and MCDU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B to E →
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05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD COMMON MODES - APPROACH
FINAL APP is a lateral and vertical managed guidance approach mode that aims guiding aircraft
from FDP down to MAP along a defined FPA It is thus recommended to arm this mode when the TO
waypoint is the FDP.
FINAL APP mode engages when:
• NAV or APP NAV is engaged,
• FINAL is armed (by pressing APPR on the FCU),
• Predictions are available in FMS,
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD COMMON MODES - APPROACH
• APPROACH phase is active,
Note:
APPROACH phase may have to be manually activated on MCDU PERF page if the
approach starts at high altitude above aerodrome level (i.e. RNAV (RNP) approaches).
• The aircraft is within the capture area of the FMS profile:
‐ Laterally: ±1.5 NM from the Final Descent Point.
‐ Vertically: +150 ft above the Final Descent Point.
• The aircraft intercepts a descending leg of the vertical flight path.
Note:
if APPR pb is pressed earlier, FINAL APP mode may engage. As a consequence,
resulting speed and altitude management in FINAL APP may be inappropriate before
FDP.
A blue arrow is displayed on ND s to indicate where the FINAL APP engagement conditions are met
and where the final descent will begin automatically.
If the same arrow is displayed in white, at least one engagement condition is not fulfilled, FINAL APP
will not engage and the aircraft will not descend automatically.
Definition of the Final Descent Point (also called Vertical Intersection Point "VIP" for RNAV
(RNP) approaches)
The Final Descent Point is the waypoint from which starts the FMS segment with coded FPA . For
RNAV (RNP ) approaches, this point may be indicated on the chart as "VIP".
This point is defined in the Navigation Database by:
‐ A constant vertical flight path beyond this point,
‐ A coded altitude constraint that may be "at" or "at or above" (e.g. +3 000 ft). This constraint
is displayed on ND (in magenta), next to the corresponding waypoint, when the CSTR key is
selected on the EFIS Control Panel. It is also shown on the F-PLN page at this WPT.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - APPROACH
FLIGHT CREW
OPERATING MANUAL
Note:
The Final Approach Fix (FAF ) is the position from where the obstacle clearance is defined
relative to an Obstacle Clearance Surface (OCS). Obstacle clearance is only ensured if
the aircraft is flying on the defined vertical flight path. Before the FAF , minimum altitudes
are published with fixed Minimum Obstacle Clearance (MOC). The Final Descent Point is
the point in the procedure at or before the FAF from which a constant vertical flight path is
defined.
DISENGAGEMENT CONDITIONS
Ident.: DSC-22_30-80-30-20-00012393.0037001 / 17 MAR 15
Applicable to: ALL
The FINAL and APP NAV modes disengage:
‐ If the flight crew pushes the APPR pb (HDG -V/S or TRK -FPA modes engage)
‐ If the flight crew pushes the LOC pb (LOC mode arms if an ILS is selected and HDG -V/S or TRK
-FPA modes engage)
‐ If the flight crew pulls out the HDG/TRK knob, the FMGS reverts to HDG -V/S or TRK -FPA basic
modes
‐ Automatically at missed Approach Point .
‐ When the GO AROUND mode engages.
Note:
If the flight crew engages V/S or FPA mode, only FINAL mode disengages. NAV mode
remains engaged.
GUIDANCE
Ident.: DSC-22_30-80-30-20-00012394.0021001 / 18 MAR 11
Applicable to: ALL
The FINAL mode guides the aircraft on the vertical profile down to the minimum.
The FINAL mode does the following:
‐ Displays a vertical deviation scale (± 200 ft) on the PFD and a VDEV symbol showing deviation
from descent path
‐ Anticipates leaving the altitude selected by the FCU when the aircraft reaches the Continue
Descent symbol (blue arrow on the ND)
‐ Gives precise vertical guidance on the descent and final path with an internal vertical speed
limitation to avoid excessive V/S.
If the autopilot is engaged while you are using the APP NAV/ FINAL modes, it disengages
automatically at the Missed Approach Point (MAP).
FD modes revert to HDG -V/S or TRK -FPA basic modes.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AP/FD COMMON MODES - GO AROUND (GA)
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-80-40-00012050.0001001 / 17 AUG 10
Applicable to: ALL
Go-around mode combines the Speed Reference System (SRS ) vertical mode with the GA TRK
lateral mode.
ENGAGEMENT CONDITIONS
Ident.: DSC-22_30-80-40-00012210.0002001 / 17 AUG 10
Applicable to: ALL
Setting at least one thrust lever to the TOGA detent engages both SRS /GA TRK modes, if:
‐ The flaps lever is at least in position 1, and
‐ The aircraft is in flight, or
‐ The aircraft has been on ground for less than 30 s (AP disengages and can be re-engaged 5 s
after lift-off).
FD bars are automatically restored in SRS /GA TRK modes. If FPV /FPD was previously selected, it
reverts to FD bars.
The FMA displays “SRS ” and “GA TRK” in green.
DISENGAGEMENT CONDITIONS
Ident.: DSC-22_30-80-40-00012220.0028001 / 17 AUG 10
Applicable to: ALL
The SRS mode disengages:
‐ Automatically, at the Go-around acceleration altitude (GA ACC ALT ), or if ALT * mode engages
(above 400 ft RA)
‐ If the flight crew engages another vertical mode
‐ If the flight crew selects a speed while in SRS mode: SRS reverts to OP CLB mode and a
triple-click aural warning is heard.
Note:
In Engine Out conditions, the SRS mode does not automatically disengage at EO ACC
ALT. Refer to DSC-22_20-60-40 General.
GA TRK disengages when the flight crew engages another lateral mode, above 100 ft RA.
Note:
In dual AP configuration, disengagement of the Go-around mode on either axis causes AP2
to disconnect.
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FCOM
A to C
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AP/FD COMMON MODES - GO AROUND (GA)
GUIDANCE
Ident.: DSC-22_30-80-40-00012213.0009001 / 16 MAR 11
Applicable to: ALL
The SRS law maintains the current speed at Go-around engagement, or VAPP , whichever is higher.
Nevertheless, the SRS speed target is limited to VLS +25 kt, in a two-engine configuration, and VLS
+15 kt, in an engine-out configuration. When the SRS mode disengages, the target speed becomes
the smaller of green dot speed or speed constraints.
GA TRK mode guides the aircraft along the current track at Go-around initiation.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_30-90-00011930.0001001 / 17 MAR 17
Applicable to: ALL
The autothrust (A/THR ) is a function of the FMGS , it includes two independent A/THR commands,
one per FMGC . Each one is able to control the thrust of both engines simultaneously through two
Engine Interface Units and two Electronic Engine Controls (IAE engines) or two Engine Control Units
(CFM engines). Only one FMGC controls the active A/THR , it is called the master FMGC.
Thrust is controlled:
‐ Automatically when the A/THR is active
‐ Manually by the flight crew.
The autothrust is active when the A/THR pb of the FCU is lighted green and A/THR is displayed
white in the FMA 5th column.
The position of the thrust levers determines whether A/THR is armed, active, or disconnected.
The autothrust system, when active:
‐ Maintains a specific thrust in THRUST mode
‐ Controls the aircraft speed or Mach in SPEED/MACH mode
‐ Uses ALPHA FLOOR mode to set maximum thrust when the aircraft angle of attack exceeds a
specific threshold.
The autothrust system can operate independently or with the AP /FD:
‐ When performing alone, A/THR always controls the speed
‐ If the autothrust system is working with the AP /FD , the A/THR mode and AP /FD pitch modes are
linked together. Refer to DSC-22_30-10 Interaction between AP/FD and A/THR Modes.
When autothrust is active, the FMGS commands the thrust according to the vertical mode logic, but
uses a thrust not greater than the thrust commanded by the position of the thrust lever. For example,
when the thrust levers are set at the CL (climb) detent, FG can command thrust between idle and
max climb.
The autothrust system, when armed, automatically activates if the thrust levers are moved into the
active range sector. Outside of this range, thrust levers control thrust directly.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
THRUST LEVERS
Ident.: DSC-22_30-90-00011957.0001001 / 23 JUN 15
Applicable to: ALL
The flight crew uses the thrust levers to do the following:
‐ Manually select engine thrust
‐ Arm and activate autothrust (A/THR)
‐ Engage reverse thrust
‐ Engage the takeoff and go-around modes.
When autothrust is disconnected, the thrust levers control thrust directly: each lever position
corresponds to a given thrust.
Five detents divide each of the thrust lever sectors into four segments. The detents are:
: Max takeoff thrust
TO GA
FLX MCT : Max continuous thrust (or FLX at takeoff)
CL
: Maximum climb thrust
IDLE
: Idle thrust for both forward and reverse thrust
MAX REV : Maximum reverse thrust
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
When the thrust levers are at the IDLE position, the flight crew can pull them up to clear the IDLE
stop and select reverse thrust. (There is no reverse detent as such).
A/THR ARMING CONDITIONS
Ident.: DSC-22_30-90-00011958.0001001 / 23 JUN 15
Applicable to: ALL
Arming conditions of the A/THR are numerous. The following is a list of the most important ones:
‐ One FMGC operative
‐ One FAC operative
‐ Two ADIRS operative
‐ Two FADECs operative
‐ One channel of the FCU operative
‐ One LGCIU operative
‐ A/THR is not manually disabled (instinctive disconnect pb has not been pressed for more than
15 s).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_30-90 P 3/16
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
The flight crew arms A/THR:
‐ On ground
• By pushing the A/THR pb on the FCU when the engines are not running, or
• By setting the thrust levers at the FLX or TOGA detent when the engines are running.
‐ In flight
• By pushing the A/THR pb on the FCU while the thrust levers are out of the active range, or
• While A/THR is active (“A/THR ” white on the FMA ), by setting all thrust levers beyond the CL
detent or at least one lever above the MCT detent, or
• By engaging the go around mode.
When the A/THR is armed:
‐ The FCU’s A/THR pb light comes on
‐ “A/THR ” is displayed in blue on the FMA.
Note:
At takeoff, if the thrust levers are set back to idle, the A/THR disengages and cannot be
rearmed until the aircraft becomes airborne.
A/THR ACTIVATION
Applicable to: ALL
Ident.: DSC-22_30-90-A-00011959.0001001 / 14 MAY 12
GENERAL
The A/THR is active when it controls thrust or speed. The position of the thrust lever determines
the maximum thrust that the A/THR system can command (except in α-floor condition).
The A/THR being armed, is activated:
‐ When the flight crew sets both thrust levers between the CL and IDLE detents (two engines
operative), or
‐ When the flight crew sets one thrust lever between the MCT and IDLE detents (one engine
inoperative).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-22_30-90 P 4/16
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
The A/THR being disconnected, is activated when the flight crew pushes the A/THR pb on the
FCU while the thrust levers are within the active range, including IDLE position.
Note:
When the flight crew sets both thrust levers to IDLE position, the A/THR disconnects
but, if the flight crew pushes the A/THR pb of the FCU, they will simultaneously arm and
activate the autothrust. Due to the thrust levers position, IDLE thrust will be maintained.
When ALPHA FLOOR is activated, regardless of the initial status of A/THR and the position of the
thrust levers, the A/THR activates.
When A/THR is active:
‐ The A/THR pb on the FCU lights up
‐ The FMA displays A/THR mode in green in the first column and "A/THR" in white in the fifth
column.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_30-90-A-00011960.0002001 / 16 MAR 11
EFFECTS OF THRUST LEVER MOVEMENT DURING A/THR ACTIVATION
While A/THR is active:
‐ When both thrust levers are set above the CL detent (both engines operative) or one thrust
lever is set above MCT (one engine operative), the A/THR reverts from active to armed. “A/THR
” turns to blue on the FMA and the thrust levers control thrust directly.
The FMA displays "MAN THR” in white in its first column.
The thrust levers provide the flight crew with an immediate increase of thrust when both thrust
levers are pushed above the CL detent (two engines) or the active thrust lever above the MCT
detent (one engine operative).
‐ When both thrust levers are set below the CL detent (both engines operative) or one thrust lever
is set below MCT (one engine operative), a repeating warning (amber caution, single chime,
“A/THR LIMITED” ECAM message) is activated every 5 s until the flight crew moves the lever
back into the detent. “LVR CLB ” (both engines operative) or “LVR MCT ” (one engine operative)
flashes white in the first column of the FMA.
This device reminds the flight crew that the normal operating position of the thrust levers, when
A/THR active, is the CL detent (two engines) or the MCT detent (one engine operative).
‐ When one thrust lever is in the CL detent and the other one out of detent, the “LVR ASYM”
amber message comes up until both levers are set in the CL detent (only with both engines
operative).
A/THR DISCONNECTION
Applicable to: ALL
Ident.: DSC-22_30-90-B-00011961.0001001 / 17 AUG 10
GENERAL
When the A/THR is disconnected, it is neither armed nor active.
The A/THR can be disconnected in two ways:
‐ Standard disconnection:
• The flight crew pushes the instinctive disconnect pb on the thrust levers, or
• The flight crew sets both thrust levers to IDLE detent.
‐ Non-standard disconnection:
• The flight crew pushes the A/THR pb on the FCU while A/THR is active/armed, or
• The system loses one of the arming conditions.
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FCOM
← D to E →
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
CAUTION
If the flight crew pushes and holds one instinctive disconnect pb for more than
15 s, the A/THR system is disconnected for the remainder of the flight. All A/THR
functions including ALPHA FLOOR are lost, and they can be recovered only at the
next FMGC power-up (on ground).
THRUST LOCK FUNCTION
Ident.: DSC-22_30-90-00011963.0002001 / 17 AUG 10
Applicable to: ALL
The Thrust Lock function is activated when the thrust levers are in the CL detent (or the MCT detent
with one engine out), and:
‐ The flight crew pushes the A/THR pb on the FCU, or
‐ The A/THR disconnects due to a failure.
The thrust is locked at its level prior to disconnection. Moving the thrust levers out of CL or MCT
suppresses the thrust lock and gives the flight crew manual control with the thrust levers.
When the Thrust Lock function is active:
‐ “THR LK” flashes amber on the FMA
‐ ECAM “ENG THRUST LOCKED” flashes every 5 s
‐ ECAM displays “THR LEVERS......MOVE”
‐ A single chime sounds and the Master Caution light flashes every 5 s.
All warnings cease when the flight crew moves the thrust levers out of the detent.
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FCOM
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
A/THR DISCONNECTION CAUTION
Ident.: DSC-22_30-90-00011964.0002001 / 17 AUG 10
Applicable to: ALL
MASTER
CAUTION light
CONSEQUENCE
Illuminated
3 s maximum
Illuminated
ECAM MESSAGE
A/THR OFF amber message
9 s maximum
AUDIO
CLR pb on ECAM
CONTROL PANEL
Single chime
Flashing ENG THRUST
LOCKED amber caution, AUTO
FLT A/THR OFF amber caution,
blue "THR LEVERS.....MOVE"
Single chime
Extinguished
Illuminated
MASTER
CAUTION light
ACTION
A/THR DISCONNECTION
BY INSTINCTIVE
DISCONNECT pb
OR SETTING TWO
BY OTHER MEANS
LEVERS TO IDLE
(if above 50 ft RA)
‐ Extinguishes MASTER
CAUTION light
‐ Erases ECAM message
CLR pb on ECAM
CONTROL PANEL
INSTINCTIVE
DISCONNECT pb
No effect
‐ Extinguishes MASTER
CAUTION light
‐ Erases ECAM message
ECAM STATUS MESSAGE
NO
Extinguishes MASTER
CAUTION light
‐ Extinguishes MASTER
CAUTION light and CLR pb
‐ Erases ECAM message
‐ Calls status
Extinguishes MASTER
CAUTION light
YES
The standard disconnection triggers temporary ECAM message and caution light. Single chime
sounds.
The non standard disconnection triggers caution light and ECAM message removed only by a flight
crew action. Single chime sounds.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
A/THR MODES
Applicable to: ALL
Ident.: DSC-22_30-90-C-00011965.0002001 / 23 JUN 15
GENERAL
Except in takeoff and go-around situations, normal operation of the A/THR system requires the
thrust levers to be:
‐ In the CL detent for the two-engine configuration. If they are not set in the CL detent, “LVR CLB
” flashes white on the FMA.
‐ In MCT detent when in the one-engine-out configuration. If the appropriate lever is not set in the
MCT detent, “LVR MCT ” flashes white on the FMA.
The A/THR modes are selected automatically in conjunction with the AP /FD modes (except for
ALPHA FLOOR):
A/THR in THRUST mode
A/THR in SPEED/MACH mode
A/THR in RETARD mode
AP /FD pitch mode maintains the speed:
OP CLB - OP DES - CLB - EXP CLB - EXP DES - SRS - FLARE and
DES (IDLE path)
If neither AP nor FD is engaged
If AP /FD controls a vertical path:
V/S - FPA - ALT * - ALT CST* - ALT - ALT CRZ - G/S * - G/S - FINAL and DES
(geometric path)
AP /FD engaged in LAND mode during an automatic landing
Ident.: DSC-22_30-90-C-00011966.0002001 / 23 JUN 15
THRUST MODE
In THRUST mode, autothrust commands a specific thrust level in conjunction with the AP /FD
pitch mode. This thrust level is limited by thrust lever position.
FMA Display
THR MCT
THR CLB
THR LVR
THR IDLE
Note:
Meaning
Single engine thrust in climb. The live engine is at maximum continuous thrust
(thrust lever in MCT detent)
Climb thrust in two engine configuration (at least one thrust lever in the CL
detent, the other one below CL)
Undetermined thrust (neither CLB nor MCT thrust)
Minimum thrust (both engines at IDLE thrust)
When the A/THR is armed for takeoff or go-around, the FMA displays “MAN TOGA ” (or
“MAN FLX”) in white to remind the flight crew that the thrust levers have been positioned
properly.
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FCOM
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_30-90-C-00011967.0001001 / 27 JAN 12
RETARD MODE
The RETARD mode is only available during automatic landing (AP engaged in LAND mode).
At approximately 40 ft RA , the RETARD mode engages and remains engaged after touchdown.
The A/THR commands IDLE thrust during the flare, and the FMA and engine warning display
“IDLE”. If the autopilot is disengaged during the flare before touchdown, the SPEED mode
replaces the RETARD mode, and the flight crew has to manually reduce thrust.
Note:
In an automatic landing, the system generates a “RETARD” callout at 10 ft RA , which
prompts the flight crew to move the thrust levers to IDLE in order to confirm thrust
reduction. In manual landing conditions, the system generates this callout at 20 ft RA, as
a reminder.
Ident.: DSC-22_30-90-C-00011968.0002001 / 17 AUG 10
ALPHA FLOOR
ALPHA FLOOR is a protection that commands TOGA thrust, regardless of the thrust levers’
positions. This protection is available from lift-off to 100 ft RA on approach.
ALPHA FLOOR calls up the following indications:
‐ “A FLOOR” in green, surrounded by a flashing amber box on the FMA, and in amber on the
engine warning display, (as long as α-floor conditions are met)
‐ “TOGA LK” in green, surrounded by a flashing amber box on the FMA , when the aircraft leaves
the α-floor conditions. TOGA thrust is frozen.
To cancel ALPHA FLOOR or TOGA LK thrust, the flight crew must disconnect the autothrust.
Ident.: DSC-22_30-90-C-00011969.0001001 / 17 AUG 10
SPEED/MACH MODE
In SPEED/MACH mode, the A/THR adjusts the thrust in order to acquire and hold a speed or
Mach target.
The speed or Mach target may be:
‐ Selected on the FCU by the flight crew
‐ Managed by the FMGC.
When in SPEED/MACH mode, the A/THR does not allow speed excursions beyond the following
limits, regardless of the target speed or Mach number:
‐ For a selected speed target, the limits are VLS and VMAX (VMO -MMO , VFE -VLE, whichever
applies)
‐ For a managed speed target, the limits are maneuvering speed (Green Dot, S , F , whichever
applies) and maximum speed (340/0.80-VFE -VLE, whichever applies).
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FCOM
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
The changeover from SPEED to MACH mode is either automatic, performed by the FMGC, or
manual, with the flight crew pushing the SPD/MACH pb.
The FMA displays “SPEED” or “MACH”.
APPROACH AUTOTHRUST:
Below 3 200 ft RA , with at least CONF 1, the A/THR logic is modified to be more responsive to
speed variation. This is referred to as approach autothrust.
SPEED MODE IN APPROACH PHASE
Applicable to: ALL
Ident.: DSC-22_30-90-D-00011970.0001001 / 17 AUG 10
GENERAL
When the aircraft flies an approach in managed speed, the speed target displayed on the PFD in
magenta is variable during the approach.
This managed speed target is computed in the FMGS using the “ground speed mini function”.
Ident.: DSC-22_30-90-D-00011971.0002001 / 17 MAR 17
GROUND SPEED MINI FUNCTION PRINCIPLE
The purpose of the "ground speed mini function" is to take advantage of the aircraft inertia when
the wind conditions vary during the approach. It does so by providing the flight crew with an
adequate indicated speed target. When the aircraft flies this indicated speed target, the energy of
the aircraft is maintained above a minimum level ensuring standard aerodynamic margins versus
stall.
If the A/THR is active in SPEED mode, it will automatically follow the IAS target, ensuring an
efficient thrust management during the approach.
The minimum energy level is the energy level the aircraft will have at touch down if it lands at
VAPP speed with the tower reported wind as inserted in the PERF APPR page.
The minimum energy level is represented by the Ground Speed the aircraft will have at touch
down. This Ground Speed is called “GROUND SPD MINI”.
During the approach, the FMGS continuously computes the speed target using the wind
experienced by the aircraft in order to keep the ground speed at or above the “Ground Speed
Mini”.
The ground speed mini enables an efficient management of the thrust in gusts or longitudinal
shears. Thrust varies in the right sense, but in a smaller range (± 15 % N1) in gusty situations,
which explains why it is recommended in such situations.
It provides additional but rational safety margins in shears.
It allows pilots "to understand what is going on" in perturbed approaches by monitoring the target
speed magenta bugs: when target goes up = head wind gust.
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FCOM
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DSC-22_30-90 P 11/16
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
The speed target is displayed on the PFD speed scale in magenta when approach phase and
managed speed are active. It is independent of the AP /FD and/or A/THR engagements.
Wind is a key factor in the "ground speed mini function".
Ident.: DSC-22_30-90-D-00011972.0001001 / 17 AUG 10
TWR WIND
It is the MAG WIND entered in the PERF APPR page. It is the average wind as provided by
the ATIS or the tower. Gusts must not be inserted, they are included in the ground speed mini
computation.
Ident.: DSC-22_30-90-D-00011973.0001001 / 17 AUG 10
TWR HEADWIND COMPONENT
The TWR HEADWIND COMPONENT is the component of the MAG WIND projected on the
runway axis (landing runway entered in the flight plan). It is used to compute VAPP and GS mini.
Ident.: DSC-22_30-90-D-00011974.0001001 / 17 AUG 10
CURRENT HEADWIND COMPONENT
The actual wind measured by ADIRS is projected on the aircraft axis to define the CURRENT
HEADWIND COMPONENT (instantaneous headwind).
The CURRENT HEADWIND COMPONENT is used to compute the variable speed target during
final (IAS target).
Ident.: DSC-22_30-90-D-00011975.0002001 / 17 AUG 10
VAPP COMPUTATION
VAPP , automatically displayed on the MCDU PERF APPR page, is computed as follows:
‐ VAPP = VLS+1/3 of the TWR HEADWIND COMPONENT, or
‐ VAPP = VLS +5 kt, whichever is the highest.
"1/3 of the TWR HEADWIND COMPONENT" has two limits:
‐ 0 kt as the minimum value (no wind or tailwind)
‐ +15 kt as the maximum value.
The flight crew can manually modify the VAPP and TWR wind values on the PERF APPR page.
Ident.: DSC-22_30-90-D-00011976.0002001 / 01 OCT 12
SPEED TARGET COMPUTATION
The FMGS continuously computes a speed target (IAS target) that is the MCDU VAPP value plus
an additional variable gust.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
DSC-22_30-90 P 12/16
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
The gust is the instantaneous difference between the CURRENT HEADWIND COMPONENT
and the TWR HEADWIND COMPONENT. It is always positive (or equal to zero for no wind or
tailwind).
The IAS target is displayed on the PFD as a magenta triangle moving with the gust variation.
The IAS targets have 2 limits:
‐ VAPP, as the minimum value
‐ VFE -5 kt in CONF FULL, or VFE of the next configuration in CONF 1, 2 or 3 as the maximum
value.
Ident.: DSC-22_30-90-D-00011977.0001001 / 17 MAR 17
GROUND SPEED MINI (GS MINI) COMPUTATION
Ground speed mini concept has been defined to prevent the aircraft energy from dropping below a
minimum level during final approach. The GS mini value is not displayed to the flight crew.
This minimum energy level is the energy the aircraft will have at landing with the expected tower
wind; it is materialized by the ground speed of the aircraft at that time which is called GS mini:
GS mini = VAPP - Tower head wind component
In order to achieve that goal, the aircraft ground speed should never drop below GS mini in the
approach, while the winds are changing. Thus the aircraft IAS must vary while flying down, in
order to cope with the gusts or wind changes. In order to make this possible for the pilot or for the
A/THR , the FMGS continuously computes an IAS target speed, which ensures that the aircraft
ground speed is at least equal to GS mini; the FMGS uses the instantaneous wind component
experienced by the aircraft:
IAS Target Speed = GS mini + Current headwind component
This target speed is limited by VAPP in case of tailwind or if instantaneous wind is lower than the
tower wind.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
DSC-22_30-90 P 13/16
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
DSC-22_30-90 P 14/16
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I
DSC-22_30-90 P 15/16
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
AUTOTHRUST
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_30-90 P 16/16
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT MODE ANNUNCIATOR (FMA)
FLIGHT CREW
OPERATING MANUAL
FLIGHT MODE ANNUNCIATOR (FMA)
Applicable to: ALL
Ident.: DSC-22_30-100-A-00012356.0012001 / 19 DEC 12
GENERAL
The Flight Mode Annunciator (FMA ) which is just above the PFD s, shows the status of the
A/THR , the AP /FD vertical and lateral modes, the approach capabilities, and the AP /FD -A/THR
engagement status.
A white box is displayed for 10 s around each new annunciation. The white box display time may
be increased to 15 s in some mode reversion cases associated with an aural triple click.
Ident.: DSC-22_30-100-A-00012357.0002001 / 17 AUG 10
THE THREE LEFT COLUMNS
The first line shows the engaged modes in green.
The second line shows the armed modes in blue or magenta.
Magenta indicates that the modes are armed or engaged because of a constraint.
The third line displays special messages:
‐ Messages related to flight controls have first priority:
• “MAN PITCH TRIM ONLY” in red, flashing for 9 s, then steady
• “USE MAN PITCH TRIM” in amber, pulsing for 9 s, then steady.
‐ Messages related to the FMGS have second priority.
Ident.: DSC-22_30-100-A-00012358.0014001 / 16 MAR 11
THE FOURTH COLUMN
Displays approach capabilities in white.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-22_30-100 P 1/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT MODE ANNUNCIATOR (FMA)
FLIGHT CREW
OPERATING MANUAL
Displays minimum in blue.
Note:
The BARO or RADIO value on the FMA is not rounded off: The exact value appears on
the FMA , and is the same value as the one inserted in the MCDU PERF APPR page.
Ident.: DSC-22_30-100-A-00012359.0001001 / 17 AUG 10
THE FIFTH COLUMN
Displays the engagement status of AP , FD , and A/THR in white.
Displays a box around FD for 10 s in case of automatic FMGC switching.
Displays A/THR in blue when autothrust is armed but not active.
Note:
The FMGS synchronizes A/THR mode, AP /FD modes and approach capability to
provide identical information on both PFDs.
AUTOTHRUST ANNUNCIATIONS (FMA COLUMN 1)
Applicable to: ALL
Ident.: DSC-22_30-100-B-00012360.0002001 / 23 JUN 15
FIRST LINE
MAN
TOGA
DISPLAY
MAN
FLX XX
MAN
MCT
MAN
THR
THR MCT
COLOR
White
White box
White
White box
Blue numbers
White
White box
White
Amber box
Green
THR CLB
Green
THR IDLE
THR LVR
Green
Green
SPEED or MACH
A. FLOOR
TOGA LK
Green
Green
Amber box
Green
Amber box
MEANING
A/THR is armed, at least one thrust lever is in TOGA detent.
A/THR is armed, at least one thrust lever is in MCT /FLX detent with FLXTO
temp set at XX°. The other thrust lever is at or below the MCT/FLX detent.
A/THR is armed, at least one thrust lever is in the MCT/FLX detent, the
other is at, or below this detent.
A/THR is armed, and the most advanced thrust lever is above CL detent
(two engines operative), or one above MCT/FLX (engine-out) and not in a
detent.
A/THR is active in thrust mode and the most advanced thrust lever is in the
MCT/FLX detent (engine-out).
A/THR is active in thrust mode and the most advanced thrust lever is in the
CL detent.
A/THR is active in thrust mode and commands idle thrust.
A/THR is active in thrust mode with both thrust levers below CL detent, or
the live thrust lever (one engine) below MCT.
A/THR is active in SPEED or MACH mode.
A/THR is active and commands TOGA thrust while α FLOOR conditions are
met.
A/THR is active and TOGA thrust is locked (α FLOOR conditions are no
longer met).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-22_30-100 P 2/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT MODE ANNUNCIATOR (FMA)
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_30-100-B-00012361.0002001 / 17 AUG 10
SECOND LINE
Not used with this standard.
Ident.: DSC-22_30-100-B-00012362.0002001 / 16 NOV 15
THIRD LINE
DISPLAY
LVR CLB
(flashing)
LVR MCT
(flashing)
LVR ASYM
White
Amber
THR LK
(flashing)
Note:
COLOR
White
Amber
MEANING
Request to set the thrust levers in CL detent in the case not in position
while the aircraft is above the altitude of thrust reduction with both engines
running.
Request to set the live thrust lever in MCT/FLX detent in the case not in
position after an engine failure (with speed above green dot).
(Two engines only). One thrust lever in CL or MCT/FLX detent and the
other one is not in this detent.
After A/THR disconnection (action of the flight crew on FCU or failure)
resulting in thrust being frozen. Both thrust levers being in CL detent or one
in MCT/FLX (engine out) detent.
The amber caution light flashes and a single chime sounds every 5 s, as long as the
flight crew takes no appropriate action in the following cases:
‐ THR LK
‐ LVR CLB (if the thrust levers are below the CLB detent)
‐ LVR MCT (if the thrust levers are below the FLX/MCT detent).
AP/FD VERTICAL MODES (FMA COLUMN 2)
Applicable to: ALL
Ident.: DSC-22_30-100-C-00012363.0006001 / 23 JUN 15
FIRST LINE
SRS
CLB
DISPLAY
COLOR
Green
Green
OP CLB
Green
EXP CLB
Green
ALT*
or
ALT CST*
Green
MEANING
Takeoff or go-around mode is engaged.
Climb mode is engaged. The FMGS target altitude is higher than the
actual altitude. ALT CSTR are taken into account.
Open Climb mode is engaged. The FCU selected altitude is higher than
the actual altitude. ALT CSTR are disregarded.
Expedite Climb is engaged. The selected altitude is higher than the actual
altitude. Green dot speed is maintained, ALT CSTR are disregarded.
ALT CAPTURE is engaged:
‐ ALT * green in case of FCU selected altitude capture
‐ ALT CST* green in case of ALT CSTR capture (vertical profile).
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_30-100 P 3/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT MODE ANNUNCIATOR (FMA)
FLIGHT CREW
OPERATING MANUAL
DISPLAY
ALT
or
ALT CST
COLOR
Green
ALT CRZ
DES
Green
Green
OP DES
Green
EXP DES
Green
G/S*
G/S
V/S±XXXX
Green
Green
Green +
blue
numbers
FPA±XX
Green +
blue
numbers
Continued from the previous page
MEANING
ALTITUDE HOLD mode is engaged:
‐ ALT is green when the FCU selected altitude is held
‐ ALT CST is green when an ALT CSTR is held (vertical profile).
ALT mode is engaged and CRZ FL is held.
Descent mode is engaged. The FMGS target altitude is lower than the
actual altitude. ALT CSTR are taken into account.
Open Descent mode is engaged. The FCU selected altitude is lower than
the actual altitude. ALT CSTR are disregarded.
Expedite Descent is engaged, the selected altitude is lower than the actual
altitude. M 0.80 or 340 kt is maintained. ALT CSTR are disregarded.
Glide Slope capture mode is engaged.
Glide Slope mode is engaged.
Vertical speed mode is engaged to acquire and hold the V/S selected on
the FCU . ALT CSTR are disregarded.
If the aircraft reaches VLS or VMAX and cannot maintain the target, the
indication is boxed amber and flashes, and the target pulses.
Flight Path Angle mode is engaged to acquire and hold the FPA selected
on the FCU . ALT CSTR are disregarded.
If the aircraft reaches VLS or VMAX and cannot maintain the target, the
indication is boxed amber and flashes, and the target pulses.
Ident.: DSC-22_30-100-C-00012364.0002001 / 23 JUN 15
SECOND LINE
CLB
ALT
DISPLAY
DES
G/S
FINAL
ALT G/S
ALT G/S
ALT FINAL
ALT FINAL
DES G/S
DES FINAL
COLOR
Blue
Blue
or
Magenta
Blue
Blue
Blue
Blue/Blue
Magenta/ Blue
Blue/Blue
Magenta/ Blue
Blue/Blue
Blue/Blue
Climb mode is armed.
MEANING
Altitude mode is armed:
‐ Blue when the target altitude is the FCU selected altitude
‐ Magenta when the target altitude is an ALT CSTR.
Descent mode is armed before the descent phase.
Glide Slope mode is armed.
Final descent mode is armed.
ALT and G/S modes are armed.
ALT CST and G/S modes are armed.
ALT and FINAL modes are armed.
ALT CST and FINAL modes are armed.
DES and G/S modes are armed.
DES and FINAL modes are armed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-22_30-100 P 4/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT MODE ANNUNCIATOR (FMA)
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_30-100-C-00012365.0001001 / 17 AUG 10
THIRD LINE
DISPLAY
SPEED SEL:XXX
MACH SEL:.XX
Note:
COLOR
Blue
Blue
MEANING
Indicates a preset speed associated with the cruise or climb phase.
Indicates a preset Mach associated with the cruise or climb phase.
These two messages use both the first and second columns (third line).
AP/FD LATERAL MODES (FMA COLUMN 3)
Applicable to: ALL
Ident.: DSC-22_30-100-D-00012366.0002001 / 16 MAR 11
FIRST LINE
DISPLAY
RWY
RWY TRK
HDG
TRK
NAV
LOC*
LOC
APP NAV
GA TRK
COLOR
Green
Green
Green
Green
Green
Green
Green
Green
Green
MEANING
RWY mode is engaged.
RWY mode is engaged once airborne at or above 30 ft RA.
HEADING mode is engaged.
TRACK mode is engaged.
NAV mode is engaged to guide the aircraft along the FM lateral F-PLN.
LOC capture mode is engaged.
LOC track mode is engaged.
NAV mode is engaged during a non-ILS approach.
GO-AROUND TRACK mode is engaged.
Ident.: DSC-22_30-100-D-00012367.0001001 / 17 AUG 10
SECOND LINE
DISPLAY
NAV
LOC
APP NAV
COLOR
Blue
Blue
Blue
MEANING
NAV mode is armed.
LOC mode is armed.
NAV mode is armed for a non-ILS approach.
AP/FD COMMON MODES (FMA COLUMNS 2 AND 3)
Ident.: DSC-22_30-100-00012368.0002001 / 17 AUG 10
Applicable to: ALL
LAND
FLARE
DISPLAY
COLOR
Green
Green
MEANING
Land mode is engaged below 400 ft RA.
Flare mode is engaged.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to E →
Continued on the following page
DSC-22_30-100 P 5/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT MODE ANNUNCIATOR (FMA)
FLIGHT CREW
OPERATING MANUAL
DISPLAY
ROLL OUT
FINAL APP
COLOR
Green
Green
Continued from the previous page
MEANING
Roll out mode is engaged.
APP NAV and Final modes are engaged during a non-ILS approach.
APPROACH CAPABILITIES (FMA COLUMN 4)
Applicable to: ALL
Ident.: DSC-22_30-100-E-00012369.0002001 / 17 AUG 10
FIRST LINE
CAT 1
CAT 2
CAT 3
DISPLAY
COLOR
White
White
White
CAT 1 capability available.
CAT 2 capability available.
CAT 3 capability available.
MEANING
Ident.: DSC-22_30-100-E-00012370.0002001 / 17 AUG 10
SECOND LINE
SINGLE
DUAL
DISPLAY
COLOR
White
White
MEANING
CAT 3 capability available, with FAIL PASSIVE condition.
CAT 3 capability available, with FAIL OPERATIONAL condition.
Ident.: DSC-22_30-100-E-00012371.0009001 / 16 MAR 11
THIRD LINE
DISPLAY
BARO
XXXX
RADIO XXX/NO DH
COLOR
White
Blue
White
Blue
MEANING
Minimum Descent Altitude or Minimum Descent Height as inserted by the
flight crew on the MCDU PERF APPR page.
Decision Height as inserted by the flight crew on the MCDU PERF APPR
page.
NO DH : when NO inserted on the MCDU PERF APPR page.
AP/FD - A/THR ENGAGEMENT STATUS (FMA COLUMN 5)
Applicable to: ALL
Ident.: DSC-22_30-100-F-00012372.0001001 / 17 AUG 10
FIRST LINE
AP1 + 2
AP1
AP2
DISPLAY
COLOR
White
White
White
Autopilot 1 and 2 are engaged.
Autopilot 1 is engaged.
Autopilot 2 is engaged.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to G →
MEANING
DSC-22_30-100 P 6/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT MODE ANNUNCIATOR (FMA)
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-22_30-100-F-00012373.0002001 / 17 AUG 10
SECOND LINE
X FD Y
DISPLAY
COLOR
White
MEANING
X and Y give the FD engagement status on PFD 1 and PFD2.
X and Y can be 1, 2, or –:
‐ –: No FD is engaged on the corresponding PFD
‐ 1: FD 1 is engaged on the corresponding PFD
‐ 2: FD 2 is engaged on the corresponding PFD.
The normal status (FD 1 and 2 engaged) is 1 FD 2.
Ident.: DSC-22_30-100-F-00012374.0001001 / 17 AUG 10
THIRD LINE
A/THR
A/THR
DISPLAY
COLOR
White
Blue
A/THR is active.
A/THR is armed.
MEANING
SPECIAL MESSAGES (FMA COLUMNS 2 AND 3)
Ident.: DSC-22_30-100-00012539.0017001 / 05 NOV 15
Applicable to: ALL
The third line displays three types of messages:
‐ It gives first priority to Flight Control messages
‐ It gives second priority to vertical Flight Management messages
‐ It gives last priority to EFIS reconfiguration messages.
DISPLAY
MAN PITCH TRIM ONLY
USE MAN PITCH TRIM
CHECK APPR
SELECTION
COLOR
Red
Amber
White
SET MANAGED SPEED
or CHECK SPEED
MODE
(Also displayed on PFD)
White
MEANING
Displayed in case of loss of L+R elevators.
F/CTL are in direct law.
The aircraft is in cruise at less than 100 NM from the Top of Descent or in
descent or in approach and:
‐ A non-ILS /non-GLS approach has been selected
‐ An ILS frequency/GLS channel is tuned on the MCDU RAD NAV
page.
The SPEED target is selected but a preselected SPEED does not exist for
the next flight phase.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← G to H →
Continued on the following page
DSC-22_30-100 P 7/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT MODE ANNUNCIATOR (FMA)
FLIGHT CREW
OPERATING MANUAL
DISPLAY
SET GREEN DOT
SPEED
COLOR
White
SET HOLD SPEED
White
DECELERATE or T/D
REACHED
(Also displayed on PFD)
MORE DRAG
White
White
Continued from the previous page
MEANING
The aircraft is in Engine Out mode and the SPEED target is selected. This
message is displayed if the FCU selected speed is:
≤ Green Dot -10 kt, or
≥ Green Dot +10 kt, except in ALT * and ALT mode.
The aircraft is in selected SPEED control, a Holding pattern is inserted
in the F-PLN and the aircraft is 30 s before the deceleration point to the
precomputed HOLD SPEED.
This message is displayed if the thrust is not reduced when passing the
top of descent and the aircraft is above the descent profile.
DES mode is engaged, idle is selected, and either:
‐ The aircraft is above the vertical profile and the predicted intercept point
of the theoretical profile is at less than 2 NM from the next ALT CSTR,
or
‐ In auto speed control and the aircraft enters a speedbrake decelerating
segment.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H
DSC-22_30-100 P 8/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
TEMPORARY ABNORMAL BEHAVIORS
FLIGHT CREW
OPERATING MANUAL
CAT 3 DUAL INOPERATIVE
Ident.: DSC-22_30-110-00012674.0001001 / 28 JUN 17
Applicable to: ALL
"CAT 3 DUAL" INOP SYS is triggered in particular if one ADR or IR is rejected by FAC or FMGC.
If “CAT 3 DUAL” is displayed in INOP SYS without any other failure being detected:
CHANGE the AP in command. It may allow the CAT 3 DUAL function to be recovered.
If unsuccessful:
SET FAC 1 pb to OFF, and back to ON
WAIT for FAC 1 fault ECAM warning to disappear, and
APPLY the same sequence for FAC 2.
Note:
1. Do not reset the FACs with the C/Bs.
2. If the CAT 3 DUAL INOP SYS is associated to another ECAM message (in particular
ADR FAULT or IR FAULT...), it means that the root cause is not an ADR or IR rejection
by FAC or FMGC. And consequently the AP switch or FAC reset will not clear the CAT 3
DUAL inop.
LEFT TURN NOT EXPECTED WHILE IN HDG OR TRK MODE
Ident.: DSC-22_30-110-00015029.0001001 / 08 AUG 13
Applicable to: ALL
The AP /FD may erroneously order a left turn if the following conditions are fulfilled:
‐ The aircraft is in a right turn in HDG or TRK mode
‐ Within 180 ms, the difference between the target selected on the FCU and the current aircraft
heading/track, initially above 85 °:
1. First goes below 85 °
2. Then goes above 95 °.
The flight crew may encounter this misbehavior in two different situations:
‐ The flight crew requests a right turn, then rapidly reduces and increases again the target selected
on the FCU
‐ The flight crew increases the target selected on the FCU according to the above conditions, while
the aircraft is already in a right turn.
The misbehavior may affect either one AP /FD or both AP /FD.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_30-110 P 1/2
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT GUIDANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TEMPORARY ABNORMAL BEHAVIORS
OPERATIONAL RECOMMENDATIONS:
The flight crew must immediately take appropriate actions:
‐ The flight crew must disconnect the AP and the FD, and manually turn.
‐ When established on the intended trajectory, the flight crew can reengage the FD first, and then
the AP.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-22_30-110 P 2/2
05 SEP 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
Intentionally left blank
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-22_40-10 General
GENERAL................................................................................................................................................................ A
DSC-22_40-20 Yaw Functions
YAW DAMPING....................................................................................................................................................... A
RUDDER TRIM........................................................................................................................................................B
RUDDER TRAVEL LIMITATION.............................................................................................................................C
DSC-22_40-30 Flight Envelope Function
GENERAL................................................................................................................................................................ A
PFD Speed Scale Management..............................................................................................................................B
Alpha-Floor Protection............................................................................................................................................. C
Low - Energy Aural Alert.........................................................................................................................................D
DSC-22_40-40 Windshear Detection Function
Windshear Detection Function................................................................................................................................ A
WINDSHEAR DETECTION PRINCIPLES...............................................................................................................B
GUIDANCE.............................................................................................................................................................. C
DSC-22_40-50 Controls and Indicators
FAC ENGAGEMENT............................................................................................................................................... A
RUDDER TRIM OPERATION................................................................................................................................. B
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_40-PLP-TOC P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-22_40-PLP-TOC P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_40-10-00000840.0001001 / 24 FEB 15
Applicable to: ALL
The aircraft has two flight augmentation computers (FACs) that perform four main functions:
• Yaw function
‐ Yaw damping and turn coordination
‐ Rudder trim
‐ Rudder travel limitation
• Flight envelope function
‐ PFD speed scale management
▪ Minimum/maximum speed computation
▪ Maneuvering speed computation
‐ Alpha-floor protection
• Low-Energy Aural Alert function
• Windshear detection function
In performing these functions the FAC uses independent channels :
Yaw damper
Rudder trim
Rudder travel limit
Flight envelope
Each FAC interfaces with the elevator aileron computers (ELAC s) when the AP s are disengaged, or
with the FMGS when at least one AP is engaged.
Both FACs engage automatically at power-up.
The pilot can disengage or reset each FAC (in case of failure) by means of a pushbutton on the flight
control overhead panel.
When a FAC is disengaged (FAC pushbutton set off) but still valid, the flight envelope function of the
FAC remains active.
If both FAC s are valid, FAC 1 controls the yaw damper, turn coordination, rudder trim, and rudder
travel limit, and FAC2 is in standby.
FAC 1 keeps the aircraft within the flight envelope through FD 1 ; FAC 2 performs this function
through FD2.
If a failure is detected on any channel of FAC 1, FAC2 takes over the corresponding channel.
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A
DSC-22_40-10 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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FCOM
DSC-22_40-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
YAW FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
YAW DAMPING
Ident.: DSC-22_40-20-00000851.0001001 / 18 MAR 11
Applicable to: ALL
Yaw damping stabilizes the aircraft in yaw and coordinates its turns.
In automatic flight (AP engaged) during takeoff and go around, it assists rudder application after an
engine failure (short-term yaw compensation).
Note:
When the AP is engaged, the FMGS sends orders to the FAC to give :
‐ Yaw damping during approach
‐ Yaw control for runway alignment in ROLL OUT mode
RUDDER TRIM
Ident.: DSC-22_40-20-00000855.0001001 / 09 DEC 09
Applicable to: ALL
The rudder trim function :
‐ Executes trim orders, entered by the pilot by using the manual trim knob.
‐ When AP is engaged
▪ executes trim orders from the FMGS.
▪ Assists the system in recovering from engine failure (long-term yaw compensation) in all flight
guidance modes.
▪ If the pilot pushes the rudder more than 10 ° out of trim, it disengages the AP.
Note:
When the AP is engaged, the rudder trim knob is inoperative : the master FMGC
sends rudder trim orders to the FAC.
RUDDER TRAVEL LIMITATION
Ident.: DSC-22_40-20-00000857.0001001 / 01 OCT 12
Applicable to: ALL
This function limits rudder deflection is based on speed in order to avoid high structural loads. It is
governed by the following law :
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C →
DSC-22_40-20 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
YAW FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
If both FACs lose the rudder travel limitation function, the value of the rudder deflection limit is locked
at the time of the second failure.
When the slats are extended, the FACs automatically set the rudder deflection limit at the low-speed
setting (maximum authorized deflection).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
FLIGHT ENVELOPE FUNCTION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_40-30-00000859.0001001 / 09 DEC 09
Applicable to: ALL
As long as one Flight Augmentation Computer (FAC ) is valid, it governs the flight envelope function,
the rudder position display, and the rudder trim indication regardless of what the flight crew does with
the FAC pushbutton.
PFD SPEED SCALE MANAGEMENT
Ident.: DSC-22_40-30-00000860.0001001 / 21 MAR 17
Applicable to: ALL
The FAC controls the speed scale on the PFD (Refer to DSC-31-40 Attitude Data).
When both FAC s are operative, FAC 1 supplies data to PFD 1 and FAC 2 supplies it to PFD2.
The FAC computes:
‐ The minimum and maximum speeds:
• VSW (stall warning)
• VLS
• VFE and VFE for the next configuration
• VLE
• VMO /MMO
‐ The maneuvering speeds:
• Green Dot Speed
• S speed
• F speed
The FAC also computes the speed trend and displays it as an arrow on the PFD speed scale.
The PFD displays these various speeds as appropriate, and they also go to the FMGC to be used as
limits for various guidance modes.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-22_40-30 P 1/4
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
FLIGHT ENVELOPE FUNCTION
FLIGHT CREW
OPERATING MANUAL
Note:
The principle of the speed computation is as follows:
‐ First, the FAC computes VS1G (stall speed). From VS1G it computes the Gross Weight
(GW) which is also sent to the Elevator Aileron computers:
• When the aircraft is below 14 500 ft and 250 kt, it computes this from current angle of
attack, speed/Mach, altitude, thrust, and CG.
• When the aircraft is above 14 500 ft or 250 kt, it computes this out of the GW , which it
has memorized and updated with a fuel consumption model set in the FAC.
‐ Finally the FAC computes the various minimum and maneuvering speeds, Vα prot and
Vsw.
‐ The accuracies of the various minimum and maximum speeds are functions of the
accuracy with which the FAC computes aircraft gross weight. Normal accuracy for VLS in
CONFIG FULL is about ± 3 kt.
ALPHA-FLOOR PROTECTION
Ident.: DSC-22_40-30-00006198.0001001 / 17 MAR 17
Applicable to: ALL
Alpha-floor protection automatically sets the thrust at TOGA thrust, when the aircraft reaches a very
high angle of attack.
The Flight Augmentation Computer (FAC) generates the signal that triggers the alpha-floor mode.
This, in turn, sets TOGA thrust on the engines, regardless of the thrust lever positions (Refer to
DSC-22_30-90 A/THR Modes - General).
The FAC sends this signal when:
‐ The angle of attack is above a predetermined threshold, that is a function of the configuration.
‐ In CONF 3 and CONF FULL, this threshold decreases as a function of the aircraft deceleration
rate (down to – 3 °).
Alpha-floor is available from lift-off until the aircraft reaches 100 ft RA in approach.
Note:
The αfloor is activated through the A/THR system, when:
‐ α is greater than αfloor (9.5 ° in configuration 0; 15 ° in configuration 1, 2; 14 ° in
configuration 3; 13 ° in configuration FULL), or
‐ Sidestick deflection is greater than 14 ° nose up, with either the pitch attitude or the
angle-of-attack protection active.
The αfloor function is available from lift-off to 100 ft RA before landing.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-22_40-30 P 2/4
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
FLIGHT ENVELOPE FUNCTION
FLIGHT CREW
OPERATING MANUAL
Note:
‐ Alpha-floor is lost, when one of the following combinations of failures occurs:
SFCC 1 and FAC2, or
SFCC 2 and FAC1, or
Both FCU channels, or
1 EIU, or
Both FMGCs.
‐ Alpha-floor is lost under alternate or direct flight control law.
‐ Alpha-floor is lost in engine-out, when slats/flaps are extended.
LOW - ENERGY AURAL ALERT
Ident.: DSC-22_40-30-00006197.0001001 / 24 FEB 15
Applicable to: ALL
An aural low-energy “SPEED SPEED SPEED” alert, repeated every 5 s, warns the pilot that the
aircraft’s energy level is going below a threshold under which he has to increase thrust, in order to
regain a positive flight path angle through pitch control.
It is available in Configuration 2, 3, and FULL. The FAC computes the energy level with the following
inputs:
‐ Aircraft configuration
‐ Horizontal deceleration rate
‐ Flight path angle.
The aural alert is inhibited when:
‐ TOGA is selected, or
‐ Below 100 ft RA, or
‐ Above 2 000 ft RA, or
‐ Alpha-floor, or the ground proximity warning system alert is triggered, or
‐ In alternate or direct law, or
‐ If both radio altimeters fail.
During deceleration, the low-energy aural alert is triggered before alpha floor (unless alpha floor
is triggered by stick deflection). The amount of time between the two alerts depends on the
deceleration rate.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
DSC-22_40-30 P 3/4
22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
FLIGHT ENVELOPE FUNCTION
FLIGHT CREW
OPERATING MANUAL
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22 MAR 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
WINDSHEAR DETECTION FUNCTION
FLIGHT CREW
OPERATING MANUAL
WINDSHEAR DETECTION FUNCTION
Ident.: DSC-22_40-40-00006194.0001001 / 07 JUL 11
Applicable to: ALL
The windshear detection function is provided by the Flight Augmentation Computer (FAC) in takeoff
and approach phase in the following conditions:
‐ At takeoff, 3 s after liftoff, up to 1 300 ft RA
‐ At landing, from 1 300 ft RA to 50 ft RA
‐ With at least CONF 1 selected.
The warning consists of:
‐ A visual “WINDSHEAR” red message displayed on both PFDs for a minimum of 15 s.
‐ An aural synthetic voice announcing “WINDSHEAR” three times.
WINDSHEAR DETECTION PRINCIPLES
Ident.: DSC-22_40-40-00006195.0001001 / 23 JUN 15
Applicable to: ALL
The FACs generate the windshear warning whenever the predicted energy level for the aircraft falls
below a predetermined threshold.
In computing this energy level prediction, the FAC s use data from different sources. From ADIRS
comes data such as vertical speed, air and ground speeds and slope ; from other sources come such
derived parameters as total slope, longitudinal wind gradient, and vertical wind.
The FACs express this energy level as an angle of attack and compare it with an angle-of-attack
threshold above which windshear conditions are most likely and pilot action is required.
GUIDANCE
Ident.: DSC-22_40-40-00006196.0001001 / 09 DEC 09
Applicable to: ALL
In windshear conditions, flight guidance acts on specially adapted FD pitch orders received from the
speed reference system (SRS). The pilot must set go around thrust immediately (which also triggers
the FD SRS mode), and follow the pitch order to execute the optimum escape maneuver.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C
DSC-22_40-40 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
WINDSHEAR DETECTION FUNCTION
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
FAC ENGAGEMENT
Ident.: DSC-22_40-50-00000861.0001001 / 09 DEC 09
Applicable to: ALL
Refer to DSC-27-10-20 Yaw Control - General
RUDDER TRIM OPERATION
Ident.: DSC-22_40-50-00000862.0001001 / 09 DEC 09
Applicable to: ALL
Refer to DSC-27-10-20 Yaw Control - General
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FCOM
A to B
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
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AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
General.....................................................................................................................................................................A
Flight Plan Initialization Function.............................................................................................................................B
Takeoff Data Function............................................................................................................................................. C
Wind Data Function.................................................................................................................................................D
Flight Reports...........................................................................................................................................................E
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AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-22_45-00000864.0001001 / 18 MAR 11
Applicable to: ALL
The FMS AOC function gives an interface between a ground station and one onboard FMGC ,
allowing data transmission between these two computers via the ACARS Management Unit or the
ATSU.
Two different sets of message can be exchanged:
UPLINK messages from the ground station. They consist in reception of data requested or directly
sent to the crew.
DOWNLINK messages from the FMGC (master). They consist in reports or requests sent to the
ground station.
The FMGS /ACARS or FMGS /ATSU interface enables the following AOC capabilities.
‐ F-PLN initialization (flight plan and performance data)
‐ Takeoff data
‐ Wind data
‐ Flight reports
‐ Broadcast data
Crews can send message using ACARS FUNCTION pages or relevant MCDU pages.
Only one FMGC talks to the ground station. This FMGC is called FMGC “master”.
GENERAL SCRATCHPAD MESSAGES
NOT XMITTED TO ACARS:
NO ANSWER TO
REQUEST
:
A crew request or report was sent to the ground but the
communication was not established or not acknowledged.
A crew request was previously sent to the ground and no answer
(uplink message) was received within 4 min.
FLIGHT PLAN INITIALIZATION FUNCTION
Ident.: DSC-22_45-00000865.0001001 / 18 MAR 11
Applicable to: ALL
This function enables lateral and vertical flight plan data as well as initialization data to be exchanged
between the aircraft and a ground station. The aircraft may send flight plan requests for active and
secondary flight plan. (downlink messages). The ground station may send flight plan and initialization
data (uplink messages) either under aircraft request or automatically without any request.
Each uplink message concerns either the active or secondary flight plan but never both flight plans at
the same time. The data sent to the aircraft are checked for flight plan consistency.
A MCDU message comes up when an uplink message is received. “ACT (or SEC ) RTE UPLINK”.
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A to B →
DSC-22_45 P 1/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
If an error prevents the decoding process of the message, “INVALID RTE UPLINK” is displayed on
MCDUs.
An uplink message can be routed to the active flight plan if no engine is started and no active flight
plan exists. Otherwise, it is routed to the secondary. The crew will insert it into the secondary flight
plan or will reject it using the CLR key.
Note:
The flight plan may also be initialized using the ACARS FUNCTION page selected from
DATA INDEX page.
PERFORMANCE DATA
On ground and before engine start, the ground station may also send performance data to the
aircraft.
Performance data are always associated with the uplink flight plan. It is either automatically
inserted with the active flight plan data, or stored in the secondary with the corresponding flight
plan.
This message contains part or all of the following data:
ZFW, ZFWCG, taxi fuel, block fuel, cruise flight level, tropopause altitude, cruise temperature,
transition altitude, cost index, performance factor.
Note:
After engine start an uplink performance data message is rejected automatically without
any scratchpad message.
SCRATCHPAD MESSAGES RELATED TO FLIGHT PLAN AND PERFORMANCE
INVALID RTE UPLINK
An error is detected, the uplink message is rejected.
ACT or SEC RTE UPLINK A F-PLN is stored in the active or secondary flight plan.
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←B→
DSC-22_45 P 2/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLT NUMBER UPLINK
FLT NBR has been initialized within a F-PLN message without
previous request.
CHECK FLT NUMBER
The uplinked FLT NBR differs from the one specified in the request.
CHECK CO RTE
The uplinked CO RTE ident differs from the one specified in the
request.
INVALID FLT NBR UPLINK The uplink contains a valid F-PLN but the FLT NBR is invalid.
PERF DATA UPLINK
Performance data is received
INVALID PERF UPLINK
Performance uplink message has been rejected
RTE DATALINK IN PROG A flight plan modification is performed after a F-PLN INIT request has
been sent; this message is displayed until the uplink is received.
UPLINK INSERT IN PROG This message is displayed during insertion of a Flight Plan.
TAKEOFF DATA FUNCTION
Ident.: DSC-22_45-00000866.0001001 / 18 MAR 11
Applicable to: ALL
The takeoff data function is available for the active flight plan only. It is used to request to the ground
station, information data for up to 2 runways and to receive this data for up to 4 runways.
The crew sends a request indicating the departure airport, runway idents, CG , GW and weather
conditions (such as BARO setting wind, temperature...). In response he receives the takeoff speeds
for up to 4 runways but only one set of data may be inserted in the active flight plan for the selected
active runway.
Takeoff speeds are computed for max and flex takeoff.
The takeoff data function has required the modification of the standard PERF TAKEOFF page and
the addition of 2 news pages:
• UPLINK TO DAT REQ page that enables the crew to specify a request to the ground.
• UPLINK XXX TO DATA page (XXX for MAX or FLEX)
These 2 pages are accessed from the PERF TAKEOFF page in PREFLIGHT and DONE phase only.
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FCOM
← B to C →
DSC-22_45 P 3/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SCRATCHPAD MESSAGES RELATED TO TAKEOFF DATA
TAKEOFF DATA UPLINK :
INVALID TAKEOFF
:
UPLINK
Takeoff data uplink message is received
The UPLINK message is rejected
WIND DATA FUNCTION
Ident.: DSC-22_45-00000867.0001001 / 18 MAR 11
Applicable to: ALL
This function enables the crew to request and to receive forecasted winds associated to the active or
secondary flight plan.
The uplink message (ground station to aircraft) may be received upon crew request or automatically
without crew request.
The request is initiated from WIND pages or from ACARS FUNCTION page (Refer to DSC-22_20-70
Wind Data - Request for Wind Data).
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FCOM
← C to D →
DSC-22_45 P 4/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
The uplink wind data when received are directly displayed on the wind pages but not inserted in the
flight plan, one set for each flight phase: CLIMB, CRUISE, DESCENT. The alternate wind at alternate
cruise flight level is displayed on DESCENT page.
‐ Winds are associated to altitude for climb an descent phases
‐ Winds are associated to waypoint for cruise phase and step level. One wind per waypoint.
• On ground and without entered winds, an uplink message is directly inserted in the flight plan.
• In flight, winds are temporary stored until the crew inserts it phase per phase.
Phase of flight is indicated in the WIND title page.
• Clearing the INSERT UPLINK* prompt using the CLR key deletes the uplink wind data for the
selected phase.
When uplink winds are deleted, the wind page reverts to the previous status.
The flight plan B page is modified of the uplink wind only after it is inserted by the crew. AOC uplink
winds are then considered as crew manual entries (large font).
SCRATCHPAD MESSAGES RELATED TO WIND DATA
INVALID WIND UPLINK An error is detected, the uplink is rejected.
WIND DATA UPLINK
Uplinked winds are received.
WIND UPLINK PENDING A temporary flight plan exists or a DIR TO page is displayed when a
wind uplink is received. The message is stored.
WIND UPLINK EXISTS
A F-PLN modification (active or secondary) is attempted when uplink
winds are not inserted. This message disappears automatically when
the wind uplink is inserted or deleted.
CHECK DEST DATA
The aircraft is at 180 NM from destination, and the destination QNH ,
TEMP or WIND displayed on the PERF APPR page was received by
AOC uplink or, if following insertion of a descent wind uplink, a conflict
concerning the above parameters exists.
CHECK ALTN WIND
The uplinked alternate cruise flight level differs from the default
alternate cruise flight level.
FLIGHT REPORTS
Ident.: DSC-22_45-00000868.0001001 / 01 OCT 12
Applicable to: ALL
Flight reports provide real time information to the ground concerning the aircraft current situation and
position.
Several types of flight reports are available:
‐ The Position report : provides current aircraft position
‐ the Progress report : provides data relative to the destination
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FCOM
← D to E →
DSC-22_45 P 5/8
24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
‐ The Flight-Plan report : provides the active route
‐ the Performance Data report : provides performance data currently used by FMS.
These reports may be manually initiated via a dedicated prompt or automatically sent in response to
a ground request or upon specific conditions.
POSITION REPORT
This report is sent:
‐ manually via a MCDU prompt or
‐ following a ground request or
‐ automatically upon sequencing a designated reporting fix (designated by the ground in a uplink
message).
The manual POSITION REPORT downlink prompt is displayed on the PROG page. (SEND POS
prompt).
Note:
Position report are initiated from active flight plan only.
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←E→
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
POSITION REPORT CONTENT
‐
‐
‐
‐
‐
‐
‐
‐
‐
‐
Aircraft position
Overfly reporting waypoint
Time of report (UTC)
Aircraft altitude
Next reporting waypoint
ETA at next reporting waypoint
Reporting waypoint following next report
SAT
Current wind
Remaining fuel
PROGRESS REPORT
A progress report contains data relative to the aircraft arrival time and EFOB at destination for the
active F-PLN.
This downlink message is automatically sent following:
‐ a ground request or
‐ a change of destination or
‐ a change of runway or
‐ a specific event. The possible events that can be selected in the navigation database policy file
are :
• X minutes to Top of Descent
• Z minutes to Destination
• ETA changes more than W minutes from the previous report.
X, Z and W are minutes of time set in the navigation database policy file.
The progress report cannot be manually sent by the crew via a dedicated MCDU prompt.
PROGRESS REPORT CONTENT
‐
‐
‐
‐
‐
‐
Flight Number
Arrival Airport Ident
Destination Runway Ident
Predicted remaining fuel
ETA at destination
Reason for report (specific event, ground request...).
FLIGHT PLAN REPORT
The F-PLN report broadcasts flight plan data to the ground. Only data from the active flight plan
can be sent.
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FCOM
←E→
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24 JAN 17
AIRCRAFT SYSTEMS
AUTO FLIGHT - AOC FUNCTIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
This downlink message is sent to the ground:
‐ automatically following a ground request
‐ manually by the crew using a prompt displayed on the ACARS FUNCTION page ( DSC-22_20
Auto Flight - Flight Management/50 Controls and Indicators/10 MCDU - Page Description/25
FMS2 Honeywell/ACARS Function Page). This prompt may be invalidated through the
navigation database policy file.
The Flight Plan report can be downlinked either while on ground or in flight during any flight phase.
FLIGHT PLAN REPORT CONTENT
The report contains the active and alternate flight plan.
PERFORMANCE DATA REPORT
The Performance Data report is a downlink message that allows the transmission of performance
data (CG , FUEL, CG ...) relative to the active F-PLN.
This message is automatically sent following a ground request. Manual sending is not possible.
PERFORMANCE DATA REPORT CONTENT
Sends to the ground:
‐ Current GW
‐ Cruise Altitude
‐ Current CG
‐ Fuel on Board
‐ Block Fuel
‐ Reserve Fuel
‐ Cost Index
‐ Top of Climb Temperature
‐ Climb Transition Altitude
‐ Tropopause Altitude
‐ Taxi Fuel
‐ ZFW
‐ ZFWCG
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←E
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AIRCRAFT SYSTEMS
AUTO FLIGHT - PRINT INTERFACE
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AIRCRAFT SYSTEMS
AUTO FLIGHT - PRINT INTERFACE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Print Function...........................................................................................................................................................A
AOC/Printer Programming Options ................................................................................................................ B
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRINT FUNCTION
Ident.: DSC-22_46-00000869.0003001 / 01 APR 11
Applicable to: ALL
The print function enables several types of data and report to be printed :
• Flight plan initialization data
• Takeoff data
• Wind data
• Preflight report
• In flight report
• Post flight report
The 3 first reports may differ when automatically or manually printed for the following reason :
The automatic process prints the uplink message although the manual process prints the current
active data as displayed on the relevant MCDU pages.
The last 3 reports being processed from the same sources are identical in automatic or manual
printing.
Note:
ACARS is not necessary linked to printing process. The printing function may be activated
within the FMGS and selected independently from the ACARS.
‐ One or several print functions may be deactivated Refer to DSC-22_20-50-10-25 Print Function
Pages.
‐ If an ACARS function is not active, (not selected in the nav database policy file) the printing
process is invalidated for this specific ACARS function.
AOC/PRINTER PROGRAMMING OPTIONS
Ident.: DSC-22_46-00000870.0002001 / 11 FEB 11
Applicable to: ALL
Option programming for the AOC /PRINTER functions is obtained through the Navigation Data Base
policy file or the Airline Modifiable Information (AMI) file.
The list summarizes the possible options:
Data Link (ACARS or AOC) Inhibit
F-PLN Data Request Inhibit
Performance Data Request Inhibit
Takeoff Data Request Inhibit
Wind Data Request Inhibit
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Disables AOC function
Disables uplink and downlink requests of F-PLN
initialization data
Disables uplink and downlink requests of Performance
Initialization data
Disables uplink and downlink request of Takeoff
Initialization data
Disables uplink and downlink request of predicted wind
data
A to B →
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AIRCRAFT SYSTEMS
AUTO FLIGHT - PRINT INTERFACE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Flight Number Enable
Position Report Inhibit
Progress Report Triggers
F-PLN Report Inhibit
Auto Print of ACARS or AOC uplinks
Auto Print of Flight Reports
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Flight Number is included within the F-PLN Request or
Progress Report downlinks
Disables a manual Position Report downlink
Defines the triggers for the automatic downlink of the
Progress Report
Disables the manual downlink of the F-PLN Report
Selects/Deselects the automatic printing of the F-PLN ,
INIT , TO and wind data uplinks.
If Autoprint is selected, the crew can deselect it
manually.
If auto printing is deselected, the crew cannot manually
reselect it.
Selects/Deselects the automatic printing of the
Preflight, Inflight, Postflight reports.
If selected, the crew can deselect it manually.
If autoprint is deselected, the crew cannot manually
preselected it.
←B
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AIRCRAFT SYSTEMS
COMMUNICATIONS
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AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-23-10 General
DSC-23-10-10 Introduction
Introduction...............................................................................................................................................................A
DSC-23-10-20 Radio Tuning
Description............................................................................................................................................................... A
Radio Management Panel....................................................................................................................................... B
DSC-23-10-30 Intercommunication Systems
Audio Management System.................................................................................................................................... A
Cabin Intercommunication Data System................................................................................................................. B
DSC-23-10-40 Cockpit Voice Recorder
Description............................................................................................................................................................... A
Controls and Indicators............................................................................................................................................B
DSC-23-10-50 Controls
Audio Control Panel.................................................................................................................................................A
Side Stick Radio Selector........................................................................................................................................B
Loudspeaker Volume Knob..................................................................................................................................... C
Audio Switching....................................................................................................................................................... D
DSC-23-20 Internal Communication
DSC-23-20-10 Flight Crew Interphone System
Flight Crew Interphone System............................................................................................................................... A
DSC-23-20-20 Cabin Interphone System
Introduction...............................................................................................................................................................A
Cabin Call System................................................................................................................................................... B
DSC-23-20-30 Service Interphone System
Introduction...............................................................................................................................................................A
Ground Mechanic Call System................................................................................................................................B
DSC-23-20-40 Passenger Address
Description............................................................................................................................................................... A
Controls and Indicators............................................................................................................................................B
Continued on the following page
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AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-23-30 External Communication
DSC-23-30-10 Radio Communication
Continued from the previous page
Description............................................................................................................................................................... A
VHF.......................................................................................................................................................................... B
HF............................................................................................................................................................................ C
SELCAL (Selective calling)..................................................................................................................................... D
DSC-23-40 Emergency Communication
DSC-23-40-10 Emergency Evacuation
Controls and Indicators............................................................................................................................................A
Purser Station.......................................................................................................................................................... B
DSC-23-40-30 Emergency Locator Transmitter
Controls and Indicators............................................................................................................................................A
DSC-23-50 Memo Display
ACARS ........................................................................................................................................................... A
ATSU .............................................................................................................................................................. B
AUDIO 3 XFRD....................................................................................................................................................... C
SATCOM ........................................................................................................................................................ D
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05 SEP 17
AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
GENERAL - INTRODUCTION
FLIGHT CREW
OPERATING MANUAL
INTRODUCTION
Ident.: DSC-23-10-10-00018503.0001001 / 17 MAR 17
Applicable to: ALL
The communications system comprises the following subsystems :
‐ VHF/HF transceivers
‐ Radio tuning systems (Radio Management Panels).
‐ Audio integrating system (Audio Management Unit, Audio Control Panels).
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A
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AIRCRAFT SYSTEMS
COMMUNICATIONS
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GENERAL - INTRODUCTION
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
GENERAL - RADIO TUNING
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-23-10-20-00018494.0001001 / 17 MAR 17
Applicable to: ALL
Identical Radio Management Panels (RMPs):
‐ Give the flight crew control of all VHF radio communication systems (HF systems ).
‐ Provide backup to the FMGCs for controlling radio navigation systems (Refer to
DSC-34-NAV-30-10 General).
The two RMPs are on the center pedestal (and the third is on the overhead panel).
Each RMP can control any VHF (HF ) transceiver. RMP 1 and RMP 2 are connected directly
to all VHF (HF ) transceivers, (whereas RMP3 is connected to them via RMP 1 and RMP
2). RMP s are connected together so that each RMP is updated to the selections made on the other
RMPs.
Only RMP1 functions in EMER ELEC CONFIG.
If one RMP fails, the remaining one controls all the VHF (HF ) transceivers.
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AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
GENERAL - RADIO TUNING
FLIGHT CREW
OPERATING MANUAL
RADIO MANAGEMENT PANEL
Ident.: DSC-23-10-20-00018495.0002001 / 17 MAR 17
Applicable to: ALL
(1)
Frequency displays
The ACTIVE display window shows the active frequency of the selected radio, which is
identified by a green light on the selection key.
The STBY /CRS (standby/course) display window shows a standby frequency that the pilot can
activate by pressing the transfer key or change by rotating the tuning knobs. (For a description
of the CRS function Refer to DSC-34-NAV-30-30 Radio Management Panel (RMP)).
(2)
Transfer key
Pressing this key moves the active frequency to the standby window and the standby
frequency to the active window.
This tunes the selected receiver to the new active frequency.
(3)
Radio com selection keys
When the pilot presses one of these keys:
• The ACTIVE window displays the frequency set on that radio.
• The STBY /CRS window displays the selected standby frequency or course.
• The selected key displays a green monitor light.
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AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL - RADIO TUNING
(4)
Frequency selector knobs
The pilot uses these concentric knobs to select the STBY frequency or CRS.
The outer knob controls whole numbers; the inner knob controls decimal fractions.
(5)
AM pb-sw
If the aircraft has HF radios and the flight crew has selected an HF tranceiver, this switch
selects the AM mode. (The default mode is the SSB, or single side-band, mode).
This key displays a green monitor light when the AM mode is active.
(6)
SEL indicator
The SEL indicator on both RMP s comes on amber when a transceiver normally associated
with one RMP is tuned by another:
• VHF 1 tuned by RMP 2 or RMP 3,
• VHF 2 tuned by RMP 1 or RMP 3.
• VHF 3, HF 1, HF 2 ( ) tuned by RMP 1 or RMP 2.
(7)
NAV pb sw (with transparent switchguard)
The pilot presses this key to be able to select navigation receivers and courses through the
RMP. It does not affect the selection of communication radios and their frequencies. (Refer to
DSC-34-NAV-30-30 Radio Management Panel (RMP), for additional information).
(8)
Radio navigation selection keys
The pilot presses one of these keys to select a navigation radio to control through this RMP.
This turns on the green monitor light in the key.
Refer to DSC-34-NAV-30-30 Radio Management Panel (RMP), for additional information.
(9)
ON/OFF sw
This switch controls the power supply to the RMP.
Note:
RMP 3 is able to control VHF and HF transceivers through RMP 1 and RMP 2 even
when they are OFF.
(10) LOAD FUNCTION
When the ATC sends (CONTACT or MONITOR) CPDLC messages to the flight crew, a white
light above the LOAD key comes on to indicate that the sent frequency is available to be
loaded.
Press on this LOAD key before closing the CONTACT/MONITOR messages to load this VHF
frequency to the STBY /CRS window.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←B→
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AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
GENERAL - RADIO TUNING
When a frequency from the ATC services (sent label via datalink) has been received,
the ATSU validates the frequency and simultaneously sends the information to all the
RMP in order to activate the LOAD function.
When the LOAD function is activated, the flight crew can repeatedly load the
frequency on each RMP as often as necessary; except if DATA is present on standby
window.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
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AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
GENERAL - INTERCOMMUNICATION SYSTEMS
FLIGHT CREW
OPERATING MANUAL
AUDIO MANAGEMENT SYSTEM
Ident.: DSC-23-10-30-00018496.0002001 / 17 MAR 17
Applicable to: ALL
The audio management system allows the flight crew to use :
‐ All the radio communication and radio navigation facilities installed on the aircraft in transmission
and reception mode.
‐ The interphone systems.
‐ The call systems.
‐ The passenger address system.
The audio management system includes :
‐ An audio management unit (AMU).
‐ Three audio control panels (ACPs) (fourth and fifth optional).
‐ Sockets at each station:
• Headset jack and boomset connector (hand microphone connector ) for pilot, copilot, and
third occupant.
• Headset jack for fourth occupant.
‐ One interphone jack at the ground power receptacle.
‐ Boomsets for the pilot, copilot, and third occupant, and three hand microphones (fourth ).
‐ Three cockpit oxygen mask microphones.
‐ One radio press-to-talk switch on each sidestick.
‐ One SELCAL code selection panel (avionics compartment).
‐ Two cockpit loudspeakers with separate volume controls.
‐ If installed, a jack panel in the electronic compartment that groups the headset jack, service
interphone jack, hand mike connector, and boomset.
‐ An audio switching facility.
If audio channel 1 or 2 fails due to a failure either in an ACP or the corresponding AMU, the crew can
use the AUDIO SWITCHING selector to select the third audio channel.
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AIRCRAFT SYSTEMS
COMMUNICATIONS
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FLIGHT CREW
OPERATING MANUAL
GENERAL - INTERCOMMUNICATION SYSTEMS
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FCOM
←A→
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22 MAR 17
AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL - INTERCOMMUNICATION SYSTEMS
LOCATION OF COMPONENTS (PILOT’S STATION)
CABIN INTERCOMMUNICATION DATA SYSTEM
Ident.: DSC-23-10-30-00018497.0002001 / 17 MAR 17
Applicable to: ALL
The Cabin Intercommunication Data System (CIDS) transmits, controls, and processes signals for
the following cabin systems :
‐ Cabin and service interphone
‐ Passenger address
‐ Passenger lighted signs
‐ Reading lights (LED technology)
‐ General cabin illumination
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-23-10-30 P 3/4
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AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
‐
‐
‐
‐
‐
‐
GENERAL - INTERCOMMUNICATION SYSTEMS
Emergency evacuation signalling
Lavatory smoke detectors and indicators
Passenger entertainment music and video
Escape slide bottle pressure monitoring
Vacuum system control function
Cargo and lavatory smoke detection function
The CIDS has the following main components :
‐ Two CIDS directors connected in parallel ; one active, and the other on standby.
‐ Flight Attendant Panel (FAP) to monitor and control the cabin systems.
‐ Attendant Indication Panels (AIP), After Attendant Panels (AAP) and Area Call Panels (ACP)
‐ Decoder/Encoder Units (DEUs) linked to the two directors.
• Type A units (for passengers) installed along the cabin.
The loudspeakers, lighted signs, call buttons, call lights and general illumination ballast units are
divided into small groups, each connected to a type A DEU.
• Type B units (for attendants) installed near the exit doors. The Area Call panels, smoke
detectors, attendant handsets, slide and door pressure sensors, and attendant indicator panels,
are connected to type B DEUs.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
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22 MAR 17
AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
GENERAL - COCKPIT VOICE RECORDER
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-23-10-40-00018569.0002001 / 17 MAR 17
Applicable to: ALL
The cockpit voice recorder (CVR) records :
‐ direct conversations between crew members in the cockpit
‐ all aural warnings sounded in the cockpit
‐ audio communications received and transmitted
‐ intercommunications conversations between crew members
‐ announcements transmitted over the passenger address system, if PA reception is selected on at
least one audio control panel.
Only the last 2 h of recording are retained.
The CVR system consists of :
‐ a remote microphone behind the overhead panel
‐ a “hot mike” function, which records the crew members voice directly from their microphone, even
if the push to talk switch is not activated.
‐ a crashproof four-track recorder, equipped with an underwater locating beacon, in the aft section
of the aircraft
‐ a control panel on the overhead panel.
It is energized automatically :
‐ on the ground during the first 5 min after the aircraft electrical network is energized
‐ on the ground with one engine running
‐ in flight
On the ground, it is stopped automatically 5 min after the last engine shutdown provided the CVR
jack is not used.
On the ground, the crew can energize the CVR manually by pressing the GND CTL pushbutton.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
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22 MAR 17
AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
GENERAL - COCKPIT VOICE RECORDER
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
Ident.: DSC-23-10-40-00018570.0001001 / 17 MAR 17
Applicable to: ALL
(1)
GND CTL switch (spring-loaded)
ON : The CVR , DFDR , and QAR are on.
The ON light comes on blue.
AUTO : The CVR , DFDR , and QAR are on, according to the logic. (Refer to
DSC-23-10-40 Description).
(2)
CVR ERASE pb
Pressed for 2 s : This completely erases the tape, if :
‐ The aircraft is on the ground, and
‐ The parking brake is on.
(3)
CVR TEST pushbutton
Pressed and : This activates the test, if the CVR is on (the GND CTL pushbutton pressed,
held
or during the first 5 min after energization of the aircraft electrical network),
and the parking brake is on.
Refer to PRO-NOR-SOP-06 Overhead Panel - RCDR for additional
information.
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B
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22 MAR 17
AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
GENERAL - CONTROLS
FLIGHT CREW
OPERATING MANUAL
AUDIO CONTROL PANEL
Ident.: DSC-23-10-50-00018498.0002001 / 17 MAR 17
Applicable to: ALL
(1)
Transmission keys
Pressed
: The associated channel is selected for transmission.
The three green lines come on.
The pilot deselects the channel by pressing the pushbutton again, or
selecting another channel.
CALL
: The legend flashes amber (and buzzer sounds) when the SELCAL system
detects a call.
MECH
: The legend flashes amber (and buzzer sounds) for a call from the nose gear
bay. The MECH light goes off after 60 s, if it is not reset.
ATT
: The legend flashes amber (and buzzer sounds) for a call from a cabin crew
member. The ATT light goes off after 60 s, if it is not reset.
SAT CALL It : The legend flashes amber when the SATCOM system detects a call.
The three green lines flash during the establishment of air to ground calls, or
when SATCOM calls are on hold.
After call establishment, the three green lines remain steady.
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
GENERAL - CONTROLS
FLIGHT CREW
OPERATING MANUAL
(2)
Reception knobs
‐ Pressing and releasing the knob (knob out) selects the associated audio reception channel
and the integral white light comes on
‐ Rotating the knob adjusts the volume
‐ The INTEG LT knob or ANN LT knob controls the brightness
‐ Pressing the knob (knob stays in) disconnects the associated audio reception channel.
Note:
To receive DME audio navigation signals that are associated with an ILS or MLS or
GLS station: the flight crew must select the ILS pb (or LS pb) on the FCU . On some
aircraft, the VOR reception channel must also be active on the ACP.
(3)
SELCAL/CALL RESET key
Pressing this key extinguishes CALL, MECH , and ATT lights.
(4)
ON VOICE key
This key allows the flight crew to inhibit the audio navigation signals (VOR , ADF)
Pressing this key filters out IDENT signals and turns on the green ON light.
(5)
INT/RAD switch
This switch operates as a press-to-talk switch for boom mike or oxygen mask mike.
INT
: Boom and mask mikes transmit on interphone regardless of
which transmission key is selected. For reception on interphone,
the crew member must have INT selected (INT reception knob
out).
Neutral
: Reception is normal. Boom and mask mikes do not transmit.
RAD (press and hold) : Boom and mask mikes transmit on the radio selected on the
audio control panel.
(6)
Passenger address (PA) function
(Refer to DSC-23-20-40 Description).
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AIRCRAFT SYSTEMS
COMMUNICATIONS
A318/A319/A320/A321
GENERAL - CONTROLS
FLIGHT CREW
OPERATING MANUAL
SIDE STICK RADIO SELECTOR
Ident.: DSC-23-10-50-00018499.0001001 / 17 MAR 17
Applicable to: ALL
This selector has the same function as the INT/RAD switch on the ACP.
NEUTRAL (spring-loaded) : Boom and mask mikes are dead.
Reception is normal.
RADIO (squeezed)
: Boom and mask mikes transmit through the equipment selected by
the transmission key on the ACP.
Note:
If RADIO is selected on the side stick when the INT/RAD switch is on INT, the radio
function has priority over the interphone function.
LOUDSPEAKER VOLUME KNOB
Ident.: DSC-23-10-50-00018500.0001001 / 17 MAR 17
Applicable to: ALL
This knob adjusts the volume of the loudspeaker for radio communication.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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B to C →
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
GENERAL - CONTROLS
FLIGHT CREW
OPERATING MANUAL
OFF
:
Clockwise rotation
:
Note:
Loudspeaker does not respond to signals from the aircraft's radio
equipment.
Loudspeaker broadcasts signals from the aircraft's radio equipment at
increasing volume.
This knob does not control the loudness of aural alert and voice messages.
In the case of acoustic feedback (i.e. Larsen effect) from the cockpit loudspeaker, the flight
crew should reduce the volume of the cockpit loudspeaker. However, the flight crew should
ensure that the volume of the cockpit loudspeaker is sufficient to hear radio communication.
AUDIO SWITCHING
Ident.: DSC-23-10-50-00018501.0001001 / 17 MAR 17
Applicable to: ALL
The crew can switch to the third ACP if ACP 1 or ACP2 fails.
When the crew does this, it takes away the third occupant's access to the acoustic equipment.
AUDIO 3 XFRD appears in green on the ECAM MEMO display.
NORM : Each crew member uses his dedicated communication equipment.
CAPT 3: The pilot uses his acoustic equipment and the third occupant's ACP.
F/O 3 : The copilot uses his acoustic equipment and the third occupant's ACP.
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AIRCRAFT SYSTEMS
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INTERNAL COMMUNICATION - FLIGHT CREW INTERPHONE SYSTEM
FLIGHT CREW INTERPHONE SYSTEM
Ident.: DSC-23-20-10-00019716.0001001 / 17 MAR 17
Applicable to: ALL
This system allows the flight crew members to communicate among themselves and, through a jack
on the external power panel, with the ground mechanic.
EXTERNAL POWER PANEL (FORWARD OF THE NOSE L/G BAY)
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INTERNAL COMMUNICATION - CABIN INTERPHONE SYSTEM
FLIGHT CREW
OPERATING MANUAL
INTRODUCTION
Ident.: DSC-23-20-20-00018481.0001001 / 20 JUL 17
Applicable to: ALL
The system allows the flight crew to communicate with the flight attendants, and the flight attendants
to communicate among themselves.
Note:
Cabin interphone monitoring may be deactivated in flight depending on CIDS
customization.
(1)
CAB transmission key
Pressed : Three green lines come on.
Boom, mask, and hand mikes may be used for cabin interphone.
(2)
CAB reception knob
Pressed and released :
(knob out)
Pressed (knob in)
:
The integral white light comes on.
The station receives audio signals from the cabin.
Rotating the knob adjusts the volume.
The white light goes out.
The cabin interphone is disconnected.
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
INTERNAL COMMUNICATION - CABIN INTERPHONE SYSTEM
CABIN CALL SYSTEM
Applicable to: ALL
Ident.: DSC-23-20-20-10-00018482.0001001 / 02 NOV 16
CALLS FROM THE COCKPIT
The pushbuttons described here below are installed on the CALLS panel located on the overhead
panel.
PURS /FWD/MID /EXIT /AFT PUSHBUTTON
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INTERNAL COMMUNICATION - CABIN INTERPHONE SYSTEM
When pressed, the following aural and visual alerts will trigger in the cabin:
‐ Two lights come on in pink on the related area of the CALLS panel, as applicable.
‐ On the Attendant Indication Panel (AIP), the “CAPTAIN CALL” message appears and a light
comes on in green.
‐ A high-low chime sounds in the related section of the cabin, as applicable.
ALL pb
When pressed, all the stations simultaneously respond, as indicated above.
EMER pb-sw (GUARDED)
When pressed, the following aural and visual alerts will trigger in the cabin:
‐ Two pink lights flash on all area call panels.
‐ The “EMERGENCY CALL” message appears on all AIPs.
‐ A high-low chime sounds three times, on all of the loudspeakers.
Depending on aircraft configuration, on the cockpit CALLS panel, the white ON light and the
amber CALL light come on.
The following aural and visual alerts will trigger in the cockpit, when an emergency call is made
from the cabin to the cockpit:
‐ On the EMER pb-sw: The amber CALL light flashes.
‐ The ATT lights will flash on all Audio Control Panels (ACPs).
‐ Three buzzers will sound consecutively (for approx. three seconds each).
The cabin call system will reset, when the cabin crewmember hangs up the handset.
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INTERNAL COMMUNICATION - CABIN INTERPHONE SYSTEM
TT light
When the TT pb on the FWD or AFT Attendant Panel is pressed, the TT light on the cockpit
CALLS panel comes ON and a buzzer sounds three times in the cockpit.
ATTND ADV pb
When pressed, in the case of an imminent takeoff or landing, the ON light comes on in blue, in
addition to a green light on the area call panel in the cabin.
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INTERNAL COMMUNICATION - CABIN INTERPHONE SYSTEM
Ident.: DSC-23-20-20-10-00018483.0001001 / 17 MAR 17
CALLS FROM THE CABIN
(1)
CPT key
When pressed, the following aural and visual alerts will trigger in the cockpit:
‐ The ATT lights will flash on all Audio Control Panels (ACPs).
‐ A buzzer (inhibited during takeoff and landing) will sound.
In the cabin, the “CAPTAIN” message will appear on the Attendant Indication Panel (AIP) for
which the CPT key was pressed.
(2)
EMER CALL key
When pressed, the following aural and visual alerts will trigger in the cockpit:
‐ On the EMER pb-sw: The ON light flashes in white, and the CALL light flashes in amber.
‐ The ATT lights will flash on all ACPs.
‐ Three buzzers (inhibited during takeoff and landing) will sound consecutively.
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INTERNAL COMMUNICATION - CABIN INTERPHONE SYSTEM
In the cabin, the “EMERGENCY CALL” message will appear on all AIPs or on the AIP of the
originating station based on its customization.
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INTERNAL COMMUNICATION - SERVICE INTERPHONE SYSTEM
INTRODUCTION
Ident.: DSC-23-20-30-00018485.0001001 / 20 JUL 17
Applicable to: ALL
The system allows for communication between :
‐ The flight crew and the service interphone jacks.
‐ The flight attendant stations and the service interphone jacks.
‐ The different service interphone jacks.
The Service Interphone system has :
‐ Seven interphone jacks.
‐ An OVRD switch located on the overhead panel.
The audio lines from the interphone jacks are connected to both CIDS directors.
LOCATION OF INTERPHONE JACKS
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INTERNAL COMMUNICATION - SERVICE INTERPHONE SYSTEM
CONTROLS AND INDICATORS AT OVERHEAD PANEL
(1)
SVCE INT OVRD pushbutton switch
Auto : Ground personnel can communicate with the flight crew by means of the service
interphone jacks 10 s after the aircraft has landed. The landing gear must be
compressed.
ON : Communication is possible when the landing gear is not compressed.
The ON light is white.
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FLIGHT CREW
OPERATING MANUAL
GROUND MECHANIC CALL SYSTEM
Applicable to: ALL
Ident.: DSC-23-20-30-10-00018486.0001001 / 17 MAR 17
CONTROLS AND INDICATORS ON OVERHEAD PANEL
MECH pb
Pressed (and held) :
Released
:
COCKPIT CALL lights up blue on the external power panel in the nose
L/G bay.
An external horn sounds.
COCKPIT CALL remains lighted.
The ground mechanic can extinguish it by pressing the RESET button
on the external power panel. The external horn stops sounding.
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INTERNAL COMMUNICATION - SERVICE INTERPHONE SYSTEM
Ident.: DSC-23-20-30-10-00018487.0001001 / 17 MAR 17
CONTROLS AND INDICATORS ON THE EXTERNAL POWER PANEL
(1)
COCKPIT CALL pushbutton
Pressed : This calls the cockpit.
The MECH lights flash amber on the ACPs and a buzzer sounds.
Released : The MECH lights go out after 60 s if they are not reset on the ACPs.
The buzzer stops.
(2)
COCKPIT CALL light
The blue light appears when cockpit calls the ground mechanic. An external horn also
sounds.
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(3)
INTERNAL COMMUNICATION - SERVICE INTERPHONE SYSTEM
RESET pushbutton
Pressed: The COCKPIT CALL light goes out.
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INTERNAL COMMUNICATION - PASSENGER ADDRESS
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-23-20-40-00018685.0001001 / 17 MAR 17
Applicable to: ALL
The passenger address allows all crew members to make announcements to passengers in the
cabin through loudspeakers. It can be operated from the cockpit (with ACP or handset) or from the
cabin (attendant stations).
CONTROLS AND INDICATORS
Ident.: DSC-23-20-40-00018686.0001001 / 20 JUL 17
Applicable to: ALL
(1)
(2)
PA reception knob
Pressed and released :
(knob out)
Pressed (knob in)
:
PA transmission key
Pressed and held
:
Note:
The message goes to the loudspeakers, and the integral white light
comes on.
The flight crew can turn the knob to adjust the volume.
The PA reception to the loudspeakers is disconnected.
The white light goes out.
The flight crew may use a boom, mask, or hand mike to make an
announcement.
Three green lines come on.
The flight crew may use a cockpit handset to make PA announcements without action
on the ACPs.
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INTERNAL COMMUNICATION - PASSENGER ADDRESS
(3)
OBS AUDIO ENT sw
ON
: Announcement from the cockpit can be heard through channel 9 of
Passenger Entertainment System (PES).
OFF
: Normal functionning of PES is restored.
(4)
PAIN USE light
The light comes on when the PA is activated from the cockpit or from the cabin (cabin
attendant or prerecorded announcement).
(5)
IFEIN USE light
The light comes on when the IFE system is in use.
(6)
VIDEO IN USE light
The light comes on when the video system is in use.
The flight crew can also use the cockpit handset, located at the bottom of the pedestal, for PA
announcements.
Note:
Due to numerous customizations of the handset and keypad, their functions are not
described in detail.
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EXTERNAL COMMUNICATION - RADIO COMMUNICATION
DESCRIPTION
Ident.: DSC-23-30-10-00018475.0001001 / 17 MAR 17
Applicable to: ALL
Either of the two Radio Management Panels (RMPs) (third RMP ) can be used to tune each
transceiver.
To transmit, the flight crew uses the Audio Control Panel (ACP ) to select a VHF or HF system. The
ACP works through the Audio Management Unit (AMU ). Each system is connected to the RMP s, for
frequency selection, and to the AMU for connection to the audio integrating and SELCAL (selective
calling) systems.
VHF
Ident.: DSC-23-30-10-00018472.0001001 / 27 APR 17
Applicable to: ALL
Two identical VHF communication systems (third VHF system ) are installed.
Each system has a transceiver in the avionics compartment, and an antenna on the fuselage. Only
VHF1 functions in EMER ELEC CONFIG. Its range is from 118.0 to 136.975 MHz.
HF
Ident.: DSC-23-30-10-00018473.0003001 / 04 JUL 17
Applicable to: ALL
Two identical HF communication systems are optional. Each has a transceiver in the avionics
compartment, and a common tuner and antenna in the vertical stabilizer. Its range is from 2.8 to 24
MHz.
The HF DATA transmission is inhibited on ground. A GND HF DATALINK pb, located on the
overhead panel, may override the inhibition. HF must not be used during refueling.
The HF VOICE MODE is not inhibited on ground. The use of HF on ground must be limited to
operational needs. It is important to check that nobody stays in the direct vicinity of the antennas if
the HF is use on ground.
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EXTERNAL COMMUNICATION - RADIO COMMUNICATION
SELCAL (SELECTIVE CALLING)
Ident.: DSC-23-30-10-00018476.0001001 / 17 MAR 17
Applicable to: ALL
Upon receiving a call code corresponding to that of the aircraft, the SELCAL system aurally and
visually advises the flight crew that a ground station is calling the aircraft.
The aural warning is inhibited during takeoff and landing.
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EMERGENCY COMMUNICATION - EMERGENCY EVACUATION
CONTROLS AND INDICATORS
Ident.: DSC-23-40-10-00018468.0001001 / 18 MAY 17
Applicable to: ALL
(1)
COMMAND pb (guarded)
ON :
In the cockpit : ‐ EVAC light flashes red.
‐ Depending on aircraft configuration, horn sounds.
In the cabin : ‐ EVAC lights flash at FWD and AFT attendant panels.
‐ Evacuation tone sounds.
OFF : The alert is stopped.
The EVAC light flashes red when the alert is activated.
(2)
HORN SHUT OFF pb
Pressing this button silences the cockpit horn.
(3)
CAPT and PURS/CAPT sw
CAPT and PURS : The alert may either be activated from the cockpit or the cabin.
CAPT
: The alert may only be activated from the cockpit.
If one of the cabin CMD pb is pressed, only the cockpit horn sounds for
3 s.
(4)
CMD pb
Pressing this button activates the alert, if the cockpit switch is at the CAPT & PURS position.
Pressing it again stops the alert.
(5)
RESET pb
Pressing this button silences the EVAC tone.
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(6)
EMERGENCY COMMUNICATION - EMERGENCY EVACUATION
EVAC light
This light flashes when the alert is activated.
PURSER STATION
Ident.: DSC-23-40-10-00018469.0001001 / 17 MAR 17
Applicable to: ALL
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EMERGENCY COMMUNICATION EMERGENCY LOCATOR TRANSMITTER
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
Ident.: DSC-23-40-30-00018516.0002001 / 17 MAR 17
Applicable to: ALL
(1)
ELT selector
ON
:
ARMED
:
TEST/RESET :
Note:
The Emergency Locator Transmitter (ELT) transmits an emergency signal.
In case of impact, the ELT transmits an emergency signal (on 121.5, 243
and 406 MHz).
Starts the ELT autotest.
If the ELT is unduly triggered in ARMED mode (by an external impact, hard landing,
etc.), select the TEST/RESET position to reset the ELT and stop signal transmission.
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(2)
EMERGENCY COMMUNICATION EMERGENCY LOCATOR TRANSMITTER
ON light and ELT light
These lights come on amber either when the emergency signal is transmitted, or during ELT
autotest.
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MEMO DISPLAY
FLIGHT CREW
OPERATING MANUAL
ACARS
Ident.: DSC-23-50-00018505.0001001 / 31 AUG 17
Applicable to: ALL
ACARS CALL :
This memo appears in green when ACARS has received a message from the
ground requesting a voice communication on VHF. This message is pulsing
green during 60 s then steady.
This memo appears in green when VHF 3 is operating in voice mode and ACARS
communication is interrupted.
This memo appears in green when ACARS has received a message from the
ground. This message is pulsing green during 60 s then steady.
This memo appears in green when ACARS communications between the aircraft
and the ground are lost, or when a failure occurs at ATSU initialization to indicate
to the crew to enter some initialization parameters.
VHF 3 VOICE :
ACARS MSG :
ACARS STBY :
ATSU
Ident.: DSC-23-50-00018506.0001001 / 31 AUG 17
Applicable to: ALL
VHF 3 VOICE
:
HF VOICE
:
This memo appears in green, if VHF 3 is operating in voice mode and ACARS
communication is interrupted.
This memo appears in green, if both HF s are operating in voice mode.
This message flashes for 10 s and then steady.
AUDIO 3 XFRD
Ident.: DSC-23-50-00018507.0001001 / 17 MAR 17
Applicable to: ALL
AUDIO 3 XFRD
:
This memo appears in green, if the AUDIO SWITCHING selector is not on
NORM.
SATCOM
Ident.: DSC-23-50-00018508.0001001 / 31 AUG 17
Applicable to: ALL
SATCOM ALERT :
This memo appears in green when a message with priority level below 4 is
received from the ground.
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PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-24-10 Description
DSC-24-10-10 General
General.....................................................................................................................................................................A
DSC-24-10-20 Generation of Electrical Power
AC Generators......................................................................................................................................................... A
DC Generation......................................................................................................................................................... B
Circuit Breakers (C/Bs)............................................................................................................................................C
DSC-24-10-30 Operations
DSC-24-10-30-10 General
General.....................................................................................................................................................................A
DSC-24-10-30-20 Normal Configuration
In Flight.................................................................................................................................................................... A
On Ground............................................................................................................................................................... B
DSC-24-10-30-30 Abnormal Configurations
Failure of One Engine Generator............................................................................................................................A
Failure of AC BUS 1............................................................................................................................................... B
Failure of One TR................................................................................................................................................... C
Failure of TR 1 and TR 2....................................................................................................................................... D
Emergency Generation after Loss of All Main Generators..................................................................................... E
EMER GEN Running............................................................................................................................................... F
EMER GEN Running (Cont'd).................................................................................................................................G
Flight with Batteries Only........................................................................................................................................ H
On Ground, Batteries Only (Speed < 50 kt).............................................................................................................I
Smoke Configuration................................................................................................................................................ J
DSC-24-10-30-40 Distribution Table
Distribution Table..................................................................................................................................................... A
DSC-24-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Overhead Panel (Cont'd)......................................................................................................................................... B
External Power Panel..............................................................................................................................................C
Forward Cabin......................................................................................................................................................... D
ECAM ELEC Page.................................................................................................................................................. E
Memo Display.......................................................................................................................................................... F
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DESCRIPTION - GENERAL
GENERAL
Ident.: DSC-24-10-10-00017750.0001001 / 21 MAR 16
Applicable to: ALL
The electrical power system consists of a three-phase 115/200 V 400 Hz constant-frequency AC
system and a 28 V DC system. Electrical transients are acceptable for equipment. Commercial
supply has secondary priority.
In normal configuration, the electrical power system provides AC power. The electrical power system
is constituted of 2 engine generators and 1 APU generator. Each generator can provide AC power to
all electrical bus bars. A part of this AC power is converted into DC power for certain applications.
In the event that normal AC power is not available, an emergency generator can provide AC power.
In the event that all AC power is not available, the electrical power system can invert DC power from
the batteries into AC power.
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DESCRIPTION - GENERATION OF ELECTRICAL POWER
AC GENERATORS
Ident.: DSC-24-10-20-00017751.0001001 / 21 MAR 16
Applicable to: ALL
ENGINE – DRIVEN GENERATORS
Two AC generators (GEN 1, GEN 2), one driven by each main engine through an integrated drive,
supply aircraft electrical power. Each generator can supply up to 90 KVA of three phase 115/200 V
400 Hz power.
Two Generators Control Units (GCU ) control the output of their respective generator. The main
functions of each GCU are :
‐ Control the frequency and voltage of the generator output.
‐ Protect the network by controlling the associated generator line contactor.
APU GENERATOR AND EXTERNAL POWER
A third generator (APU GEN ), driven directly by the APU and producing the same output as each
main engine generator, can replace either or both main engine generators at any time.
A ground power connector near the nosewheel allows ground power to be supplied to all busbars.
A Ground Power Control Unit (GPCU) :
‐ Protects the network by controlling the external power contactor, or
A Ground and Auxiliary Power Control Unit (GAPCU) :
‐ Regulates, via the APU Electronic Control Box, the frequency and voltage of the APU generator.
‐ Protects the network by controlling the external power contactor and the APU generator line
contactor.
EMERGENCY GENERATOR
The blue hydraulic circuit drives an emergency generator that automatically supplies emergency
AC power to the aircraft electrical system, if all main generators fail. This generator supplies 5 KVA
of three-phase 115 and 200 V 400 Hz power.
A Generator Control Unit (GCU) :
‐ Keeps the emergency generator at a constant speed,
‐ Controls the generator's output voltage,
‐ Protects the network by the controlling the emergency generator line contactor, and
‐ Controls the emergency generator start-up.
STATIC INVERTER
A static inverter transforms DC power from Battery 1 into one KVA of single-phase 115 V 400 Hz
AC power, which is then supplied to part of the AC essential bus. When the aircraft speed is above
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DESCRIPTION - GENERATION OF ELECTRICAL POWER
50 kt, the inverter is automatically activated, if only the batteries are supplying electrical power to
the aircraft, regardless of the BAT 1 and BAT 2 pushbutton positions.
When the aircraft speed is below 50 kt, the inverter is activated, if only the batteries are supplying
electrical power to the aircraft, and both BAT 1 and BAT 2 pushbuttons are on.
DC GENERATION
Ident.: DSC-24-10-20-00017752.0001001 / 21 MAR 16
Applicable to: ALL
TRANSFORMER RECTIFIERS (TRS)
Two main transformer rectifiers, TR 1 and TR 2, supply the aircraft's electrical system, with up to
200 A of DC current.
A third (identical) Transformer Rectifier, the ESS TR , can power the essential DC circuit from the
emergency generator, if the engine and APU generators all fail, or if TR 1 or TR 2 fails.
Each TR controls its contactor by internal logic.
A fourth Transformer Rectifier (TR Entertainment ) powers the DC Entertainment bus bar
dedicated to the In-Flight Entertainment system (IFE ) in order to take into account IFE needs.
BATTERIES
Two main batteries, each with a normal capacity of 23 Ah, are permanently connected to the two
hot buses.
Each battery has an associated Battery Charge Limiter (BCL).
The BCL monitors battery charging and controls its battery contactor.
CIRCUIT BREAKERS (C/BS)
Ident.: DSC-24-10-20-00000874.0002001 / 15 FEB 11
Applicable to: ALL
The aircraft has two types of C/Bs:
‐ Monitored (green): When out for more than 1 min, the C/B TRIPPED warning is triggered on the
ECAM.
‐ Non-monitored (black).
The Wing Tip Brake (WTB ) C/Bs have red caps on them to prevent them from being reset.
The C/B TRIPPED warning on the ECAM indicates the location of the affected C/B . The following
panels are monitored: OVHD PNL , L(R) ELEC BAY, REAR PNL J-M or N-R or S-V or W-Z.
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Note:
DESCRIPTION - GENERATION OF ELECTRICAL POWER
The flight crew can clear the ECAM C/B TRIPPED caution by pressing:
‐ The EMER CANC pb: When pressed, this pushbutton clears and inhibits the ECAM C/B
TRIPPED caution for the remainder of the flight, or
‐ The CLR pb: When pressed, this pushbutton only clears the ECAM C/B TRIPPED
caution. If the C/B remains pulled, any additional tripped circuit breakers on the same
panel will not be detected, and the ECAM will not trigger the caution. However, if the C/B
is pushed, any additional tripped circuit breakers will be detected, and the ECAM will
trigger the caution again.
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DESCRIPTION - GENERATION OF ELECTRICAL POWER
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DESCRIPTION - OPERATIONS
General
GENERAL
Ident.: DSC-24-10-30-10-00017759.0001001 / 21 MAR 16
Applicable to: ALL
GEN 1 and 2 when operating have priority over the APU generator and over external power.
External power has priority over the APU generator when the EXT PWR pb switch is ON.
The APU generator or external power can supply the entire network.
One engine generator can supply the entire network, except the DC BUS Entertainment.
The generators cannot be connected in parallel.
Note:
Two generators are needed to supply the DC BUS Entertainment , except on ground,
where the APU generator (if not overloaded) or the external power is sufficient.
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24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-24-10-30-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
Normal Configuration
IN FLIGHT
Ident.: DSC-24-10-30-20-00000876.0002001 / 09 OCT 12
Applicable to: ALL
Each engine-driven generator supplies its associated AC BUS (1 and 2) via its generator line
contactor (GLC 1 and GLC 2).
AC BUS 1 normally supplies the AC ESS BUS via a contactor.
TR 1 normally supplies DC BUS 1, DC BAT BUS, and DC ESS BUS.
TR 2 normally supplies DC BUS 2.
The two batteries are connected to the DC BAT BUS, if they need charging. When they are fully
charged, the battery charge limiter disconnects them.
ON GROUND
Ident.: DSC-24-10-30-20-00000877.0002001 / 22 MAY 12
Applicable to: ALL
Either the APU generator, or external power, may supply the complete system.
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FCOM
A to B →
DSC-24-10-30-20 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - OPERATIONS
On ground, when only ground services are required, external power can supply the AC and DC GND
/FLT BUSES directly without supplying the entire aircraft network.
Personnel select this configuration with the MAINT BUS switch in the forward entrance area.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-24-10-30-20 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DESCRIPTION - OPERATIONS
←B
DSC-24-10-30-20 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-24-10-30-20 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
Abnormal Configurations
FAILURE OF ONE ENGINE GENERATOR
Ident.: DSC-24-10-30-30-00017760.0002001 / 21 MAR 16
Applicable to: ALL
The system automatically replaces the failed generator, with the :
‐ APU GEN, if available, or
‐ Other engine generator.
Part of the galley load and the DC BUS Ent are automatically shed.
Note:
The Galley Load Automatic Shedding allows all the galley load to be automatically
shed.
FAILURE OF AC BUS 1
Ident.: DSC-24-10-30-30-00017761.0002001 / 21 MAR 16
Applicable to: ALL
‐ AC BUS 2 can supply AC ESS BUS, and ESS TR can supply DC ESS BUS, both via the AC ESS
FEED pb. This is done automatically with the AC ESS FEED Auto Switching .
‐ DC BUS 2 supplies DC BUS 1 and DC BAT BUS automatically after 5 s.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-24-10-30-30 P 1/10
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
FAILURE OF ONE TR
Ident.: DSC-24-10-30-30-00000880.0002001 / 21 MAR 16
Applicable to: ALL
The contactor of each TR opens automatically, in case of :
‐ Overheat
‐ Minimum current
The other TR automatically replaces the faulty one.
The ESS TR supplies the DC ESS BUS.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-24-10-30-30 P 2/10
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
FAILURE OF TR 1 AND TR 2
Ident.: DSC-24-10-30-30-00000881.0002001 / 09 OCT 12
Applicable to: ALL
If TR 1 and TR 2 are lost, DC BUS 1, DC BUS 2, and DC BAT BUS are lost. The DC ESS BUS is
supplied by the ESS TR.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
DSC-24-10-30-30 P 3/10
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - OPERATIONS
EMERGENCY GENERATION AFTER LOSS OF ALL MAIN GENERATORS
Ident.: DSC-24-10-30-30-00000882.0002001 / 21 MAR 16
Applicable to: ALL
If both AC BUS 1 and AC BUS 2 are lost and the aircraft speed is above 100 kt, the Ram Air Turbine
(RAT) extends automatically. This powers the blue hydraulic system, which drives the emergency
generator by means of a hydraulic motor. This generator supplies the AC ESS BUS, and the DC ESS
BUS via the ESS TR.
If the RAT stalls, or if the aircraft is on the ground with a speed below 100 kt, the emergency
generator has nothing to drive it. The emergency generation network automatically transfers to the
batteries and static inverter, and the system automatically sheds the AC SHED ESS and DC SHED
ESS buses.
When the aircraft is on ground :
‐ Below 100 kt, DC BAT BUS is automatically connected to the batteries.
‐ Below 50 kt, AC ESS BUS is automatically shed, leading to the loss of all display units.
Note:
1. During RAT extension and emergency generator coupling (about 8 s), the batteries
power the emergency generation network.
2. On ground, if only the batteries are powering the emergency generation network, APU
start is only available when the speed is below 100 kt.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E
DSC-24-10-30-30 P 4/10
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
EMER GEN RUNNING
Ident.: DSC-24-10-30-30-00000883.0002001 / 17 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
DSC-24-10-30-30 P 5/10
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
EMER GEN RUNNING (CONT'D)
Ident.: DSC-24-10-30-30-00000884.0002001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
DSC-24-10-30-30 P 6/10
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
FLIGHT WITH BATTERIES ONLY
Ident.: DSC-24-10-30-30-00017762.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
DSC-24-10-30-30 P 7/10
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - OPERATIONS
ON GROUND, BATTERIES ONLY (SPEED < 50 KT)
Ident.: DSC-24-10-30-30-00017763.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I
DSC-24-10-30-30 P 8/10
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
SMOKE CONFIGURATION
Ident.: DSC-24-10-30-30-00017764.0002001 / 21 MAR 16
Applicable to: ALL
In this configuration the main busbars are shed. The electrical distribution is the same as it is in
the emergency electrical configuration (loss of main generators), except the fact that in smoke
configuration the fuel pumps are connected upstream of the GEN 1 line connector.
The procedure sheds approximately 75 % of electrical equipment. All equipment that remains
powered is supplied via the circuit breakers on the overhead panel (except for equipment supplied by
hot buses).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J→
DSC-24-10-30-30 P 9/10
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
DESCRIPTION - OPERATIONS
ECAM ELEC page is identical to that for emergency generator running.
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FCOM
←J
DSC-24-10-30-30 P 10/10
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
Distribution Table
DISTRIBUTION TABLE
Ident.: DSC-24-10-30-40-00017765.0002001 / 21 MAR 16
Applicable to: ALL
AC AC AC AC AC TR 1 TR 2 ESS TR DC DC DC DC DC DC HOT HOT
BUS BUS ESS SHED STAT
TR Ent. BUS BUS BUS BAT ESS SHED BUS BUS
1
2 BUS ESS INV
1 2 Ent. BUS BUS ESS 1 2
(1)
(1)
NORM CONF GEN GEN GEN GEN 1
2 1
1
GEN GEN 1
2
GEN
ONE GEN
X
INOP
AVAIL-X- (1, 2
or APU )
EMER CONF • BEFORE
EMER GEN
AVAILABILITY
(about 8 s)
• EMER GEN RUNNING
GEN GEN X
X
GEN GEN GEN X X
X
-
ST
INV
BAT
1
ST
INV
BAT
1
-
EMEREMERGEN GEN
TR 1 FAULT
TR 2TRENTTR 1
GEN GEN GEN
2
2
1
TR 2TRENTTR 1
GEN GEN GEN
X
X
X
TR 1
GEN
1
TR 1
GEN
X
TR 1
GEN
1
TR 1
GEN
X
BAT BAT
1
2
BAT
2
-
BAT BAT
1
2
-
-
-
-
-
-
-
-
-
EMERGEN
-
-
-
-
GEN GEN GEN GEN 1
2 1
1
-
GEN GEN 2
1
TR 2 FAULT
GEN GEN GEN GEN 1
2 1
1
GEN 1
TR 1 + 2
FAULT
GEN GEN GEN GEN 1
2 1
1
-
(1)
-
GEN TR 1
2
GEN
1
GEN TR 1
X
GEN
X
-
TR 2 TR 2
GEN GEN
2
2
-
GEN 1
TR 1 TR 1
GEN GEN
1
1
-
GEN 1
-
-
-
BAT BAT
1
2
ESS ESS BAT
TR TR 1
EMEREMER
GEN GEN
TR 2 ESS ESS BAT
GEN TR TR 1
2 GEN GEN
1
1
TR 1 ESS ESS BAT
GEN TR TR 1
1 GEN GEN
1
1
ESS ESS BAT
TR TR 1
-GEN -GEN
1
1
BAT
2
BAT
2
BAT
2
BAT
2
Two generators are needed to supply the DC BUS Entertainment , except on ground, where
the APU generator (if not overloaded) or the external power is sufficient.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-24-10-30-40 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
DESCRIPTION - OPERATIONS
FLIGHT CREW
OPERATING MANUAL
ON GROUND
BAT. ONLY
Speed
>100 kt
AC AC AC AC AC TR 1 TR 2
BUS BUS ESS SHEDSTAT
1
2 BUS ESS INV
EMEREMERGEN GEN
Rat stall or
50 kt ≤ speed
≤ 100 kt
-
Speed < 50 kt -
-
ST INV
BAT
1
-
ST INV
BAT
1
ST INV
BAT
1
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
-
-
ESS TR DC DC DC DC DC DC HOT
TR Ent. BUS BUS BUS BAT ESS SHED BUS
1 2 Ent. BUS BUS ESS 1
EMERESS ESS BAT
GEN
TR TR 1
EMEREMER
GEN GEN
BAT BAT - BAT
1-2
2
1
-
←A
-
-
-
-
BAT BAT
1-2
2
-
HOT
BUS
2
BAT
2
BAT
2
BAT BAT
1
2
DSC-24-10-30-40 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-24-20-00017766.0004001 / 21 MAR 16
Applicable to: ALL
(1)
BAT 1(2) ind.
Shows battery voltage in white.
(2)
BAT 1(2) pb-sw
Controls the operation of the corresponding battery charge limiter.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-24-20 P 1/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
Auto
:
The battery charge limiter controls automatically the connection and the
disconnection of the corresponding battery to the DC BAT BUS (3 PP) by
closing and opening of the battery line contactor.
‐ The batteries are connected to the DC BAT BUS in the following cases:
• APU starting (MASTER SW pb-sw at ON and N < 95 %).
Note:
The connection is limited to 3 min when the emergency
generator is running.
• Battery voltage below 26.5 V (battery charge). The charging cycle ends
when battery charge current goes below 4 A.
▪ On ground, immediately
▪ In flight, after a time delay of 30 min.
• Loss of AC BUS 1 and 2 when below 100 kt (EMER GEN not
supplying).
‐ If AC BUS 1 and 2 are not energized and the EMER GEN is not supplying:
• Battery 1 supplies the AC STAT INV BUS, and, if speed is greater than
50 kt, the AC ESS BUS.
• Battery 2 supplies the DC ESS BUS.
Note:
In normal configuration the batteries are disconnected most of
the time.
Note:
A battery automatic cut-off logic prevents the batteries from
discharging completely when the aircraft is on the ground
(parking).
Automatic battery contactors open when:
‐ The aircraft is on the ground
‐ The BAT pb switches are at AUTO
‐ The main power supply (EXT PWR + GEN) is cut off
‐ Battery voltage is low.
The flight crew can reset the contactors by switching the BAT
pb-sw to OFF then to AUTO.
OFF
:
FAULT light :
The battery charge limiter is not operating: the battery line contactor is open.
OFF comes on white if the DC BAT BUS is supplied. Hot buses remain
supplied.
Comes on amber, accompanied by an ECAM caution, when the charging
current for the corresponding battery is outside limits.
In this case the battery contactor opens.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-24-20 P 2/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(3)
IDG 1(2) (Integrated Drive Generator) pb-sw (guarded)
CAUTION
1. Maintaining the IDG pb-sw during more than 3 s may damage the IDG
disconnection mechanism.
2. Disconnect the IDG only when the engine is running or windmilling. If not,
the IDG will be damaged when starting the engine.
The IDG switches are normally springloaded out.
Pressing this switch disconnects the IDG from its driveshaft: only maintenance personnel can
reconnect it.
FAULT : Lights up amber, and ECAM caution comes on, if:
light
‐ IDG oil outlet overheats (above 185 °C), or
‐ IDG oil pressure is low (inhibited at low engine speed: N2 below 14 %).
It extinguishes when the IDG is disconnected.
(4)
GEN 1 (2) pb-sw
ON
: The generator field is energized and the line contactor closes if electrical
parameters are normal.
OFF
: The generator field is de-energized and the line contactors opens.
The fault circuit is reset.
FAULT light : Lights up amber, and an ECAM caution comes on, if:
‐ The associated generator control unit (GCU) trips it.
Note:
If a differential fault trips the protection, reset action has no effect
after two attempts.
‐ Opening of the line contactor (except if the GEN pb-sw is selected OFF).
(5)
APU GEN pb-sw
ON
: The APU generator field is energized and the line contactor closes if parameters
are normal and the EXT PWR line contactor is open.
The bus tie contactor 1(2) closes automatically if GEN 1(2) is not operating.
OFF
: The generator field is de-energized and the line contactor opens. The fault circuit
is reset.
FAULT : Same as GEN 1 or 2 FAULT
light
The APU GEN FAULT light is inhibited when APU speed is too low or if the APU
GEN line contactor opens after EXT PWR or ENG GEN takes over.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-24-20 P 3/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(6)
BUS TIE pb
AUTO
:
OFF
(7)
:
The bus tie contactors (BTC s) automatically open or close to maintain
power supply to both AC BUS 1 and 2.
‐ One contactor is closed, when:
• One engine generator supplies the associated AC BUS, and
• The APU generator, or external power supplies the other side.
‐ Both contactors are closed during single-engine operation, or operation on
the APU generator, or external power supply.
Both bus tie contactors open.
AC ESS FEED pb
NORMAL
: The AC ESS BUS is supplied by AC BUS 1.
ALTN
: The AC ESS BUS is supplied by AC BUS 2. The light comes on when
manually selected.
Note:
FAULT light :
The amber light, and ECAM caution come on, when the AC ESS BUS is not
electrically-supplied.
Note:
(8)
With the AC ESS FEED Auto Switching , AC BUS 2 will
automatically supply AC ESS BUS when AC BUS 1 is lost.
In case of a total loss of the main generators, the AC ESS BUS is
automatically supplied by the emergency generator, or by the static
inverter, if the emergency generator is not available.
GALLEY pb or GALY & CAB pb
AUTO
: Main galley, secondary galley, in-seat power supply and IFE
system (prerecorded announcement, telephone system, video/airshow,
music…), are supplied.
The main galley, the in-seat power supply and the IFE systems are
automatically shed:
‐ In flight: When only one generator is operating.
‐ On ground: When only one engine generator is operating. (All galleys are
available when the APU GEN or EXT PWR is supplying power.)
Note:
With the Galley Load Automatic Shedding the secondary
galley is also automatically shed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-24-20 P 4/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OFF
:
FAULT light :
(9)
The main galley, secondary galley, in-seat power supply and IFE
system (prerecorded announcement, telephone system, video/airshow,
music ....) are not supplied.
The electrical supply of the heating floor panels is shed.
The amber light, and ECAM caution come on, when the load on any
generator is more than 100 % of rated output.
EXT PWR pb
AVAIL light comes on green, if:
‐ External power is plugged in, and
‐ External power parameters are normal.
When pressed:
‐ If the AVAIL light was on:
• The external power line contactor closes
• The AVAIL light goes off
• The ON light comes on blue.
‐ If the ON light was on:
• The external power line contactor opens
• The ON light goes off
• The AVAIL light comes on.
Note:
1. External power has priority over the APU generator. The engine generators have
priority over external power.
2. The ON light stays on, even when the engine generators supply the aircraft.
(10) COMMERCIAL pb
ON : All aircraft commercial electrical loads are supplied:
‐ Cabin and cargo lights
‐ Water and toilet system
‐ Drain mast ice protection
‐ Galley
‐ Passenger's entertainment
‐ Semi-automatic cargo loading
OFF : Switches off all aircraft commercial electrical loads.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-24-20 P 5/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL (CONT'D)
Ident.: DSC-24-20-00017778.0002001 / 21 MAR 17
Applicable to: ALL
(1)
MAN ON pb (guarded)
AUTO : When the following conditions are met:
‐ AC BUS 1 is not electrically supplied, and
‐ AC BUS 2 is not electrically supplied, and
‐ Aircraft speed is greater than 100 kt.
• The RAT extends, and
• The blue hydraulic system drives the emergency generator.
Pressed :
(2)
As soon as the emergency generator electrical parameters are within tolerance
the emergency generator is connected to the aircraft network.
This selects manual RAT extension.
Emergency generator coupling occurs 3 s after the RAT supplies the emergency
generator.
FAULT light
This light comes on red if the emergency generator is not supplying power when AC BUS 1 and
AC BUS 2 are not powered.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
DSC-24-20 P 6/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(3)
CONTROLS AND INDICATORS
EMER GEN TEST pb (guarded)
Pressed and held:
‐ If AC NORMAL BUSES are supplied:
• The EMER GEN is driven hydraulically if the blue electric pump is running.
The AC ESS BUS and the DC ESS BUS are connected to the emergency generator.
(The DC ESS SHED and AC ESS SHED buses are not powered.)
• ECAM displays the ELEC page automatically (only on the ground).
‐ If only the batteries supply the aircraft:
• The static inverter powers the AC ESS BUS.
(4)
GEN 1 LINE pb-sw
OFF
: GEN 1 line contactor opens.
The AC BUS 1 channel is supplied from GEN 2 through bus tie contactors. This is
used for smoked drill.
SMOKE : Refer to DSC-26-30-20 GEN 1 LINE pb-sw.
light
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-24-20 P 7/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
EXTERNAL POWER PANEL
Ident.: DSC-24-20-00000891.0001001 / 21 MAR 16
Applicable to: ALL
(1)
EXT PWR NOT IN USE
This white light comes on to inform ground personnel that the ground power unit is not
supplying the aircraft network and can be removed.
(2)
EXT PWR AVAIL
This amber light comes on to indicate that external power is available and the voltage is
correct.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-24-20 P 8/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
FORWARD CABIN
Ident.: DSC-24-20-00000892.0001001 / 22 MAY 12
Applicable to: ALL
MAINT BUS SW:
This switch allows personnel to energize electrical circuits for ground servicing without energizing
the entire aircraft electrical system.
ON : The switch latches magnetically if external power is connected and normal (AVAIL light
on).
The AC and DC GND /FLT buses have power and the following loads can be energized:
‐ passenger compartment lighting
‐ galley lighting
‐ entrance area lights
‐ lavatory lighting and service
‐ vacuum cleaner sockets
‐ flight compartment service outlets
‐ hydraulic pump (yellow system)
‐ flight compartment flood lighting
‐ fuel quantity indications
‐ refueling
‐ cargo hold lighting
‐ main and nose landing gear compartment lighting
‐ belly fairing panel service outlets
‐ ground call
‐ equipment compartment lights and service outlets
‐ navigation lights.
OFF :
The switch trips when the external source is removed.
The AC and DC GND /FLT buses are connected to AC BUS 2 and DC BUS 2.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
DSC-24-20 P 9/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
ECAM ELEC PAGE
Ident.: DSC-24-20-00017780.0002001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
DSC-24-20 P 10/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
CONTROLS AND INDICATORS
Battery indications
‐ BAT pb-sw at OFF:
Legend is in white.
‐ BAT pb-sw at Auto:
(A)
Legend is normally white, but becomes amber:
‐ when voltage and current indications change to amber, or
‐ in case of a BAT FAULT alert.
(B) Battery voltage is normally green, but becomes amber if V > 31 V or V < 25 V.
(C) Battery current is normally green, but becomes amber if discharge current > 5 A.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
DSC-24-20 P 11/18
22 MAR 17
AIRCRAFT SYSTEMS
ELECTRICAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
(2)
Battery charge/discharge indication
(3)
DC BAT indication
It is normally in green. It becomes amber, if DC BAT voltage ≤ 25 V.
(4)
Bus bar indication
The bus bar indication is normally green. It becomes amber when the corresponding bus bar is
not powered.
SHED appears in amber, when AC or DC SHED ESS BUS is shed.
(5)
TR 1 (2) indication
(A) Normally white, this legend becomes amber when legends B and C do.
(B) The TR voltage is normally in green. It becomes amber, if V > 31 V, or V < 25 V.
(C) The TR current is normally in green. It becomes amber, when the TR current ≤ 5 A.
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FLIGHT CREW
OPERATING MANUAL
(6)
CONTROLS AND INDICATORS
ESS TR indication
This legend follows the logic of the above-noted TR 1 (2) legend.
The voltage and current are not displayed, when the essential TR contactor is open.
(7)
EMER GEN indication
(A) This legend is normally in white. It becomes amber when either the voltage or frequency
legend becomes amber.
(B)
This legend is normally in green. It becomes amber, if:
‐ V > 120 V or
‐ V < 110 V.
(C)
This legend is normally in green. It becomes amber, if:
‐ F > 410 Hz or
‐ F < 390 Hz .
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
Voltage and frequency indications are not displayed, when the EMER GEN line contactor
is open.
(8)
GEN 1(2) indications
‐ GEN pb-sw is OFF:
GEN is amber.
OFF indication is white
1 or 2 indication is white if the associated engine is running, amber if it is not.
‐ GEN pb-sw is ON.
(A) GEN 1 or GEN 2, normally white, becomes amber if any of the following legends
become amber.
(B) The load legend, normally green, becomes amber if load > 100 %.
(C) The voltage legend, normally green, becomes amber if V > 120 V or V < 110 V.
(D) The frequency legend, normally green, becomes amber if F > 410 Hz or F < 390 Hz.
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FLIGHT CREW
OPERATING MANUAL
(9)
CONTROLS AND INDICATORS
APU GEN indications
‐ When the APU MASTER sw is OFF this legend is white regardless of the position of the
APU GEN pb-sw.
‐ When the APU MASTER sw is ON, and the APU GEN pb-sw is OFF:
The APU GEN legend is amber.
The OFF legend is white.
‐ When the APU MASTER sw is ON and the APU GEN pb-sw is ON:
The indications are the same as for GEN 1 (2).
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FLIGHT CREW
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CONTROLS AND INDICATORS
(10) EXT PWR indications
‐ External power is not available.
‐ When external power is available:
(A) This legend is normally white, but becomes amber, if either of the following legends
turns amber.
(B) This legend is normally green, but becomes amber, if V > 120 V or if V < 110 V.
(C) This legend is normally green, but becomes amber, if F > 410 Hz or if F < 390 Hz.
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CONTROLS AND INDICATORS
‐ This legend appears during the static inverter test, and when pressing the ELEC pb on the
ECAM control panel while ESS BUSES are supplied by the batteries. It is normally green,
but becomes amber, if:
V < 110 V or V> 120 V.
F < 390 Hz or F > 410 Hz.
(11) IDG indications
(A) IDG1 (2) legend
The IDG legend is normally white, but becomes amber, if:
• Oil outlet temperature > 185 °C.
• Oil pressure gets too low.
• IDG becomes disconnected.
The 1 or 2 is white if the corresponding engine is running, amber if it is not and the
FADEC is powered.
(B) DISC/LO PR indication
The DISC legend appears in amber, when the IDG is disconnected.
LO PR appears in amber, when IDG low pressure is detected and the associated engine
is running.
(C) Oil outlet temperature
This legend is normally in green, but appears amber, if T > 185 °C.
It flashes, if 147 °C < T < 185 °C (advisory).
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CONTROLS AND INDICATORS
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OPERATING MANUAL
(12) GALLEY SHED indication
This legend appears in white when:
‐ The GALLEY pb-sw is OFF, or
‐ The main galleys are shed, meaning:
• In flight, only one generator is operating.
• On ground, the aircraft is being supplied by one engine generator only.
The legend is not displayed, when the aircraft is in its normal configuration.
(13) RISE indication
This number, displayed in green, is the difference between the temperature at the IDG inlet and
that at the IDG outlet.
MEMO DISPLAY
Ident.: DSC-24-20-00016808.0001001 / 21 MAR 16
Applicable to: ALL
EMER GEN
:
This memo appears in green, when the emergency generator is running.
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PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-25-10 Flight Deck
DSC-25-10-10 General
General.....................................................................................................................................................................A
Principles For Pushbuttons With Integrated Indications..........................................................................................B
General Arrangement.............................................................................................................................................. C
DSC-25-10-20 Cockpit Plan
General.....................................................................................................................................................................A
Right Rear Corner................................................................................................................................................... B
Left Rear Corner......................................................................................................................................................C
DSC-25-10-30 Seats
Pilot Seats................................................................................................................................................................A
Pilot Seat Mechanical Adjustment...........................................................................................................................B
Pilot Seat Electrical Adjustment .....................................................................................................................C
Head Rest Adjustment ................................................................................................................................... D
Armrest Adjustment................................................................................................................................................. E
Observer Seat.......................................................................................................................................................... F
Observer Seat Adjustment...................................................................................................................................... G
Armrest.....................................................................................................................................................................H
DSC-25-10-40 Main Instrument Panels
Main Instrument Panel - Captain Side.................................................................................................................... A
Main Instrument Panel - First Officer Side..............................................................................................................B
DSC-25-10-50 Pedestal
Pedestal................................................................................................................................................................... A
DSC-25-10-60 Overhead Panel
Overhead Panel....................................................................................................................................................... A
DSC-25-10-70 C/B Panels
C/B Panels............................................................................................................................................................... A
DSC-25-10-80 Foot Warmer (If Installed)
General.....................................................................................................................................................................A
Controls.................................................................................................................................................................... B
DSC-25-20 Emergency Equipment
Flashlights .......................................................................................................................................................A
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PRELIMINARY PAGES - TABLE OF CONTENTS
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FLIGHT DECK - GENERAL
GENERAL
Ident.: DSC-25-10-10-00020853.0001001 / 17 MAR 17
Applicable to: ALL
The aircraft and system controls, required for piloting the aircraft, are arranged in such a way that the
crew faces forward and all crewmembers can monitor instruments and systems.
The designers concentrated system controls on the overhead panel by making extensive use of
pushbuttons, directly installed in the system synoptic.
Note:
This chapter describes the panels and equipment of the basic aircraft configuration, and
may not correspond to the customized configuration of a specific aircraft.
For more information on the installed equipment or panels, refer to the relevant chapter's
system description.
PRINCIPLES FOR PUSHBUTTONS WITH INTEGRATED INDICATIONS
Ident.: DSC-25-10-10-00000983.0001001 / 21 MAR 16
Applicable to: ALL
Whenever possible, pushbuttons used for corrective actions, have integrated status and failure
indications.
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FLIGHT DECK - GENERAL
The pushbutton positions, and their illuminated indications, follow the "lights out” principle.
‐ While corresponding to particular aircraft configurations, indications also have the following color
codes :
• Warnings
RED
: A failure requiring immediate action.
• Cautions
AMBER : A failure, of which the flight crew should be aware, but does not call for immediate
action.
• Indications
GREEN : For normal system operation.
BLUE : For normal operation of a system used temporarily
WHITE : ‐ For an abnormal pushbutton position.
‐ For a test result or maintenance information.
When the aircraft is in a normal configuration, only green lights can be permanently lit, whereas
blue lights can be intermittently.
‐ Pushbutton positions :
POSITION
Pressed In
Released Out
Note:
BASIC FUNCTION
ON, AUTO, OVRD, OPEN
OFF, MAN , ALTN, SHUT
1. Certain pushbutton lights have two dots, indicating that the corresponding part of the
pushbutton is not used.
2. Certain pushbuttons do not remain pressed in. These are referred to as “Momentary
Action” pushbuttons.
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FLIGHT CREW
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GENERAL ARRANGEMENT
Ident.: DSC-25-10-10-00018419.0001001 / 17 MAR 17
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FLIGHT DECK - GENERAL
Applicable to: ALL
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←C
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FLIGHT DECK - COCKPIT PLAN
GENERAL
Ident.: DSC-25-10-20-00017002.0001001 / 17 MAR 17
Applicable to: ALL
The cockpit can accommodate two crewmembers, plus a third and fourth occupant .
The two pilot seats are mounted on columns.
The third and fourth occupant seats are folding seats.
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FLIGHT DECK - COCKPIT PLAN
FLIGHT CREW
OPERATING MANUAL
RIGHT REAR CORNER
Ident.: DSC-25-10-20-00000986.0001001 / 06 DEC 16
Applicable to: ALL
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B
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FLIGHT DECK - COCKPIT PLAN
FLIGHT CREW
OPERATING MANUAL
LEFT REAR CORNER
Ident.: DSC-25-10-20-00018428.0001001 / 17 MAR 17
Applicable to: ALL
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C
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FLIGHT DECK - COCKPIT PLAN
FLIGHT CREW
OPERATING MANUAL
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FLIGHT DECK - SEATS
FLIGHT CREW
OPERATING MANUAL
PILOT SEATS
Ident.: DSC-25-10-30-00018429.0002001 / 17 MAR 17
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FLIGHT DECK - SEATS
FLIGHT CREW
OPERATING MANUAL
Applicable to: ALL
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←A
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FLIGHT CREW
OPERATING MANUAL
PILOT SEAT MECHANICAL ADJUSTMENT
Ident.: DSC-25-10-30-00000989.0001001 / 22 MAR 17
Applicable to: ALL
To adjust a seat mechanically, the occupant must lift the appropriate control handle. This unlocks the
seat so that it may be moved. Releasing the control handle returns it to springloaded locked position.
On electrically-powered seats, the mechanical adjustment is a backup: The seat should be adjusted
electrically.
PILOT SEAT ELECTRICAL ADJUSTMENT
Ident.: DSC-25-10-30-00018405.0001001 / 17 MAR 17
Applicable to: ALL
To adjust a seat electrically, the occupant must press the appropriate control switch in the desired
direction, and release it when the seat reaches the desired position. The switch then returns to the
springloaded neutral position.
To adjust the vertical position of the lumbar cushion, the occupant must:
‐ Pull the control out to the unlocked position
‐ Turn the control to adjust the position of the cushion
‐ Push the control into the locked position.
HEAD REST ADJUSTMENT
Ident.: DSC-25-10-30-00018406.0001001 / 17 MAR 17
Applicable to: ALL
To adjust the headrest in inclination, the occupant presses the inclination control button, and
releases it to lock the position.
To control the height of the headrest, the occupant must push it horizontally, adjust the height, and
release it to lock the position.
ARMREST ADJUSTMENT
Ident.: DSC-25-10-30-00000993.0001001 / 21 MAR 17
Applicable to: ALL
To adjust the inboard armrest, the occupant must turn the knurled knob, located on the bottom
surface of the armrest.
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B to E
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FLIGHT CREW
OPERATING MANUAL
OBSERVER SEAT
Ident.: DSC-25-10-30-00018430.0001001 / 17 MAR 17
Applicable to: ALL
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F
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FLIGHT CREW
OPERATING MANUAL
OBSERVER SEAT ADJUSTMENT
Ident.: DSC-25-10-30-00000995.0001001 / 21 MAR 17
Applicable to: ALL
This seat has three positions :
‐ Normal : Centered on aircraft axis.
‐ Intermediate : Clear of the cockpit entrance.
‐ Stowed : Seat vertical and headrest folded back. The seat is usable in this position, and does not
impede access to the documents and equipment on the right side of the cockpit.
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G
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FLIGHT CREW
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ARMREST
Ident.: DSC-25-10-30-00018431.0001001 / 17 MAR 17
Applicable to: ALL
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FLIGHT DECK - SEATS
FLIGHT CREW
OPERATING MANUAL
The position of the armrest is adjustable as follows:
A. Height adjustment
B. Pitch adjustment
The armrest also has a memory display (C) that shows pitch and height.
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FLIGHT DECK - SEATS
FLIGHT CREW
OPERATING MANUAL
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FLIGHT DECK - MAIN INSTRUMENT PANELS
MAIN INSTRUMENT PANEL - CAPTAIN SIDE
Ident.: DSC-25-10-40-00020851.0001001 / 21 MAR 17
Applicable to: ALL
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A
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FLIGHT CREW
OPERATING MANUAL
FLIGHT DECK - MAIN INSTRUMENT PANELS
MAIN INSTRUMENT PANEL - FIRST OFFICER SIDE
Ident.: DSC-25-10-40-00020852.0001001 / 21 MAR 17
Applicable to: ALL
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B
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EQUIPMENT
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FLIGHT DECK - PEDESTAL
FLIGHT CREW
OPERATING MANUAL
PEDESTAL
Ident.: DSC-25-10-50-00020854.0001001 / 17 MAR 17
Applicable to: ALL
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A
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FLIGHT CREW
OPERATING MANUAL
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FLIGHT DECK - OVERHEAD PANEL
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-25-10-60-00020855.0001001 / 17 MAR 17
Applicable to: ALL
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GLG A318/A319/A320/A321 For A/C: HC-CRU
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FLIGHT DECK - OVERHEAD PANEL
←A
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FLIGHT DECK - C/B PANELS
C/B PANELS
Ident.: DSC-25-10-70-00018436.0001001 / 17 MAR 17
Applicable to: ALL
OVERHEAD PANEL
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FLIGHT DECK - C/B PANELS
RIGHT REAR PANEL
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←A
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FLIGHT DECK - FOOT WARMER (IF INSTALLED)
GENERAL
Ident.: DSC-25-10-80-00017009.0001001 / 17 MAR 17
Applicable to: ALL
The foot warmer system has a heating panel attached to each pedal. The temperature of the
panels is about 20 °C (68 °F).
CONTROLS
Ident.: DSC-25-10-80-00017008.0001001 / 17 MAR 17
Applicable to: ALL
The Foot Warmer ON/OFF control switch is located on the main instrument panel, on the
captain's and first officer's side.
FOOT WARMER sw
Operation of the associated heating panel on captain's pedals or first officer's pedals.
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A to B
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FLIGHT DECK - FOOT WARMER (IF INSTALLED)
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EMERGENCY EQUIPMENT
FLIGHT CREW
OPERATING MANUAL
FLASHLIGHTS
Ident.: DSC-25-20-00018439.0001001 / 17 MAR 17
Applicable to: ALL
Emergency flashlights are installed in a bracket at each lateral console.
Each flashlight comes on automatically when it is removed from its bracket.
A push-to-test button and its associated red/green LED indicate the battery status.
(1)
Push-to-Test Button
Pressing this button indicates the battery status.
(2)
Charge Indicator (LED)
When the Push-to-Test button is pressed:
‐ If the LED comes on in green (flashes green one time), the flashlight battery is charged
‐ If the LED comes on in red (flashes red one time), the battery is low, and should be changed
‐ If the LED does not come on, the flashlight system has a failure and must be repaired.
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A
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EQUIPMENT
A318/A319/A320/A321
EMERGENCY EQUIPMENT
FLIGHT CREW
OPERATING MANUAL
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FIRE PROTECTION
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PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-26-10 General
Description............................................................................................................................................................... A
DSC-26-20 Engines and APU
DSC-26-20-10 System Description
Fire Detection...........................................................................................................................................................A
Extinguishing............................................................................................................................................................ B
Fire Detection and Detection Fault Logic............................................................................................................... C
DSC-26-20-20 Controls and Indicators
FIRE Panel...............................................................................................................................................................A
ENG MASTER Panel...............................................................................................................................................B
EXTERNAL POWER Panel.....................................................................................................................................C
MAINTENANCE Panel............................................................................................................................................ D
DSC-26-30 Avionics Bay
DSC-26-30-10 System Description
Smoke Detection......................................................................................................................................................A
DSC-26-30-20 Controls and Indicators
EMER ELEC PWR Panel........................................................................................................................................A
VENTILATION Panel............................................................................................................................................... B
DSC-26-40 Lavatory
DSC-26-40-10 System Description
Smoke Detection......................................................................................................................................................A
Wastebin Fire Extinguishing.................................................................................................................................... B
DSC-26-50 Cargo Compartments
DSC-26-50-10 System Description
Smoke Detection......................................................................................................................................................A
Fire Extinguishing.................................................................................................................................................... B
DSC-26-50-20 Controls and Indicators
CARGO SMOKE Panel........................................................................................................................................... A
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FIRE PROTECTION
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PRELIMINARY PAGES - TABLE OF CONTENTS
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FIRE PROTECTION
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-26-10-00021387.0006001 / 17 MAR 17
Applicable to: ALL
The fire and smoke protection system includes:
‐ Fire and overheat detection for the engines and APU
‐ Smoke detection for the cargo compartments, the lavatories, and the avionics bay
‐ Fire extinguishing for the cargo compartments, the engines, the APU, and the lavatories.
In addition, the aircraft includes portable fire extinguishers in the cockpit and in the cabin areas.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A
DSC-26-10 P 1/2
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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22 MAR 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ENGINES AND APU - SYSTEM DESCRIPTION
FIRE DETECTION
Ident.: DSC-26-20-10-00021393.0001001 / 17 MAR 17
Applicable to: ALL
The engines and the APU each have a fire and overheat detection system consisting of:
‐ Two identical detection loops (A and B) mounted in parallel
‐ A Fire Detection Unit (FDU).
The fire detection loops consist of:
‐ Three or four (as installed) engine fire sensing elements, in the pylon nacelle, in the engine core,
and in the engine fan section
‐ One fire sensing element in the APU compartment.
When a sensing element is subjected to heat, it sends a signal to the FDU. As soon as loops A and B
detect temperature above a preset level, the fire warning system is triggered.
A fault in one loop (break or loss of electrical supply) does not affect the warning system and the
unaffected loop still protects the aircraft.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-26-20-10 P 1/2
05 SEP 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ENGINES AND APU - SYSTEM DESCRIPTION
EXTINGUISHING
Ident.: DSC-26-20-10-00021395.0001001 / 04 JUL 17
Applicable to: ALL
ENGINES
Each engine has two fire extinguisher bottles, with electrically-operated squibs to discharge their
agents. Each squib has a dual electric supply. The flight crew controls the discharge of the fire
extinguisher bottles from the FIRE panel in the cockpit.
APU
The APU has one fire extinguisher bottle, with two electrically-operated squibs to discharge its
agent. The flight crew controls the discharge of the fire extinguisher bottle from the FIRE panel in
the cockpit. When an APU fire is detected on the ground, the APU automatically shuts down, and
the extinguisher bottle discharges automatically.
FIRE DETECTION AND DETECTION FAULT LOGIC
Ident.: DSC-26-20-10-00021394.0001001 / 17 MAR 17
Applicable to: ALL
Fire detection units process all the warnings and cautions originating in the sensing elements.
‐ A fire warning appears, if:
• Both loops A and B send a fire signal, or
• One loop sends a fire signal and the other one is failed, or
• Breaks occur in both loops within 5 s of each other (flame effect), or
• A test is performed on the FIRE panel
‐ A loop-fault caution appears, if:
• One loop is failed, or
• Both loops are failed, or
• The FDU fails.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B to C
DSC-26-20-10 P 2/2
05 SEP 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ENGINES AND APU - CONTROLS AND INDICATORS
FIRE PANEL
Applicable to: ALL
Ident.: DSC-26-20-20-10-00021396.0002001 / 17 MAR 17
Ident.: DSC-26-20-20-10-00021415.0001001 / 17 MAR 17
ENG 1(2) FIRE PB
The pushbutton normal position is in, and guarded. When the flight crew pushes it, the pushbutton
is released and sends an electrical signal that performs the following for the corresponding engine:
‐ Silences the aural fire warning
‐ Arms the fire extinguisher squibs
‐ Closes the low-pressure fuel valve
‐ Closes the hydraulic fire shut off valve
‐ Closes the engine bleed valve
‐ Closes the pack flow control valve
‐ Cuts off the FADEC power supply
‐ Deactivates the IDG.
The red lights come on, regardless of the pushbutton position, whenever the fire warning for the
corresponding engine is activated.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-26-20-20 P 1/6
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ENGINES AND APU - CONTROLS AND INDICATORS
Ident.: DSC-26-20-20-10-00021420.0001001 / 17 MAR 17
AGENT 1(2) PB-SW
Both AGENT pushbutton-switches of an affected engine become active when the flight crew
releases the ENG 1(2) FIRE pb.
A brief push on the pushbutton-switch discharges the corresponding fire agent.
‐ “SQUIB” comes on white when the flight crew releases the ENG 1(2) FIRE pb to help the flight
crew identify the AGENT pb-sw to be activated.
‐ “DISCH” comes on amber when the corresponding fire extinguisher bottle has lost pressure.
Ident.: DSC-26-20-20-10-00021421.0001001 / 17 MAR 17
ENG 1(2) FIRE TEST PB
This pushbutton tests the operation of the fire detection and extinguishing system for ENG 1(2).
When pressed:
‐ A continuous repetitive chime (CRC) sounds
‐ The MASTER WARNING lights flash
‐ ENG FIRE warning appears on ECAM.
‐ On the FIRE panel:
• The ENG 1(2) FIRE pb lights up red
• The SQUIB lights come on white if discharge supplies are available
• The DISCH lights come on amber.
‐ On the ENG MASTER panel (pedestal):
• The FIRE lights come on red.
Ident.: DSC-26-20-20-10-00021423.0001001 / 17 MAR 17
APU FIRE PB
The pushbutton normal position is in, and guarded. When the flight crew pushes it, the pushbutton
is released and sends an electrical signal that performs the following for the APU:
‐ Shuts down the APU
‐ Silences the aural warning
‐ Arms the squib on the APU fire extinguisher
‐ Closes the low-pressure fuel valve
‐ Shuts off the APU fuel pump
‐ Closes the APU bleed valve and X bleed valve and deactivates the APU generator.
The red lights come on, regardless of the pushbutton position, whenever an APU fire warning is
activated.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-26-20-20 P 2/6
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ENGINES AND APU - CONTROLS AND INDICATORS
Ident.: DSC-26-20-20-10-00021424.0001001 / 17 MAR 17
AGENT PB-SW
The APU AGENT pb-sw becomes active when the flight crew releases the APU FIRE pb.
A brief push on the pushbutton-switch discharges the corresponding fire agent.
‐ “SQUIB” comes on white when the pilot releases the APU FIRE pb.
‐ “DISCH” comes on amber when the fire extinguisher bottle has lost pressure.
Note:
A red disk, which is outside at the rear of the fuselage, signals that the agent is not
discharged overboard due to bottle overpressure.
Ident.: DSC-26-20-20-10-00021425.0001001 / 17 MAR 17
APU FIRE TEST PB
This pushbutton tests the operation of the APU fire detection and extinguishing system.
When pressed:
‐ A continuous repetitive chime (CRC) sounds
‐ The MASTER WARNING lights flash
‐ APU FIRE warning appears on ECAM.
‐ On the FIRE panel:
• The APU FIRE pb lights up red
• The SQUIB light comes on white if discharge supplies are available
• The DISCH light comes on amber.
Note:
The automatic shutdown of the APU on the ground does not occur when the flight crew
performs this test.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-26-20-20 P 3/6
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ENGINES AND APU - CONTROLS AND INDICATORS
ENG MASTER PANEL
Applicable to: ALL
Ident.: DSC-26-20-20-20-00021427.0001001 / 17 MAR 17
Ident.: DSC-26-20-20-20-00021428.0001001 / 17 MAR 17
ENG 1(2) FIRE LIGHT
This light identifies the engine to be shutdown in the case of fire.
The light comes on red when an engine fire warning is triggered.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
DSC-26-20-20 P 4/6
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ENGINES AND APU - CONTROLS AND INDICATORS
EXTERNAL POWER PANEL
Applicable to: ALL
Ident.: DSC-26-20-20-30-00021429.0001001 / 17 MAR 17
Ident.: DSC-26-20-20-30-00021430.0001001 / 17 MAR 17
APU FIRE LIGHT
The red APU FIRE light comes on and an external warning horn sounds when the system detects
an APU fire.
The APU fire extinguisher discharges automatically 3 s after the appearance of the fire warning.
The light goes out when the fire has been extinguished.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
DSC-26-20-20 P 5/6
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ENGINES AND APU - CONTROLS AND INDICATORS
Ident.: DSC-26-20-20-30-00021431.0001001 / 17 MAR 17
APU SHUT OFF PB
This pushbutton is used for manual APU emergency shutdown, if an emergency situation is
detected on ground by the ground crew. When this pushbutton is pressed, the APU low pressure
fuel shutoff valve closes, and the ECB receives a signal that starts the shutdown sequence. The
shutdown sequence is the same as the APU automatic shutdown sequence, except that there is
no cool down cycle. Pressing this pushbutton also silences the external warning horn.
MAINTENANCE PANEL
Applicable to: ALL
Ident.: DSC-26-20-20-40-00021432.0001001 / 17 MAR 17
Ident.: DSC-26-20-20-40-00021435.0001001 / 17 MAR 17
TEST PB-SW
When pressed, tests the following APU circuits:
‐ Fire warning
‐ Auto extinguishing
‐ Shutdown.
During the test sequence, the APU MASTER sw must be ON.
If all circuits are operating correctly, the OK light comes on.
Note:
If the APU was running, it shuts down.
Ident.: DSC-26-20-20-40-00021436.0001001 / 17 MAR 17
RESET PB
When pressed, resets the test circuit.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
DSC-26-20-20 P 6/6
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
AVIONICS BAY - SYSTEM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
SMOKE DETECTION
Ident.: DSC-26-30-10-00021401.0001001 / 17 MAR 17
Applicable to: ALL
The air extraction duct of the avionics ventilation system has one smoke detector.
When smoke is detected for more than 5 s:
‐ The Single Chime (SC) sounds
‐ The MASTER CAUTION lights flash
‐ The ECAM AVIONICS SMOKE alert triggers
‐ On the EMER ELEC PWR panel, the SMOKE light of the GEN 1 LINE pb-sw comes on
‐ On the VENTILATION panel, the FAULT lights of the BLOWER pb-sw and the EXTRACT pb-sw
come on.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-26-30-10 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AVIONICS BAY - SYSTEM DESCRIPTION
←A
DSC-26-30-10 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
AVIONICS BAY - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
EMER ELEC PWR PANEL
Applicable to: ALL
Ident.: DSC-26-30-20-A-00021439.0001001 / 17 MAR 17
Ident.: DSC-26-30-20-A-00021440.0001001 / 17 MAR 17
GEN 1 LINE PB-SW
SMOKE light on
:
The amber light comes on when smoke is detected in the avionics
ventilation duct.
VENTILATION PANEL
Applicable to: ALL
Ident.: DSC-26-30-20-B-00021402.0001001 / 17 MAR 17
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-26-30-20 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
AVIONICS BAY - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-26-30-20-B-00021437.0001001 / 17 MAR 17
BLOWER PB-SW
FAULT light on
:
The amber light comes on when smoke is detected in the avionics
ventilation duct.
Ident.: DSC-26-30-20-B-00021438.0001001 / 17 MAR 17
EXTRACT PB-SW
FAULT light on
:
The amber light comes on when smoke is detected in the avionics
ventilation duct.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-26-30-20 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
LAVATORY - SYSTEM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
SMOKE DETECTION
Ident.: DSC-26-40-10-00021441.0001001 / 17 MAR 17
Applicable to: ALL
The lavatory smoke detection system consists of:
‐ One smoke detector, in the air extraction duct of the lavatory
‐ A double channel Smoke Detection Control Unit (SDCU) or a Cabin Intercommunication Data
Systems (CIDS) with a Smoke Detection Function (SDF) that triggers the applicable alerts
(cockpit and cabin).
In the case of smoke in a lavatory, the detector sends a signal to the SDCU or CIDS , which
transmits it to the Flight Warning Computer (FWC) for warning in the cockpit and in the cabin.
WASTEBIN FIRE EXTINGUISHING
Ident.: DSC-26-40-10-00001034.0001001 / 21 MAR 16
Applicable to: ALL
Each lavatory wastebin has an automatic fire extinguishing system.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-26-40-10 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
LAVATORY - SYSTEM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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22 MAR 17
AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CARGO COMPARTMENTS - SYSTEM DESCRIPTION
SMOKE DETECTION
Ident.: DSC-26-50-10-00021442.0003001 / 17 MAR 17
Applicable to: ALL
The forward and aft cargo compartments smoke detection system consists of:
‐ Two smoke detectors that are in the forward cargo compartment ceiling panel cavities. Each
detector is linked to one of the two detection loops (dual loop principle).
‐ Four smoke detectors that are in the aft cargo compartment ceiling panel cavities. Each detector is
linked to one of the two detection loops (dual loop principle).
‐ A Smoke Detection Control Unit (SDCU) with two identical channels, or a Cabin
Intercommunication Data Systems (CIDS ) with a Smoke Detection Function (SDF) , that
receives signals from the smoke detectors, and transmits it to the ECAM.
Smoke in one cavity activates the cargo smoke warning if:
‐ Both smoke detectors detect smoke, or
‐ One smoke detector detects smoke and the other is inoperative.
Cargo isolation valves close automatically, and the extraction fan stops when the cargo
smoke warning is activated.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-26-50-10 P 1/4
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CARGO COMPARTMENTS - SYSTEM DESCRIPTION
FIRE EXTINGUISHING
Ident.: DSC-26-50-10-00021443.0005001 / 17 MAR 17
Applicable to: ALL
A fire extinguishing system protects the forward and aft cargo compartments.
One fire bottle with two discharge heads, one for each compartment, supplies three nozzles:
‐ One nozzle in the forward cargo compartment
‐ Two nozzles in the aft cargo compartment.
When the flight crew presses the FWD(AFT) DISCH pb, the action ignites the corresponding squib
on the fire bottle, which then discharges the extinguisher agent into that cargo compartment.
When the bottle is empty, the DISCH light comes on amber.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-26-50-10 P 2/4
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CARGO COMPARTMENTS - SYSTEM DESCRIPTION
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-26-50-10 P 3/4
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CARGO COMPARTMENTS - SYSTEM DESCRIPTION
Intentionally left blank
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FCOM
DSC-26-50-10 P 4/4
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CARGO COMPARTMENTS - CONTROLS AND INDICATORS
CARGO SMOKE PANEL
Applicable to: ALL
Ident.: DSC-26-50-20-10-00021446.0005001 / 17 MAR 17
Ident.: DSC-26-50-20-10-00021450.0001001 / 17 MAR 17
SMOKE LIGHT
This red light, and the associated ECAM warning, come on when the system detects smoke in the
indicated cargo compartment. This light comes on, if:
‐ Both channels detect smoke, or
‐ One channel detects smoke and the other channel is faulty.
Ident.: DSC-26-50-20-10-00021451.0002001 / 17 MAR 17
TEST PB
Tests the operation of the cargo smoke detection system.
When pressed for at least 3 s, and until released:
‐ Tests the smoke detectors in sequence
‐ Turns on the red SMOKE lights twice, and displays the ECAM warning
‐ Closes the isolation valves of the cargo ventilation system
‐ The DISCH lights come on in amber.
Ident.: DSC-26-50-20-10-00021452.0001001 / 17 MAR 17
DISCH LIGHT
Within 60 s after pressing the discharge pushbutton, the amber DISCH light comes on when the
associated bottle is fully discharged.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-26-50-20 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
FIRE PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CARGO COMPARTMENTS - CONTROLS AND INDICATORS
Ident.: DSC-26-50-20-10-00021454.0001001 / 17 MAR 17
DISCH PB
The DISCH pb ignites the squib, thereby discharging the extinguishing agent in the affected cargo
compartment.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-26-50-20 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
Intentionally left blank
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-27-10 General
DSC-27-10-10 General
General.....................................................................................................................................................................A
Basic Principle......................................................................................................................................................... B
Control Surfaces...................................................................................................................................................... C
Cockpit Controls...................................................................................................................................................... D
Computers................................................................................................................................................................E
DSC-27-10-20 Architecture
General Architecture................................................................................................................................................ A
Pitch Control............................................................................................................................................................ B
Roll Control.............................................................................................................................................................. C
Speed Brakes and Ground Spoilers....................................................................................................................... D
Yaw Control............................................................................................................................................................. E
DSC-27-20 Flight Control System
DSC-27-20-10 Normal Law
DSC-27-20-10-10 General
General.....................................................................................................................................................................A
DSC-27-20-10-20 Pitch Control
Ground Mode........................................................................................................................................................... A
Flight Mode.............................................................................................................................................................. B
Flare Mode...............................................................................................................................................................C
Protections............................................................................................................................................................... D
DSC-27-20-10-30 Lateral Control
Normal Law..............................................................................................................................................................A
Bank Angle Protection............................................................................................................................................. B
DSC-27-20-10-50 Sideslip Target
Sideslip Target......................................................................................................................................................... A
DSC-27-20-10-70 Aircraft Trimming
AIRCRAFT TRIMMING............................................................................................................................................A
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
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DSC-27-PLP-TOC P 1/2
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-27-20-20 Reconfiguration Control Laws
Continued from the previous page
General.....................................................................................................................................................................A
Flight Controls Law Reconfiguration....................................................................................................................... B
Alternate Law...........................................................................................................................................................C
Alternate Law Without Reduced Protection............................................................................................................ D
Direct Law................................................................................................................................................................ E
Abnormal Attitude Laws...........................................................................................................................................F
Mechanical Back-Up................................................................................................................................................G
DSC-27-20-30 Controls and Indicators
Pedestal................................................................................................................................................................... A
Lateral Consoles...................................................................................................................................................... B
Glareshield............................................................................................................................................................... C
Overhead Panel.......................................................................................................................................................D
Side Stick Indications On PFD................................................................................................................................E
ECAM F/CTL Page.................................................................................................................................................. F
ECAM Wheel Page................................................................................................................................................. G
Memo Display.......................................................................................................................................................... H
DSC-27-30 Flaps and Slats
DSC-27-30-10 Description
General.....................................................................................................................................................................A
Main Components....................................................................................................................................................B
Architecture.............................................................................................................................................................. C
Configurations.......................................................................................................................................................... D
Alpha/Speed Lock Function (Slats)......................................................................................................................... E
DSC-27-30-20 Controls and Indicators
Pedestal................................................................................................................................................................... A
ECAM Upper Display...............................................................................................................................................B
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-27-PLP-TOC P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
GENERAL - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-27-10-10-00001043.0001001 / 21 MAR 16
Applicable to: ALL
The fly-by-wire system was designed and certified to render the new generation of aircraft even more
safe, cost effective, and pleasant to fly.
BASIC PRINCIPLE
Ident.: DSC-27-10-10-00001044.0001001 / 21 MAR 16
Applicable to: ALL
Flight control surfaces are all :
‐ Electrically-controlled, and
‐ Hydraulically-activated.
The stabilizer and rudder can also be mechanically-controlled.
Pilots use sidesticks to fly the aircraft in pitch and roll (and in yaw, indirectly, through turn
coordination).
Computers interpret pilot input and move the flight control surfaces, as necessary, to follow their
orders.
However, when in normal law, regardless of the pilot’s input, the computers will prevent excessive
maneuvers and exceedance of the safe envelope in pitch and roll axis.
However, as on conventional aircraft, the rudder has no such protection.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-27-10-10 P 1/6
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
GENERAL - GENERAL
FLIGHT CREW
OPERATING MANUAL
CONTROL SURFACES
Ident.: DSC-27-10-10-00001045.0001001 / 21 MAR 16
Applicable to: ALL
The flight controls are electrically or mechanically controlled as follows :
PITCH AXIS
Elevator
Stabilizer
=
=
Electrical
Electrical for normal or alternate control. Mechanical for manual trim control
=
=
Electrical
Electrical
=
Mechanical, however control for yaw damping, turn coordination and trim is
electrical.
ROLL AXIS
Ailerons
Spoilers
YAW AXIS
Rudder
SPEED BRAKES
Speed
brakes
Note:
=
Electrical
All surfaces are hydraulically actuated.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-27-10-10 P 2/6
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
GENERAL - GENERAL
FLIGHT CREW
OPERATING MANUAL
COCKPIT CONTROLS
Ident.: DSC-27-10-10-00001046.0001001 / 21 MAR 16
Applicable to: ALL
‐ Each pilot has a sidestick controller with which to exercise manual control of pitch and roll. These
are on their respective lateral consoles.
The two sidestick controllers are not coupled mechanically, and they send separate sets of signals
to the flight control computers.
‐ Two pairs of pedals, which are rigidly interconnected, give the pilot mechanical control of the
rudder.
‐ The pilots control speed brakes with a lever on the center pedestal.
‐ The pilots use mechanically interconnected handwheels on each side of the center pedestal to
control the trimmable horizontal stabilizer.
‐ The pilots use a single switch on the center pedestal to set the rudder trim.
‐ There is no manual switch for trimming the ailerons.
COMPUTERS
Ident.: DSC-27-10-10-00001047.0001001 / 21 MAR 16
Applicable to: ALL
Seven flight control computers process pilot and autopilot inputs according to normal, alternate, or
direct flight control laws.
The computers are :
2 ELAC s
(Elevator Aileron Computer)
For : Normal elevator and stabilizer control.
Aileron control.
3 SEC s
(Spoilers Elevator Computer)
For : Spoilers control.
Standby elevator and stabilizer control.
2 FAC s
(Flight Augmentation Computer)
For : Electrical rudder control.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D to E →
DSC-27-10-10 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
GENERAL - GENERAL
FLIGHT CREW
OPERATING MANUAL
IN ADDITION 2 FCDC
Flight Control Data Concentrators (FCDC ) acquire data from the ELAC s and SEC s and send it to
the electronic instrument system (EIS ) and the centralized fault display system (CFDS).
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
GENERAL - GENERAL
FLIGHT CREW
OPERATING MANUAL
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OPERATING MANUAL
Intentionally left blank
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FLIGHT CREW
OPERATING MANUAL
GENERAL ARCHITECTURE
Ident.: DSC-27-10-20-00001048.0002001 / 13 JAN 14
Applicable to: ALL
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GENERAL - ARCHITECTURE
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OPERATING MANUAL
PITCH CONTROL
Applicable to: ALL
Ident.: DSC-27-10-20-A-00001049.0001001 / 21 MAR 16
GENERAL
Two elevators and the Trimmable Horizontal Stabilizer (THS ) control the aircraft in pitch. The
maximum elevator deflection is 30 ° nose up, and 17 ° nose down. The maximum THS deflection
is 13.5 ° nose up, and 4 ° nose down.
Ident.: DSC-27-10-20-A-00001050.0001001 / 21 MAR 16
ELECTRICAL CONTROL
‐ In normal operations, ELAC2 controls the elevators and the horizontal stabilizer, and the green
and yellow hydraulic jacks drive the left and right elevator surfaces respectively.
The THS is driven by N° 1 of three electric motors.
‐ If a failure occurs in ELAC 2, or in the associated hydraulic systems, or with the hydraulic jacks,
the system shifts pitch control to ELAC 1. ELAC 1 then controls the elevators via the blue
hydraulic jacks and controls the THS via the N° 2 electric motor.
‐ If neither ELAC 1 nor ELAC 2 is available, the system shifts pitch control either to SEC 1 or to
SEC 2, (depending on the status of the associated circuits), and to THS motor N° 2 or N° 3.
In case of failure, the actuators are reconfigured, Refer to DSC-27-10-20 Pitch Control Schematic.
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FLIGHT CREW
OPERATING MANUAL
GENERAL - ARCHITECTURE
Ident.: DSC-27-10-20-A-00001051.0001001 / 21 MAR 16
MECHANICAL CONTROL
Mechanical control of the THS is available from the pitch trim wheel at any time, if either the green
or yellow hydraulic system is functioning.
Mechanical control from the pitch trim wheel has priority over electrical control.
Ident.: DSC-27-10-20-A-00001053.0002001 / 21 MAR 16
ACTUATION
ELEVATORS
‐ Two electrically-controlled hydraulic servojacks drive each elevator.
Each servojack has three control modes :
• Active
: The jack position is electrically-controlled.
• Damping : The jack follows surface movement.
• Centering : The jack is hydraulically retained in the neutral position.
‐ In normal operation :
• One jack is in active mode.
• The other jack is in damping mode.
• Some maneuvers cause the second jack to become active.
‐ If the active servojack fails, the damped one becomes active, and the failed jack is
automatically switched to damping mode.
‐ If neither jack is being controlled electrically, both are automatically switched to the centering
mode.
‐ If neither jack is being controlled hydraulically, both are automatically switched to damping
mode.
‐ If one elevator fails, the deflection of the remaining elevator is limited in order to avoid putting
excessive asymmetric loads on the horizontal tailplane or rear fuselage.
STABILIZER
‐ A screwjack driven by two hydraulic motors drives the stabilizer.
‐ The two hydraulic motors are controlled by :
• One of three electric motors, or
• The mechanical trim wheel.
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AIRCRAFT SYSTEMS
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GENERAL - ARCHITECTURE
Ident.: DSC-27-10-20-A-00001054.0001001 / 09 OCT 12
SCHEMATIC
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AIRCRAFT SYSTEMS
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GENERAL - ARCHITECTURE
FLIGHT CREW
OPERATING MANUAL
ROLL CONTROL
Applicable to: ALL
Ident.: DSC-27-10-20-B-00001055.0003001 / 09 OCT 12
GENERAL
One aileron and four spoilers on each wing control the aircraft about the roll axis.
The maximum deflection of the ailerons is 25 °.
The ailerons extend 5 ° down when the flaps are extended (aileron droop).
The maximum deflection of the spoilers is 35 °.
Ident.: DSC-27-10-20-B-00001056.0001001 / 21 MAR 16
ELECTRIC CONTROL
‐ The ELAC 1 normally controls the ailerons.
If ELAC 1 fails, the system automatically transfers aileron control to ELAC2.
If both ELACs fail, the ailerons revert to the damping mode.
‐ SEC 3 controls the N° 2 spoilers, SEC 1 the N° 3 and 4 spoilers, and SEC2 the N° 5 spoilers.
If a SEC fails, the spoilers it controls are automatically retracted.
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
GENERAL - ARCHITECTURE
Ident.: DSC-27-10-20-B-00001057.0001001 / 21 MAR 16
ACTUATION
AILERONS
Each aileron has two electrically controlled hydraulic servojacks.
One of these servojacks per aileron operates at a time.
Each servojack has two control modes :
Active
: Jack position is controlled electrically
Damping : Jack follows surface movement.
The system automatically selects damping mode, if both ELACs fail or in the event of blue and
green hydraulic low pressure.
SPOILERS
A servojack positions each spoiler. Each servojack receives hydraulic power from either the
green, yellow, or blue hydraulic system, controlled by the SEC1, 2 or 3 (Refer to DSC-27-10-20
General Architecture diagram).
The system automatically retracts the spoilers to their zero position, if it detects a fault or loses
electrical control.
If the system loses hydraulic pressure, the spoiler retains the deflection it had at the time of the
loss, or a lesser deflection if aerodynamic forces push it down.
When a spoiler surface on one wing fails, the symmetric one on the other wing is inhibited.
SPEED BRAKES AND GROUND SPOILERS
Applicable to: ALL
Ident.: DSC-27-10-20-C-00001058.0011001 / 26 MAY 14
SPEED BRAKE CONTROL
The pilot controls the speedbrakes with the speed brake lever.
The speedbrakes are actually spoilers 2, 3 and 4.
Speedbrake extension is inhibited, if:
‐ SEC 1 and SEC 3 both have faults, or
‐ An elevator (L or R) has a fault, or
‐ Angle-of-attack protection is active, or
‐ Flaps are in configuration FULL, or
‐ Thrust levers above MCT position, or
‐ Alpha Floor activation.
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OPERATING MANUAL
GENERAL - ARCHITECTURE
If an inhibition occurs when the speedbrakes are extended, they retract automatically and stay
retracted until the inhibition condition disappears and the pilots reset the lever. (The speedbrakes
can be extended again 10 s or more after the lever is reset).
When a speedbrake surface on one wing fails, the symmetric one on the other wing is inhibited.
Note:
L3
1. For maintenance purposes, the speedbrake lever will extend the N° 1 surfaces when
the aircraft is stopped on ground, whatever the slat/flap configuration.
2. When the aircraft is flying faster than 315 kt or M 0.75 with the autopilot engaged, the
speedbrake retraction rate is reduced (Retraction from FULL to in takes about 25 s).
The maximum speedbrake deflection in manual flight is:
40 ° for spoilers 3 and 4
20 ° for spoiler 2.
The maximum speedbrake deflection with the autopilot engaged is:
25 ° for spoilers 3 and 4
12.5 ° for spoiler 2.
The maximum speedbrake deflection achievable with the autopilot engaged is obtained by setting
the speedbrake lever to the half way position. On setting the position of the speedbrake lever from
half to full, no increase in speedbrake deflection will be achieved.
For these surfaces (which perform both roll and speedbrake functions) the roll function has priority.
When the sum of a roll order and a simultaneous speedbrake order on one surface is greater than
the maximum deflection available in flight, the same surface on the other wing is retracted until the
difference between the two surfaces is equal to the roll order.
Ident.: DSC-27-10-20-C-00017787.0002001 / 28 APR 16
GROUND SPOILER CONTROL
The ground spoiler function involves all spoilers (full extension) and ailerons (Aileron Anti Droop
).
When a ground spoiler surface on one wing fails, the symmetric ground spoiler surface on the
other wing is inhibited.
ARMING
The pilot arms the ground spoilers by pulling the speedbrake control lever up into the armed
position.
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
GENERAL - ARCHITECTURE
FULL EXTENSION – REJECTED TAKEOFF PHASE
▪ If the ground spoilers are armed and the speed exceeds 72 kt, the ground spoilers will
automatically extend as soon as both thrust levers are reset to idle.
▪ If the ground spoilers are not armed and the speed exceeds 72 kt, the ground spoilers will
automatically extend as soon as reverse is selected on one engine (the other thrust lever
remains at idle).
FULL EXTENSION - LANDING PHASE
The ground spoilers will automatically extend when the following conditions are met:
‐ Speed brake lever not in the retracted position or ground spoilers armed and:
• Both main landing gears on ground,
• Both thrust levers at or below Idle position, or Reverse selected on at least one engine
(and the other thrust lever below MCT position).
‐ Speed brake lever in the retracted position but ground spoilers not armed and:
• Both main landing gears on ground,
• Reverse selected on at least one engine (and the other thrust lever below MCT position).
The ailerons are fully-extended (Aileron Anti Droop ), provided one aileron servocontrol is
available on each side, when:
‐ The ground spoilers are fully extended
‐ Flaps are not in clean CONF
‐ Pitch attitude is lower than 2.5 °
‐ Flying manually
‐ In normal law only.
PARTIAL EXTENSION
In order to accelerate the full spoiler extension, the Phased Lift Dumping (PLD) function allows
the ground spoilers to deploy with a reduced deflection when the following conditions are met:
‐ Speed brake lever not in the retracted position or ground spoilers armed and:
• One main landing gear on ground,
• Both thrust levers at or below Idle position.
‐ Speed brake lever in the retracted position but ground spoilers not armed and:
• One main landing gear on ground,
• Reverse selected on at least one engine (and the other thrust lever below MCT position).
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
GENERAL - ARCHITECTURE
In order to reduce the bounce severity at landing in the case of an inappropriate thrust lever
handling during flare, ground spoilers are also partially deployed when the following conditions
are met:
‐ Ground spoilers armed,
‐ Both main landing gears on ground,
‐ Both thrust levers at or below the Climb position.
RETRACTION
The ground spoilers retract:
• After landing,
• After a rejected takeoff, when the ground spoilers are disarmed.
• During a touch and go, when at least one thrust lever is advanced above 20 °.
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
GENERAL - ARCHITECTURE
Ident.: DSC-27-10-20-C-00001060.0002001 / 22 MAY 12
ROLL CONTROL - SCHEMATIC
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AIRCRAFT SYSTEMS
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GENERAL - ARCHITECTURE
FLIGHT CREW
OPERATING MANUAL
YAW CONTROL
Applicable to: ALL
Ident.: DSC-27-10-20-D-00001061.0001001 / 09 OCT 12
GENERAL
One rudder surface controls yaw.
Ident.: DSC-27-10-20-D-00001062.0001001 / 21 MAR 16
ELECTRICAL RUDDER CONTROL
The yaw damping and turn coordination functions are automatic.
The ELAC s compute yaw orders for coordinating turns and damping yaw oscillations, and
transmit them to the FACs.
Ident.: DSC-27-10-20-D-00001063.0001001 / 21 MAR 16
MECHANICAL RUDDER CONTROL
The pilots can use conventional rudder pedals to control the rudder.
Ident.: DSC-27-10-20-D-00001064.0001001 / 21 MAR 16
RUDDER ACTUATION
Three independent hydraulic servojacks, operating in parallel, actuate the rudder. In automatic
operation (yaw damping, turn coordination) a green servo actuator drives all three servojacks. A
yellow servo actuator remains synchronized and takes over if there is a failure.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL - ARCHITECTURE
There is no feedback to the rudder pedals from the yaw damping and turn coordination functions.
Ident.: DSC-27-10-20-D-00001065.0003001 / 21 MAR 16
RUDDER TRAVEL LIMIT
The maximum rudder travel deflection gradually reduces as the speed increases, to avoid
structural loads:
In the case of a failure that causes loss of the Rudder Travel limit system, the rudder deflection
limit stops at the last value reached. At slats extension, full rudder travel authority is recovered.
In all cases, the available rudder deflection provides sufficient yaw control within the entire flight
envelope. This includes the case of maximum asymmetric thrust.
Ident.: DSC-27-10-20-D-00015506.0001001 / 21 MAR 16
RELATIONSHIP BETWEEN SIDESLIP/RUDDER DEFLECTION/RUDDER PEDAL TRAVEL
Regardless of the aircraft speed, therefore the maximum rudder deflection, full rudder pedal travel
remains available. However, except at low speed, maximum rudder deflection is achieved before
reaching maximum rudder pedal travel.
Ident.: DSC-27-10-20-D-00001066.0002001 / 21 MAR 16
RUDDER TRIM
The two electric motors that position the artificial feel unit also trim the rudder. In normal
operation, motor N° 1 (controlled by FAC 1), powers the trim, and FAC2 with motor N° 2 remains
synchronized as a backup.
In manual flight, the pilot can apply rudder trim via the rotary RUD TRIM switch on the pedestal.
The pilot can use a button on the RUD TRIM panel to reset the rudder trim to zero.
Note:
With the autopilot engaged, the FMGC computes the rudder trim orders. The rudder trim
rotary switch and the rudder trim reset pushbutton are not active.
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Ident.: DSC-27-10-20-D-00001067.0001001 / 21 MAR 16
SCHEMATIC
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GENERAL - ARCHITECTURE
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OPERATING MANUAL
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FLIGHT CONTROL SYSTEM - NORMAL LAW
General
GENERAL
Ident.: DSC-27-20-10-10-00001068.0001001 / 17 MAR 17
Applicable to: ALL
Flight control normal law covers:
‐ three-axis control
‐ flight envelope protection
‐ alleviation of maneuver loads
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FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - NORMAL LAW
One of the PF's primary tasks is to maintain the aircraft within the limits of the normal flight envelope.
However, some circumstances, due to extreme situations or aircraft mishandling, may provoke the
violation of these limits.
Despite system protections, the PF must not exceed deliberately the normal flight envelope. In
addition, these protections are not designed to be structural limit protections (e.g. opposite rudder
pedal inputs). Rather, they are designed to assist the PF in emergency and stressful situations,
where only instinctive and rapid reactions will be effective.
Protections are intended to:
• Provide full authority to the PF to consistently achieve the best possible aircraft performance in
extreme conditions
• Reduce the risks of overcontrolling, or overstressing the aircraft
• Provide PF with an instinctive and immediate procedure to ensure that the PF achieves the best
possible result.
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AIRCRAFT SYSTEMS
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FLIGHT CONTROL SYSTEM - NORMAL LAW
FLIGHT CREW
OPERATING MANUAL
Pitch Control
GROUND MODE
Ident.: DSC-27-20-10-20-00001069.0001001 / 20 SEP 13
Applicable to: ALL
Ground mode is a direct relationship between sidestick deflection and elevator deflection, without
auto trim.
It automatically sets the trimmable horizontal stabilizer (THS) at 0 ° (inside the green band).
A setting that the pilot enters manually to adjust for CG has priority for takeoff.
When the aircraft reaches 75 kt during the takeoff roll, the system reduces the maximum up elevator
deflection from 30 ° to 20 °.
FLIGHT MODE
Ident.: DSC-27-20-10-20-00001070.0003001 / 17 MAR 17
Applicable to: ALL
The normal-law flight mode is a load-factor-demand mode with automatic trim and protection
throughout the flight envelope.
Following normal law, the sidestick controllers set the elevator and THS to maintain load factor
proportional to stick deflection and independent of speed.
With the sidestick at neutral, wings level, the system maintains 1 g in pitch (corrected for pitch
attitude), and there is no need for the pilot to trim by changing speed or configuration. Therefore
pilots only need to perform minor corrections on the sidestick, if the aircraft deviates from its intended
flight path. If the pilot senses an overcontrol, the sidestick should be released.
Pitch trim is automatic both in manual mode and when the autopilot is engaged. In normal turns (up
to 33 ° of bank) the pilot does not have to make any pitch corrections once the turn is established.
The flight mode is active from takeoff to landing, and follows the logic shown schematically (Refer to
DSC-27-20-10-10 General).
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
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FLIGHT CONTROL SYSTEM - NORMAL LAW
FLIGHT CREW
OPERATING MANUAL
Airbus Pitch Characteristic
Automatic pitch trim freezes in the following situations:
‐ The pilot enters a manual trim order.
‐ The radio height is below 50 ft (100 ft with autopilot engaged).
‐ The load factor goes below 0.5 g.
When angle-of-attack protection is active, the THS setting is limited between the setting at the
aircraft’s entry into this protection and 3.5 ° nose down. (Neither the pilot nor the system can apply
additional nose-up trim).
Similarly, when the load factor is higher than 1.25 g or when the aircraft exceeds 33 ° of bank, the
THS setting is limited to values between the actual setting and 3.5 ° nose down.
When High Speed or High Mach Protection is active, the THS Setting is limited between the setting
at the aircraft’s entry into this protection and 11 ° nose-up.
CONTROL WITH AUTOPILOT ENGAGED
‐ The ELAC s and SECs limit what the autopilot can order.
‐ The pilot has to overcome a restraining force in order to move the sidestick when the autopilot is
engaged. If he overcomes this force, he disconnects the autopilot.
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AIRCRAFT SYSTEMS
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FLIGHT CONTROL SYSTEM - NORMAL LAW
FLIGHT CREW
OPERATING MANUAL
‐ The pilot can also disconnect the autopilot by pushing on the rudder pedals (10 ° out of trim), or
by moving the pitch trim wheel beyond a certain threshold.
‐ All protections of normal laws remain effective except pitch attitude protection.
FLARE MODE
Ident.: DSC-27-20-10-20-00001071.0001001 / 21 MAR 16
Applicable to: ALL
When the aircraft passes 50 ft RA, the THS is frozen and the normal flight mode changes to flare
mode as the aircraft descends to land. Flare mode is essentially a direct stick-to-elevator relationship
(with some damping provided by the load factor and the pitch rate feedbacks).
The system memorizes the aircraft's attitude at 50 ft, and it becomes the initial reference for pitch
attitude control.
As the aircraft descends through 30 ft, the system begins to reduce the pitch attitude to -2 °nose
down over a period of 8 s. Consequently, to flare the aircraft, a gentle nose-up action by the pilot is
required.
PROTECTIONS
Applicable to: ALL
Ident.: DSC-27-20-10-20-A-00001072.0001001 / 21 MAR 16
GENERAL
The normal law protects the aircraft throughout the flight envelope, as follows :
‐ load factor limitation
‐ pitch attitude protection
‐ high-angle-of-attack (AOA) protection
‐ high-speed protection.
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FLIGHT CONTROL SYSTEM - NORMAL LAW
Ident.: DSC-27-20-10-20-A-00001073.0001001 / 17 MAR 17
LOAD FACTOR PROTECTION
High load factors can be encountered during evasive maneuvers due to potential collisions, or
CFIT …
Pulling "g" is efficient, if the resulting maneuver is really flown with this "g" number. If the aircraft is
not able to fly this trajectory, or to perform this maneuver, pulling "g" will be detrimental.
The load factor is automatically limited to:
+2.5 g to -1 g for clean configuration.
+2 g to 0 for other configurations.
Airbus LOAD FACTOR PROTECTION AND SAFETY
On most commercial aircraft, the potential for an efficient 2.5 g maneuver is very remote.
Furthermore, as G Load information is not continuously provided in the cockpit, airline pilots are
not used to controlling this parameter. This is further evidenced by inflight experience, which
reveals that: In emergency situations, initial PF reaction on a yoke or sidestick is hesitant, then
aggressive.
With load factor protection, the PF may immediately and instinctively pull the sidestick full aft: The
aircraft will initially fly a 2.5 g maneuver without losing time. Then, if the PF still needs to maintain
the sidestick full aft stick, because the danger still exists, then the high AOA protection will take
over. Load factor protection enhances this high AOA protection.
Load factor protection enables immediate PF reaction, without any risk of overstressing the
aircraft.
Flight experience has also revealed that an immediate 2.5 g reaction provides larger obstacle
clearance, than a hesitant and delayed high G Load maneuver (two-second delay).
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FLIGHT CONTROL SYSTEM - NORMAL LAW
Ident.: DSC-27-20-10-20-A-00001074.0001001 / 17 MAR 17
PITCH ATTITUDE PROTECTION
Excessive pitch attitudes, caused by upsets or inappropriate maneuvers, lead to hazardous
situations:
• Too high a nose-up ▸ Very rapid energy loss
• Too low a nose-down ▸ Very rapid energy gain
Furthermore, there is no emergency situation that requires flying at excessive attitudes. For these
reasons, pitch attitude protection limits pitch attitude:
‐ 30 ° nose up in conf 0 to 3 (progressively reduced to 25 ° at low speed).
‐ 25 ° nose up in conf FULL (progressively reduced to 20 ° at low speed).
‐ 15 ° nose down (indicated by green symbols “=” on the PFD’s pitch scale).
The flight director bars disappear from the PFD when the pitch attitude exceeds 25 ° up or 13 °
down. They return to the display when the pitch angle returns to the region between 22 ° up and
10 ° down.
Pitch attitude protection enhances high speed protection, high load factor protection, and high
AOA protection.
Ident.: DSC-27-20-10-20-A-00001075.0002001 / 17 MAR 17
HIGH ANGLE-OF-ATTACK PROTECTION
In the normal law, the aircraft is protected against stall, in dynamic maneuvers or gusts. When the
current angle-of-attack becomes greater than αPROT , the high angle-of-attack (AOA) protection
activates.
Without pilot input, the F/CTL computers will maintain the AOA equal to αPROT . The AOA can
be further increased by the pilot input, up to a maximum value equal to αMAX . When the High
AOA protection is activated, the normal law demand is modified and the side stick input is an
angle-of-attack demand, instead of a load factor demand.
The PF must not deliberately fly the aircraft in the High AOA, except for brief periods, when
maximum maneuvering speed is required.
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AIRCRAFT SYSTEMS
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FLIGHT CONTROL SYSTEM - NORMAL LAW
FLIGHT CREW
OPERATING MANUAL
Airbus AOA Protection
Vα PROT , Vα floor, Vα MAX are mainly computed based on the AOA, and therefore they vary
with configuration, weight and load factor.
Refer to DSC-22_10-50-20 Characteristic Speedsfor more information.
The angle-of-attack will not exceed αMAX , even if the pilot gently pulls the sidestick all the
way back. The pilot can hold full back stick, if it is needed, and the aircraft stabilizes at an
angle-of-attack close to but less than the 1 g stall. When flying at αMAX , the PF can make gentle
turns, if necessary. If the pilot releases the sidestick, the angle-of-attack returns to αPROT and
stays there. As the aircraft enters protection at the amber and black strip (αPROT), the system
inhibits further nose-up trim beyond the point already reached. The nose-down trim remains
available, if the pilot pushes the stick forward.
Note:
At takeoff, the αPROT is equal to the αMAX for 5 s.
This High AOA protection has priority over all other protections.
The aircraft can also enter αPROT at a high flight level, where it protects the aircraft from the
buffet boundary. As at a low speed or low flight level, if the sidestick is merely released to neutral,
the aircraft maintains the alpha for αPROT . This value of alpha is not the same as the value used
at the low speed. Alpha for αPROT is reduced as a function of Mach, so that a typical cruise value
is about 3.5 ° for the A318 and A321 aircraft, or 4.5 ° for the A319 and A320 aircraft. Therefore,
the aircraft may climb with the sidestick free, when leaving a turn after entering αPROT.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - NORMAL LAW
If the pilot flies into αPROT , he should leave it as soon as other considerations allow, by easing
forward on the sidestick to reduce alpha below the value of αPROT, while simultaneously adding
power (if the αfloor has not yet been activated, or cancelled).
To deactivate the angle of attack protection, the pilot must push the sidestick:
‐ Greater than 8 ° forward, or,
‐ Greater than 0.5 ° for at least 0.5 s when α < αMAX.
In addition, below 200 ft, the angle of attack protection is also deactivated, when:
‐ Sidestick deflection is less than half nose-up, and
‐ Actual α is less than αPROT – 2 °.
Between the αPROT and αMAX , αfloor protection may automatically set the go-around thrust.
The αfloor will usually be triggered just after entering αPROT , and the go-around thrust will
automatically be applied. Therefore, if the sidestick is held aft, either inadvertently or deliberately,
the aircraft will start to climb at a relatively constant low airspeed. To recover a normal flight
condition, the αPROT should be exited by easing forward on the sidestick, as described above,
and the αfloor should be cancelled by using the disconnect pushbutton on either thrust lever
as soon as a safe speed is regained. Refer to DSC-22_40-30 Alpha-Floor Protectionfor more
information.
GPWS / WINDSHEAR CASE:
In the case of application of GPWS or windshear procedures, aircraft protections provide
maximum lift / maximum thrust / minimum drag. Therefore, CFIT escape manoeuvres will be
much more efficient.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - NORMAL LAW
Protected A/C Versus Non-protected A/C Go-around Trajectory
The above-illustrated are typical trajectories flown by protected or not protected aircraft, when
the PF applies the escape procedure after an aural “ GPWS PULL UP” alert.
The graph demonstrates the efficiency of the protection, to ensure a duck-under that is 50 %
lower, a bucket-distance that is 50 % shorter, a safety margin that more than doubles (due to
a quicker reaction time), and a significant altitude gain (± 250 ft). These characteristics are
common to all protected aircraft, because the escape procedure is easy to achieve, and enables
the PF to fly the aircraft at a constant AOA , close to the max AOA . It is much more difficult to
fly the stick shaker AOA on an aircraft that is not protected.
Ident.: DSC-27-20-10-20-A-00001076.0002001 / 17 MAR 17
HIGH SPEED PROTECTION
The aircraft automatically recovers, following a high speed upset. Depending on the flight
conditions (high acceleration, low pitch attitude), High Speed Protection is activated at/or above
VMO /MMO.
When it is activated, the THS setting is limited between the setting at the aircraft’s entry into this
protection and 11 ° nose-up. Positive spiral static stability is introduced to 0 ° bank angle (instead
of 33 ° in normal law), so that with the sidestick released, the aircraft always returns to a bank
angle of 0 °. The bank angle limit is reduced from 67 °to 40 °.
As the speed increases above VMO /MMO, the sidestick nose-down authority is progressively
reduced, and a permanent nose-up order is applied to aid recovery to normal flight conditions.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - NORMAL LAW
Therefore, in a dive situation:
• If there is no sidestick input on the sidestick, the aircraft will slightly overshoot VMO /MMO and
fly back towards the envelope.
• If the sidestick is maintained full forward, the aircraft will significantly overshoot VMO /MMO . At
approximately VMO +16 / MMO +0.04, the pitch nose-down authority smoothly reduces to zero
(which does not mean that the aircraft stabilizes at that speed).
The PF, therefore, has full authority to perform a high speed/steep dive escape maneuver, when
required, via a reflex action on the sidestick.
High Speed Protection is deactivated, when the aircraft speed decreases below VMO /MMO,
where the usual normal control laws are recovered.
The autopilot disconnects at VMO + 15 kt and MMO + 0.04.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
FLIGHT CONTROL SYSTEM - NORMAL LAW
1. The ECAM displays an "O/SPEED" warning at VMO + 4 kt and MMO + 0.006.
2. At high altitude, this may result in activation of the angle of attack protection.
Depending on the ELAC standard, the crew may have to push on the stick to get out of
this protection law.
Ident.: DSC-27-20-10-20-A-00001077.0001001 / 21 MAR 16
LOW ENERGY AURAL ALERT ( IF INSTALLED)
The low energy aural alert is computed by the FAC (Refer to DSC-22_40-10 General).
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CONTROL SYSTEM - NORMAL LAW
FLIGHT CREW
OPERATING MANUAL
Lateral Control
NORMAL LAW
Ident.: DSC-27-20-10-30-00001078.0001001 / 17 MAR 17
Applicable to: ALL
When the aircraft is on the ground (in “on ground” mode), the sidestick commands the aileron and roll
spoiler surface deflection. The amount of control surface deflection that results from a given amount
of sidestick deflection depends upon aircraft speed. The pedals control rudder deflection through a
direct mechanical linkage. The aircraft smoothly transitions to “in flight” mode shortly after liftoff.
When the aircraft is in the “in flight” mode, normal law combines control of the ailerons, spoilers
(except N° 1 spoilers), and rudder (for turn coordination) in the sidestick. The pilot does not need to
use the rudder for turn coordination. While the system thereby gives the pilot control of the roll and
heading, it also limits the roll rate and bank angle, coordinates the turns, and damps the dutch roll.
The roll rate requested by the pilot during flight is proportional to the sidestick deflection, with a
maximum rate of 15 °/s when the sidestick is at the stop.
When the aircraft is in “flare” mode, the lateral control is the same as in “in flight” mode.
After touchdown, the aircraft smoothly transitions from “in flight” mode to “ground” mode.
BANK ANGLE PROTECTION
Ident.: DSC-27-20-10-30-00001079.0001001 / 17 MAR 17
Applicable to: ALL
Inside the normal flight envelope, the system maintains positive spiral static stability for bank angles
above 33 °. If the pilot releases the sidestick at a bank angle greater than 33 °, the bank angle
automatically reduces to 33 °. Up to 33 °, the system holds the roll attitude constant when the
sidestick is at neutral. If the pilot holds full lateral sidestick deflection, the bank angle goes to 67 ° and
no further.
If Angle-of-Attack protection is active, and the pilot maintains full lateral deflection on the sidestick,
the bank angle will not go beyond 45 °. If High Speed Protection is active, and the pilot maintains full
lateral deflection on the sidestick, the bank angle will not go beyond 40 °. If high speed protection is
operative, the system maintains positive spiral static stability from a bank angle of 0 °, so that with
the sidestick released, the aircraft always returns to a bank angle of 0 °.
When bank angle protection is active, auto trim is inoperative.
If the bank angle exceeds 45 °, the autopilot disconnects and the FD bars disappear. The FD bars
return when the bank angle decreases to less than 40 °.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - NORMAL LAW
During a normal turn (bank angle less than 33 °), in level flight:
• The PF moves the sidestick laterally (the more the sidestick is moved laterally, the greater the
resulting roll rate - e.g. 15 °/s at max deflection)
• It is not necessary to make a pitch correction
• It is not necessary to use the rudder.
In the case of steep turns (bank angle greater than 33 °), the PF must apply:
• Lateral pressure on the sidestick to maintain bank
• Aft pressure on the sidestick to maintain level flight.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CONTROL SYSTEM - NORMAL LAW
FLIGHT CREW
OPERATING MANUAL
Sideslip Target
SIDESLIP TARGET
Ident.: DSC-27-20-10-50-00001081.0001001 / 17 MAR 17
Applicable to: ALL
If one engine fails, the FAC modifies the sideslip indication slightly to show the pilot how much rudder
to use to get the best climb performance (ailerons to neutral and spoilers retracted).
In the case of an engine failure at takeoff, or at go-around, the sideslip index on the PFD changes
from yellow to blue (to provide the conditions for the blue display of the sideslip target, Refer to
DSC-31-40 Attitude Data).
In flight, the lateral normal law commands some rudder surface deflection to minimize the sideslip.
The pilot’s response is normal and instinctive: zero the slip indication by applying the right amount of
rudder to get the best climb performance.
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FLIGHT CONTROLS
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FLIGHT CONTROL SYSTEM - NORMAL LAW
FLIGHT CREW
OPERATING MANUAL
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FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CONTROL SYSTEM - NORMAL LAW
FLIGHT CREW
OPERATING MANUAL
Aircraft Trimming
AIRCRAFT TRIMMING
Ident.: DSC-27-20-10-70-00002179.0001001 / 09 DEC 09
Applicable to: ALL
When the aircraft is :
‐ In normal cruise range (around M .77),
‐ In straight flight,
‐ With the autopilot engaged,
‐ With symmetrical engine thrust, and
‐ With fuel in the wing tanks distributed symmetrically,
the rudder trim should stay between 1 ° right and 2.3 ° left.
Note:
This indication corresponds to a true rudder deflection within ± 1.5 °, taking into account the
permanent offset of rudder trim indication, when the aircraft is in cruise conditions. (average
0.5 ° right, 0.8 ° left).
An indicated, rudder trim above 1 ° right or 2.3 ° left is acceptable, if maintenance personnel
establishes that the corresponding real rudder position is within 1.5 ° left, and 1.5 ° right.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CONTROL SYSTEM - NORMAL LAW
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
GENERAL
Ident.: DSC-27-20-20-00001082.0001001 / 17 MAR 17
Applicable to: ALL
Depending on the failures occuring to the flight control system, or on its peripherals, there are 3
levels of reconfiguration :
‐ Alternate law
They are two levels of alternate law : with and without reduced protections.
‐ Direct law
‐ Mechanical
The ECAM and PFD indicate any control law degradation.
ON THE ECAM
In ALTN Law:
FLT CTL ALTN LAW (PROT LOST)
MAX SPEED
320 kt (320 kt/M 0.77 on A318)
In Direct Law:
FLT CTL DIRECT LAW (PROT LOST)
MAX SPEED
320 kt/M 0.77
MAN PITCH TRIM USE
ON THE PFD
The PFD enhances the PF’s awarness of the status of flight controls.
Specific symbols (= in green), and specific formatting of low speed information on the speed scale
in normal law, indicate which protections are available.
When protections are lost, amber crosses (X ) appear, instead of the green protection symbols (=).
When automatic pitch trim is no longer available, the PFD indicates this with an amber “USE MAN
PITCH TRIM” message below the FMA.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
Fly-by-Wire Status Awareness via the PFD
Therefore, by simply looking at this main instrument (PFD), the flight crew is immediately aware of
the status of flight controls, and the operational consequences.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
FLIGHT CONTROLS LAW RECONFIGURATION
Ident.: DSC-27-20-20-00001083.0001001 / 22 MAY 12
Applicable to: ALL
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
ALTERNATE LAW
Ident.: DSC-27-20-20-00001084.0001001 / 21 AUG 15
Applicable to: ALL
(1)
OR SLATS OR FLAPS ≥ 2 IF L/G INFORMATION NO LONGER AVAILABLE (LGCIU 1+2
FAULT OR SEC 1+2+3 FAULT)
(2)
OR SLATS OR FLAPS < 2 IF L/G INFORMATION NO LONGER AVAILABLE (LGCIU 1+2
FAULT OR SEC 1+2+3 FAULT)
(3)
Refer to DSC-27-20-20 Flight Controls Law Reconfiguration.
PITCH CONTROL
GROUND MODE
Under alternate law the ground mode becomes active on the ground 5 s after touchdown.
It is identical to the ground mode of the normal law.
FLIGHT MODE
In flight, the alternate law pitch mode follows a load-factor demand law much as the normal law
pitch mode does, but it has less built-in protection (reduced protections).
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
FLARE MODE
In pitch alternate law the flight mode changes to the flare mode when the pilot selects landing
gear down. The flare mode is a direct stick-to-elevator relationship. (Refer to DSC-27-20-20
Direct Law).
LATERAL CONTROL
When the aircraft flying in pitch alternate law, lateral control follows the roll direct law associated
with yaw alternate or mechanical.
ROLL DIRECT LAW
Refer to DSC-27-20-20 Direct Law.
YAW ALTERNATE LAW
Only the yaw damping function is available. Damper authority is limited to ±5 ° of rudder
deflection.
REDUCED PROTECTIONS
LOAD FACTOR LIMITATION
The load factor limitation is similar to that under normal law.
PITCH ATTITUDE PROTECTION
There is no pitch attitude protection. Amber Xs replace the green double bars “=” on the PFD.
LOW SPEED STABILITY
An artificial low speed stability replaces the normal angle-of-attack protection. It is available
for all slat/flap configurations, and the low speed stability is active from about 5 kt up to about
10 kt above stall warning speed, depending on the aircraft’s gross weight and slats/flaps
configuration.
A gentle progressive nose down signal is introduced, which tends to keep the speed from falling
below these values. The pilot can override this demand.
The system also injects bank-angle compensation, so that operation effectively maintains a
constant angle of attack.
In addition, audio stall warnings (crickets + “STALL” synthetic voice message) is activated at an
appropriate margin from the stall condition.
The PFD speed scale is modified to show a black/red barber pole below the stall warning.
The α floor protection is inoperative.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
HIGH SPEED STABILITY
Above VMO or MMO, a nose up demand is introduced to avoid an excessive increase in speed.
The pilot can override this demand.
In addition, the aural overspeed warning (VMO + 4 or MMO + 0.006) remains available.
BANK ANGLE PROTECTION
Not provided.
Note:
The AP will disconnect, if speed exceeds VMO /MMO, or if the bank angle exceeds
45 °.
ALTERNATE LAW WITHOUT REDUCED PROTECTION
Ident.: DSC-27-20-20-00001085.0001001 / 21 MAR 16
Applicable to: ALL
This is identical to alternate law except that it does not include the low-speed stability or the
high-speed stability. It includes only the load factor limitation.
DIRECT LAW
Ident.: DSC-27-20-20-00001086.0001001 / 21 MAR 16
Applicable to: ALL
PITCH CONTROL
The pitch direct law is a direct stick-to-elevator relationship (elevator deflection is proportional to
stick deflection).
In all configurations the maximum elevator deflection varies as a function of CG.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
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FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
It is a compromise between adequate controllability with the CG forward, and not-too-sensitive
control with the CG aft.
There is no automatic trim : the pilot must trim manually.
The PFD displays in amber the message “USE MAN PITCH TRIM”.
No protections are operative.
The α floor function is inoperative.
Overspeed and stall warnings are available as for alternate law.
LATERAL CONTROL
When flying in “direct law”, the roll direct law associated with mechanical yaw control governs
lateral control.
ROLL DIRECT LAW
The roll direct law is a direct stick-to-surface-position relationship. System gains are set
automatically to correspond to slat/flap configuration.
With the aircraft in the clean configuration, the maximum roll rate is about 30 °/s.
With slats extended, it is about 25 °/s.
To limit roll rate, the roll direct law uses only ailerons and spoilers N° 4 and 5.
If spoiler N° 4 has failed, spoiler N° 3 replaces it.
If the ailerons have failed, all roll spoilers become active.
YAW MECHANICAL CONTROL
The pilot controls yaw with the rudder pedals.
The yaw damping and turn coordination functions are lost.
ABNORMAL ATTITUDE LAWS
Ident.: DSC-27-20-20-00001087.0002001 / 18 JAN 17
Applicable to: ALL
If for any reason the aircraft goes far outside the normal flight envelope and reaches an extreme
attitude, the flight control law will be modified.
The abnormal attitude law will engage and will provide the PF with maximum efficiency to recover
normal attitude.
L2
The abnormal attitude law engages when one of the following values is reached:
‐ Bank angle above 125 °
‐ Pitch attitude above 50 ° nose up or below 30 ° nose down
‐ Speed below 60 to 90 kt (depending on the aircraft pitch attitude), or above 440 kt
‐ Mach above 0.91
‐ Angle of attack above 30 ° to 40 °, or below -10 °
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
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FLIGHT CREW
OPERATING MANUAL
L1
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
When the abnormal attitude law engages:
‐ The pitch alternate law is active with no protection, except load–factor protection and without
autotrim.
‐ The roll direct law is active
‐ The yaw mechanical law is active.
When the aircraft returns within the normal flight envelope, the abnormal attitude law disengages and
the following conditions remains for the remainder of the flight:
‐ The pitch alternate law is active with no protection and with autotrim.
‐ The roll direct law is active
‐ The yaw alternate law is active.
MECHANICAL BACK-UP
Ident.: DSC-27-20-20-00001088.0001001 / 17 MAR 17
Applicable to: ALL
The purpose of the mechanical backup is to achieve all safety objectives in MMEL dispatch
condition: to manage a temporary and total electrical loss, the temporary loss of five fly-by-wire
computers, the loss of both elevators, or the total loss of ailerons and spoilers.
PITCH
The pilot manually applies trim to the THS to control the aircraft in pitch.
The PFDs display “MAN PITCH TRIM ONLY” in red.
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
LATERAL
The pilot uses the rudder pedals as the mechanical backup to laterally control the aircraft .
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FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
PEDESTAL
Ident.: DSC-27-20-30-00001090.0002001 / 08 JUL 15
Applicable to: ALL
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AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
RUD TRIM rotary selector
Controls the rudder trim actuator, which moves the neutral point of the artificial feel by the
equivalent of one degree of rudder travel per second.
Note:
(2)
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
The rudder trim rotary selector has no effect, when the autopilot is engaged.
RESET pb
By pushing the RESET pb, the zero trim position is ordered at 1.5 °/s.
After the reset, an indication of up to 0.3° (L or R) may be observed in the rudder trim position
indication.
Note:
The RESET pb is not active, when the autopilot is engaged.
(3)
Position Indicator
Displays the rudder trim direction (L or R) and value.
(4)
SPEEDBRAKE lever
The lever controls:
‐ The position of the speedbrake surfaces.
To set speedbrake surfaces to a required position, the lever has to be pushed down and set
to the required position. A “hardpoint” is provided at “½” SPEEDBRAKE position.
‐ The manual preselection of the ground spoilers.
To arm the ground spoilers, the lever must be pulled up when in the RET position.
When the lever is armed (or reverse thrust is selected), all spoiler's surfaces will
automatically extend at landing, or in case of a rejected takeoff.
(5)
PITCH TRIM Wheel
Both pitch trim wheels provide mechanical control of the THS and have priority over electrical
control. A pilot action on the pitch trim wheel disconnects the autopilot.
Note:
Crew action on the pitch trim wheel does not disconnect the ELACs (micro-switches,
actuated by the override mechanism, ensure that the computers remain synchronized
with the manually-selected position).
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
The THS is manually-controlled on ground for the THS setting, before takeoff and in flight,
when in direct law.
‐ Before takeoff, the pilot sets the THS to the angular value, determined as a function of the
aircraft CG , using the CG scale on the wheel. The relationship between the aircraft CG and
the THS setting shown on the trim wheel is only applicable for takeoff. The limits of the THS
normal setting range for takeoff are indicated by a green band on the pitch trim wheel.
‐ In flight, when in direct law, the pilot uses the THS conventionally to fly in trim. In flight, the
aircraft pitch trim setting depends on aircraft CG , weight, altitude and speed. Consequently,
the relation between the aircraft CG , and the THS setting displayed on the pitch trim wheel,
does not apply in flight.
Following nosewheel touchdown, as the pitch attitude becomes less than 2.5 ° for more than
5 s, pitch trim is automatically reset to zero.
Note:
This function is inoperative, when the green or yellow hydraulic system is not
pressurized.
LATERAL CONSOLES
Ident.: DSC-27-20-30-00001091.0004001 / 17 MAR 17
Applicable to: ALL
SIDESTICKS
Each pilot has on his lateral console a sidestick he can use to control pitch and roll manually. Each
sidestick is springloaded to neutral.
When the autopilot is engaged, a solenoid-operated detent locks both sidesticks in the neutral
position. If the pilot applies a force above a given threshold (5 daN in pitch, 3.5 daN in roll) the
stick becomes free and the autopilot disengages.
The hand grip has two switches:
‐ Autopilot disconnect and sidestick takeover pushbutton.
‐ Push-to-talk button.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-27-20-30 P 3/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
Sidestick priority logic
‐ When only one pilot operates the sidestick, it sends his control signals to the computers.
‐ When the pilots move both side stick simultaneously in the same or opposite direction and
neither takes priority, the system adds the signals of both pilots algebraically. The total is limited
to the signal that would result from the maximum deflection of a single sidestick.
Note:
In the event of simultaneous input on both sidesticks (2 ° deflection off the neutral
position in any direction) the two green SIDE STICK PRIORITY lights on the
glareshield come on and “DUAL INPUT” voice message is activated.
A pilot can deactivate the other stick and take full control by pressing and keeping pressed his
priority takeover pushbutton.
For latching the priority condition, it is recommended to press the takeover push button for more
than 40 s.
This allows the pilot to release his takeover push button without losing priority.
However, a pilot can at any time reactivate a deactivated stick by momentarily pressing the
takeover push button on either stick.
If both pilots press their takeover pushbuttons, the pilot that presses last gets priority.
In case of a "SIDE STICK FAULT" ECAM warning, due to an electrical failure, the affected
sidestick order (sent to the computer) is forced to zero. This automatically deactivates the affected
sidestick. This explains why there is no procedure associated with this warning.
Note:
If an autopilot is engaged, any action on a takeover pushbutton disengages it.
In a priority situation
‐ A red light comes on in front of the pilot whose stick is deactivated.
‐ A green light comes on in front of the pilot who has taken control, if the other stick is not in the
neutral position (to indicate a potential and unwanted control demand).
Note:
If the aircraft is on the ground and commencing its takeoff run and one stick is
deactivated, this triggers the takeoff “CONFIG” warning.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-27-20-30 P 4/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
GLARESHIELD
Ident.: DSC-27-20-30-00001092.0002001 / 21 MAR 16
Applicable to: ALL
(1)
SIDE STICK PRIORITY lt
Red arrow light : ‐ comes on in front of the pilot losing authority.
‐ goes out if he has recovered his authority
• if the other pilot releases his TAKEOVER pushbutton prior the priority
condition is latched.
or
• If he has used his takeover push button to cancel a latched priority
situation.
Sidestick priority audio : A “PRIORITY LEFT” or “PRIORITY RIGHT”
audio voice message is given each time priority is taken.
Green CAPT and F/O lights :
‐ Both lights flash when the pilots move both sidesticks simultaneously and neither takes
priority.
‐ When a pilot has taken priority by pressing the takeover pushbutton and the other pilot's
sidestick is not at neutral, the light in front of the pilot with priority lights up. It goes out when
the other pilot returns his stick to the neutral position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-27-20-30 P 5/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
OVERHEAD PANEL
Ident.: DSC-27-20-30-00017869.0001001 / 19 SEP 16
Applicable to: ALL
(1)
ELAC 1(2) pushbutton
Controls the Elevator and Aileron Computer (ELAC) 1(2).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
DSC-27-20-30 P 6/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ON
:
OFF
:
FAULT :
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
ELAC 1(2) performs the following functions :
‐ Normal pitch and roll, normal LAF
‐ Alternate pitch, alternate LAF
‐ Direct pitch and roll
‐ Abnormal attitude
‐ Aileron droop
‐ Acquisition of autopilot orders.
The corresponding computer is not active. Switching it OFF, then ON, resets the
computer.
Comes on amber, along with an ECAM caution:
‐ When a failure is detected
‐ During ELAC power-up test (eight seconds).
Note:
The ELAC power-up test occurs when electrical power is turned on, or
after the occurrence of an electrical transient lasting longer than 25 ms.
The FAULT light goes off, when the pilot selects OFF, or at the end of the ELAC
power-up test, if its results are satisfactory.
(2)
SEC 1(2)(3) pushbutton
Controls the Spoiler and Elevator Computer (SEC) 1(2)(3).
ON
: SEC 1(2)(3) performs the following functions:
‐ Normal roll (by controlling the spoilers)
‐ Speed brakes and ground spoilers
‐ Alternate pitch (SEC 1 and SEC 2 only)
‐ Direct pitch (SEC 1 and SEC 2 only)
‐ Direct roll
‐ Alternate LAF
‐ Abnormal attitude.
OFF : The corresponding computer is not active. Switching it OFF, then ON, resets the
computer.
FAULT : Comes on amber, along with an ECAM caution, when a failure is detected.
The FAULT light goes off, when the pilot selects OFF.
(3)
FAC 1(2) pushbutton
Controls the Flight Augmentation Computer (FAC) 1(2).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-27-20-30 P 7/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ON
:
OFF
:
FAULT :
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
Both FACs perform the following functions:
‐ Normal roll (coordinating turns and damping dutch roll)
‐ Rudder trim
‐ Rudder travel limit
‐ Alternate yaw
The corresponding computer is not active. Switching it OFF, and then ON, resets
the computer.
Comes on amber, along with an ECAM caution, when a failure is detected.
The FAULT light goes off, when the pilot selects OFF.
SIDE STICK INDICATIONS ON PFD
Ident.: DSC-27-20-30-00001094.0001001 / 21 MAR 16
Applicable to: ALL
On the ground, after the first engine start, sidestick position indications appear white on both PFDs.
The indications disappear when the aircraft goes from the ground into flight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E
DSC-27-20-30 P 8/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
ECAM F/CTL PAGE
Ident.: DSC-27-20-30-00001095.0004001 / 15 OCT 12
Applicable to: ALL
(1)
Spoilers/Speedbrakes’ Indication
Δ : Spoiler deflected by more than 2.5 ° (green)
– : Spoiler retracted (green)
Δ : Spoiler fault deflected (amber)
1 : Spoiler fault retracted (amber)
× : Spoiler position not valid (amber)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
DSC-27-20-30 P 9/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
(2)
Hydraulic System Pressure Indication
It is normally green. It becomes amber, if the hydraulic system’s pressure decreases.
(3)
ELAC /SEC Indication
‐ ELAC and SEC labels are always displayed in white
‐ The computer number is normally in green, and boxed in grey.
The number and box become amber, if the computer fails, or is switched OFF.
(4)
Aileron position indication
It is indicated with a white scale and green index. It changes to amber, when neither (green nor
blue) servojack is available.
(5)
Aileron and elevator actuator indication
“G” and “B” are normally displayed in green.
They become amber, in the case of a green or blue hydraulic system low pressure. The partial
box also becomes amber, if the associated computer or actuator fails.
(6)
Elevator position indication
It is indicated with a white scale and green index. The index becomes amber, when both
associated actuators are not available.
(7)
Pitch trim position indication
The pitch trim numbers are in green. They become amber, if green and yellow hydraulic system
pressure decreases.
The “PITCH TRIM” legend is in white. It becomes amber, if the pitch trim jams.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
DSC-27-20-30 P 10/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(8)
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
Yaw control indications
(A) Rudder position indication
It is normally in green. The rudder symbol becomes amber, if the blue, green, and yellow
hydraulic pressures are low.
(B) Rudder travel limiter
It is normally in green. It becomes amber when travel limiter 1 and 2 are faulty.
Two TLU messages are displayed in amber when the TLU indexes are suppressed.
(C) Rudder trim position
It is normally in blue. It becomes amber, if the rudder trim reset fails.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
DSC-27-20-30 P 11/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
ECAM WHEEL PAGE
Ident.: DSC-27-20-30-00001096.0002001 / 15 FEB 11
Applicable to: ALL
(1)
Spoilers/Speedbrakes’ Indication
These indications are identical to those displayed on the FLT CTL page.
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-27-20-30-A-00016860.0001001 / 21 MAR 16
GND SPLRS ARMED
:
This memo appears in green when the ground spoilers are armed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G to H →
DSC-27-20-30 P 12/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
Ident.: DSC-27-20-30-A-00016859.0001001 / 21 MAR 16
SPEED BRK :
SPEED BRK :
This memo appears in green when the speedbrakes are extended.
This memo appears in amber when the speedbrakes should be retracted.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H
DSC-27-20-30 P 13/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-27-20-30 P 14/14
22 MAR 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLAPS AND SLATS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-27-30-10-00001097.0001001 / 21 MAR 16
Applicable to: ALL
Each wing has the following lift augmentation devices :
‐ Two flap surfaces.
‐ Five slat surfaces.
These surfaces are electrically controlled and hydraulically operated.
The pilot extends slats and flaps by moving the FLAPS lever on the center pedestal.
It has five positions.
MAIN COMPONENTS
Ident.: DSC-27-30-10-00001098.0001001 / 21 MAR 16
Applicable to: ALL
The slat and flap systems are similar, comprising :
‐ Two slat flap control computers (SFCCs), each containing one slat channel and one flap channel.
‐ A power control unit (PCU) consisting of two independent hydraulic motors coupled by a
differential gearbox.
The motors use green and blue hydraulic power for the slats and yellow and green power for the
flaps.
Pressure-off brakes (POBs) lock the transmission when the slat or flap surfaces have reached the
selected position or if hydraulic power fails.
‐ Five slat surfaces and two flap surfaces per wing.
‐ An assymetry position pick-off unit (APPU) that measures the assymetry between the left and right
wings.
‐ A flap disconnect detection system, which detects attachment failure and inhibits flap operation in
order to prevent further damage. A sensor detects the failure by measuring excessive differential
movement between the inner and the outer flaps.
‐ Wingtip brakes (WTBs), activated in case of assymetry, mechanism overspeed, symmetrical
runaway, or uncommanded movement of the surfaces. They cannot be released in flight.
They use blue and green hydraulic power for the slats and for the right wing flaps, and blue and
yellow hydraulic power for the left wing flaps.
‐ Feedback position pick-off units (FPPU s) that feed back position information to the SFCCs.
‐ An instrumentation position pick-off unit (IPPU ) that sends position data to the ECAM.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-27-30-10 P 1/6
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
FLAPS AND SLATS - DESCRIPTION
If the flap wingtip brakes are on, the pilot can still operate the slats, and if the slat wingtip
brakes are on, he can still operate the flaps.
If one SFCC is inoperative, slats and flaps both operate at half speed.
If one hydraulic system is inoperative, the corresponding surfaces (slats or flaps) operate at
half speed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-27-30-10 P 2/6
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLAPS AND SLATS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
ARCHITECTURE
Ident.: DSC-27-30-10-00001099.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-27-30-10 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLAPS AND SLATS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
CONFIGURATIONS
Ident.: DSC-27-30-10-00001100.0001001 / 09 OCT 12
Applicable to: ALL
The FLAPS lever has five positions: 0, 1, 2, 3 and FULL.
Two configurations correspond to position 1: Configuration 1 and Configuration 1 + F.
The pilot selects these as follows:
(1)
When in Configuration 1 + F, the flaps retract to 0 ° automatically at 210 kt (before the airspeed
reaches VFE).
(2)
When in configuration 1, the flaps extend to 10 ° automatically at 100 kt.
ALPHA/SPEED LOCK FUNCTION (SLATS)
Ident.: DSC-27-30-10-00001101.0001001 / 13 SEP 16
Applicable to: ALL
This function inhibits slat retraction at high angles-of-attack and low speeds.
The SFCC s use corrected angle-of-attack (alpha) or airspeed information from the ADIRUs to inhibit
slat retraction.
When the FLAPS lever is set to 0, the slats alpha/speed lock function activates and inhibits slats
retraction, if:
‐ The AOA is above 8.5 °, or
‐ The speed is less than 148 kt.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D to E →
DSC-27-30-10 P 4/6
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
FLAPS AND SLATS - DESCRIPTION
If the FLAPS lever is already set to 0, when either of the above conditions occurs, the
function will not activate therefore the slats will continue to retract or will remain at 0.
Once the slats alpha/speed lock function is active, the slats retract to 0 when:
‐ The AOA is less than 7.6 ° and
‐ The speed is above 154 kt.
Note:
When the aircraft is on ground and its speed is less than 60 kt, then the function will not
activate.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
DSC-27-30-10 P 5/6
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLAPS AND SLATS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-27-30-10 P 6/6
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLAPS AND SLATS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
PEDESTAL
Ident.: DSC-27-30-20-00001102.0001001 / 18 MAR 11
Applicable to: ALL
The five lever positions correspond to the following surface positions :
Position
SLATS
FLAPS
0
0
1
18
2
3
FULL
22
0
0
10
15
22
27
20
35
Indications
on ECAM
1
1+F
2
3
CRUISE
TAKEOFF
FULL
LDG
HOLD
APPR
Before selecting any position, the pilot must pull the lever out of the detent. Balks at positions 1 and 3
prevent the pilot from calling for excessive flap/slat travel with a single action.
Note:
The pilot cannot select an intermediate lever position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-27-30-20 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLAPS AND SLATS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
TAKEOFF IN CONFIGURATION 1
1 + F (18 °/10 °) is selected. If the pilot does not select configuration 0 after takeoff, the flaps
retract automatically at 210 kt.
TAKEOFF OR GO-AROUND IN CONFIGURATION 2 OR 3
If the pilot selects configuration 1, he gets 1 + F (18 °/10 °) if airspeed is under 210 kt.
If the pilot does not select configuration 0 after takeoff, the flaps retract automatically at 210 kt.
CONFIGURATION 0 TO CONFIGURATION 1 IN FLIGHT
Configuration 1 (18 °/0 °) is selected.
Note:
After flap retraction, configuration 1 + F is no longer available until the airspeed is 100 kt
or less, unless configuration 2, 3, or FULL has been selected previously.
ECAM UPPER DISPLAY
Ident.: DSC-27-30-20-00001103.0002001 / 14 NOV 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-27-30-20 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLAPS AND SLATS - CONTROLS AND INDICATORS
(1)
Position indexes
These white points indicate that the slats and flaps are in a selectable position. They do not
appear, when the aircraft is in clean configuration.
(2)
F and S
“F” and “S” normally appear in white. They become amber, if:
‐ Both relevant hydraulic systems fail, unless the aircraft is on ground with both engines
stopped.
‐ The wingtip brakes are on.
‐ There is a slats or flaps fault.
“S (F) LOCKED” legend, appears in amber, in association with an ECAM caution, when the
wingtip brakes are applied, or when the system detects a non-alignment between two flaps.
The “A-LOCK” legend pulses in green, when the slat alpha/speedlock function is active.
(3)
Flaps/Slats’ actual position
These green boxes indicate the actual flaps/slats position.
They become amber, if:
‐ Both relevant hydraulic systems fail, unless the aircraft is on ground with both engines
stopped.
‐ The wingtip brakes are on.
‐ There is a slats or flaps fault.
(4)
Selected position
It is in blue, when the surfaces are in transit.
It disappears, when the selected position is reached.
(5)
Flap lever position
The “0”, “1 + F”, “1”, “2”, “3”, or “FULL” legend appears.
‐ It is green, when the slats and flaps are in the selected position. “0” is not displayed, when
the aircraft attains clean configuration.
‐ It becomes cyan, when the slats and flaps are in transit.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-27-30-20 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLAPS AND SLATS - CONTROLS AND INDICATORS
Intentionally left blank
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AIRCRAFT SYSTEMS
FUEL
Intentionally left blank
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-28-10 Description
DSC-28-10-10 General
GENERAL................................................................................................................................................................ A
DSC-28-10-20 Tanks
Tanks........................................................................................................................................................................A
DSC-28-10-30 Engine Feed
GENERAL................................................................................................................................................................ A
Main Components....................................................................................................................................................B
Engine Feed............................................................................................................................................................ C
Fuel Feed Sequence............................................................................................................................................... D
DSC-28-10-50 APU Feed
APU FEED............................................................................................................................................................... A
DSC-28-10-60 Fuel Recirculation System
Fuel Recirculation System.......................................................................................................................................A
DSC-28-10-70 Refueling and Defueling
Refueling - Defueling............................................................................................................................................... A
DSC-28-10-80 Fuel Quantity Indication and Level Sensing
FUEL QUANTITY INDICATION (FQI) SYSTEM..................................................................................................... A
FUEL LEVEL SENSING CONTROL UNIT (FLSCU).............................................................................................. B
Fuel System Architecture........................................................................................................................................ C
DSC-28-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Refueling Control Panel...........................................................................................................................................B
Maintenance Panel.................................................................................................................................................. C
ECAM Fuel Page.....................................................................................................................................................D
ECAM Upper Display...............................................................................................................................................E
Memo Display.......................................................................................................................................................... F
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-28-PLP-TOC P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-28-10-10-00001107.0001001 / 13 NOV 13
Applicable to: ALL
The fuel system :
‐ Stores fuel in the tanks.
‐ Supplies fuel, in the correct quantities, to the fuel tanks during refueling.
‐ Supplies fuel to the engines and the Auxiliary Power Unit (APU).
‐ Circulates fuel to cool the Integrated Drive Generator (IDG).
‐ Keeps fuel in the outer tanks for wing bending and flutter relief.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-28-10-10 P 1/2
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AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
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DSC-28-10-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
DESCRIPTION - TANKS
FLIGHT CREW
OPERATING MANUAL
TANKS
Applicable to: ALL
Ident.: DSC-28-10-20-A-00020195.0001001 / 17 MAR 17
The fuel is stored in the wings, in the center tank, and in the Additional Center Tank (ACT ).
The wings have inner and outer tanks.
There is a vent surge tank outboard of the outer tank in each wing.
When the aircraft has been refueled to maximum capacity, the fuel can expand by 2 % (20 °C
temperature rise) without spilling.
There is an overpressure protector in each vent, outer and inner tank and between the center tank
and the left inner tank.
Ident.: DSC-28-10-20-A-00020196.0003001 / 17 MAR 17
(liters)
VOLUME
(US
gallons)
(KG)
WEIGHT(1)
(LB)
(1)
OUTER
TANKS
880 x 2
232 x 2
691 x 2
1 523 x 2
USABLE FUEL
INNER
CENTER
TANKS
TANK
7 099 x 2
8 250
1 875 x 2
5 573 x 2
12 286 x 2
2 992
NO ACT
24 209
TOTAL WITH
1 ACT
27 201
2 ACTs
30 193
2 179
790
6 395
7 185
7 975
6 476
2 349
19 004
21 353
23 702
14 278
ACT
5 175
41 893
47 068
52 243
Fuel density : 0.785 kg/l or 6.551 lb/US Gal.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-28-10-20 P 1/2
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AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
DESCRIPTION - TANKS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
DESCRIPTION - ENGINE FEED
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-28-10-30-00001109.0002001 / 10 DEC 09
Applicable to: ALL
The main fuel pump system supplies fuel from the center tank or the inner wing tanks to the engines.
The system has six main fuel pumps.
MAIN COMPONENTS
Applicable to: ALL
Ident.: DSC-28-10-30-A-00001110.0002001 / 01 FEB 13
TANK PUMPS
In normal operation each engine is supplied by one pump in the center tank or two pumps in its
own side inner tank.
All wing tank pumps remain on throughout the flight. They are fitted with pressure relief sequence
valves which ensure that, when all pumps are running, the center tank pumps will deliver fuel
preferentially.
Ident.: DSC-28-10-30-A-00001111.0001001 / 31 JAN 13
INTERTANK TRANSFER VALVES
Two electrical transfer valves are mounted in each wing to permit fuel transfer from outer to inner
tank.
Ident.: DSC-28-10-30-A-00001112.0001001 / 10 DEC 09
CROSS FEED VALVE
A cross feed valve controlled by a double motor allows both engines to be fed from one side or
one engine to be fed from both sides.
Ident.: DSC-28-10-30-A-00001113.0001001 / 20 MAR 17
ENGINE LP VALVES
The engine fuel flow can be stopped by its low pressure (LP ) fuel valve. The LP fuel valve is
closed by either :
‐ The engine master switch, or
‐ The ENG FIRE PUSH pushbutton.
Ident.: DSC-28-10-30-A-00001114.0002001 / 29 MAR 12
SUCTION VALVES
Closed by pumps pressure in normal operation, they allow engines to be fed by gravity if the inner
tank pumps fail.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-28-10-30 P 1/4
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
DESCRIPTION - ENGINE FEED
FLIGHT CREW
OPERATING MANUAL
Note:
Center tank pumps are not fitted with suction valves. Therefore, gravity feeding is not
possible from the center tank.
ENGINE FEED
Ident.: DSC-28-10-30-00001115.0002001 / 18 MAR 14
Applicable to: ALL
FUEL FEED SEQUENCE
Ident.: DSC-28-10-30-00021263.0001001 / 21 MAR 17
Applicable to: ALL
The tanks empty in the following sequence :
1. The ACT2 : Fuel transfers into the center tank.
2. The ACT1 : Fuel transfers into the center tank.
3. The center tank.
4. The inner tanks: Each inner tank empties down to 750 kg (1 650 lb).
5. The outer tanks: Fuel transfers into the inner tanks.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to D →
DSC-28-10-30 P 2/4
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - ENGINE FEED
CENTER TANK FUEL TRANSFER
The center tank feeds fuel to the engines, when the center tank pumps are not stopped by the
control logic described below. The inner tanks feed the engines when the center tank pumps are
stopped.
CENTER TANK TRANSFER VALVE CONTROL LOGIC
Each center tank pump stops, until approximately 500 kg (1 100 lb ) of the fuel in its associated
inner tank fuel has been used (when the fuel level reaches the underfull sensors).
With the MODE SEL in the MAN position, the center tank pumps will run. In manual mode, the
CTR TK PUMP pb-sw must be selected OFF, when the center tank is empty.
FUEL TRANSFER FROM OUTER TO INNER TANKS
The transfer valves automatically open, when the inner tank fuel reaches the low level (about
750 kg/1 650 lb), thus enabling the fuel to drain from the outer to inner tanks.
When open, the valves are latched open. They will automatically close at the next refueling
operation.
Note:
1. Two level sensors are installed in each inner tank. Each sensor controls two transfer
valves, one in each wing, ensuring simultaneous transfer to both wings.
2. The 750 kg/1 650 lb value is based on a level aircraft attitude, with no acceleration.
During steep descent or accelerations/decelerations, the transfer valves may open
with more than 750 kg/1 650 lb of fuel in each inner tank, and the low level warning
may be triggered.
IF THE AIRCRAFT HAS ONE ACT : ACT TO CENTER TANK TRANSFER
ACT transfer automatically starts after takeoff at slats' retraction, if the center tank high-level
sensor has been dry for 10 min, and the ACT is not empty.
Fuel transfers from the ACT to the center tank via pressurization of the tank, by closing the ACT
vent valve and opening the air shutoff valve.
When the ACT is empty, the ACT transfer valve, the air shutoff valve and inlet valve close, and the
ACT vent valve opens.
Note:
ACT transfer stops, if the center tank high level becomes wet, by closing the ACTs
transfer valve. The transfer valve reopens when the center tank high-level sensor
becomes dry for 10 min.
Selecting the ACT pb-sw to FWD opens the ACT transfer valve, the ACT inlet valve, and starts the
ACT transfer pump. It must be returned to AUTO, when the ACT is empty.
Center tank overflow is prevented, by returning the ACT pb-sw to AUTO, when the center tank is
full.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-28-10-30 P 3/4
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - ENGINE FEED
IF THE AIRCRAFT HAS TWO ACTS : ACT 1 + 2 TO CENTER TANK TRANSFER
ACT transfer automatically starts after takeoff at slats' retraction, if the center tank high-level
sensor has been dry for 10 min, and the ACT is not empty.
Fuel transfers from the ACT to the center tank via pressurization of the tank, by closing the ACT
vent valve and opening the air shutoff valve.
ACT2 transfers first, via the ACT transfer valve and the ACT2 inlet valve.
When ACT2 is empty, the ACT2 inlet valve shuts, and the ACT1 inlet valve opens.
When ACT1 is empty, the ACT transfer valve and ACT1 inlet valve close.
When the aircraft is on ground after landing, the air shutoff valve closes and both ACT vent valves
open, depressurizing the ACTs.
Note:
ACT transfer stop, if the center tank high level becomes wet, by closing the ACT transfer
valve. The transfer valve reopens when the center tank high-level sensor becomes dry
for 10 min.
Selecting the ACT pb-sw to FWD opens the ACT transfer valve and starts the ACT transfer pump.
ACT2 empties first, then ACT1. It must be returned to AUTO, when the ACT is empty.
Center tank overflow is prevented, by returning the ACT pb-sw to AUTO, when the center tank is
full.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
DSC-28-10-30 P 4/4
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
DESCRIPTION - APU FEED
FLIGHT CREW
OPERATING MANUAL
APU FEED
Ident.: DSC-28-10-50-00001120.0001001 / 10 DEC 09
Applicable to: ALL
A special fuel pump supplies fuel for APU startup when fuel feed pressure is low (due to loss of tank
pumps or loss of normal AC electrical supply). This pump normally runs off the AC ESS SHED, but
runs off the AC STAT INV BUS if the AC ESS SHED fails.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-28-10-50 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
DESCRIPTION - APU FEED
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-28-10-50 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
DESCRIPTION - FUEL RECIRCULATION SYSTEM
FLIGHT CREW
OPERATING MANUAL
FUEL RECIRCULATION SYSTEM
Applicable to: ALL
Ident.: DSC-28-10-60-B-00020316.0001001 / 17 MAR 17
Illustration - For information only
Ident.: DSC-28-10-60-B-00020317.0004001 / 17 MAR 17
Refer to DSC-70-40 IDG Cooling System.
Some of the fuel supplied to each engine goes from the high-pressure fuel line in that engine,
through the integrated drive generator (IDG) heat exchanger (where it absorbs heat), to the fuel
return valve and back to the outer fuel tank.
This operation ensures the IDG cooling when the oil temperature is high or when at low engine
power.
The FADEC controls the fuel return valve.
If the outer tank is already full, the fuel overflows to the inner tank through a spill pipe. On ground, the
fuel recirculation is not inhibited if there is an overflow in the surge tanks (Refer to DSC-70-40 IDG
Cooling System).
If the FUEL MODE SEL pb-sw is in AUTO mode:
If center tank is feeding, the wing tank will tend to overfill and the system automatically selects
the CTR TK PUMP off when the inner tank is full. The wing tank pumps will feed until the engine
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-28-10-60 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - FUEL RECIRCULATION SYSTEM
have used approximately 500 kg (1 100 lb) of fuel when the fuel level reaches the underfull
sensors. The logic circuits then restart the center tank pumps.
If the FUEL MODE SEL pb-sw is in MAN mode:
If center tank is feeding, the wing tanks will tend to overfill but the system does not automatically
select the CTR TK PUMPs OFF when the inner tank is full. Therefore, an overflow of the wing
tanks can occur on ground if the CTR TK PUMPs are not switched OFF.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-28-10-60 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
DESCRIPTION - REFUELING AND DEFUELING
FLIGHT CREW
OPERATING MANUAL
REFUELING - DEFUELING
Ident.: DSC-28-10-70-00021235.0002001 / 21 MAR 17
Applicable to: ALL
‐ During automatic refueling, fuel goes into the ACTs , the center tank and the outer cell of the
wing tanks simultaneously. When the outer cell of the wing tank is full, fuel overflows into the inner
cell. During manual refueling, fill the wing tanks first, then the center tank, then the ACTs .
‐ Electrical transients (caused by switching among the APU, the external and the engine electrical
supply) during automatic refueling may stop the process. If the automatic refueling process is
stopped, it is necessary to re-enter the Preselected Fuel Quantity.
‐ One (two) refueling point(s) is (are) installed under the wings, enabling the aircraft to be refueled
from either the right or left (if installed) side.
‐ A refuel panel is located on the fuselage side beneath the right wing, or under the right or left wing
adjacent to the refuel coupling.
‐ Another refuel panel is located on the cockpit overhead maintenance panel.
‐ A "READY FOR FUELING" green light is installed adjacent to the refuel coupling.
A gallery connects the refuel coupling to each tank's refuel valve.
Refueling is normally automatic, the required fuel load being set on the preselector.
Manual control is also available.
Automatic refueling starts with the outer tanks. If the selected fuel load exceeds the wing tank
capacity, the center tank is simultaneously refueled.
When an outer tank is full, the fuel overflows into the inner tank through a spill pipe.
Refuel valves close automatically, when the tanks contain the preselected load, or when sensors
detect a high fuel level.
The aircraft can be refueled, when only battery power is available.
The wing tanks can be refueled by gravity, through refueling points on top of the wings.
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DSC-28-10-70 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - REFUELING AND DEFUELING
A transfer valve, between the engine feed system and the refueling gallery, allows :
‐ The tank pumps to transfer fuel from one tank to another
‐ Defueling through the refuel coupling.
Approximate refueling time at nominal pressure is:
‐ 17 min for wing tanks
‐ 20 min for all tanks (without ACT )
‐ 25 min for all tanks (with one ACT )
‐ 27 min for all tanks (with two ACTs ).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-28-10-70 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - FUEL QUANTITY INDICATION AND LEVEL SENSING
FUEL QUANTITY INDICATION (FQI) SYSTEM
Ident.: DSC-28-10-80-00001123.0001001 / 10 DEC 09
Applicable to: ALL
The FQI is a computerized system that :
‐ transmits the actual total fuel mass, as well as the quantity and temperature of fuel in the tanks, to
the ECAM.
‐ controls automatic refueling.
Two channels perform fuel computations : channel 2 activates automatically if channel 1 fails.
The FQI system has :
‐ an FQI computer.
‐ a set of capacitance probes in each tank to measure fuel level and temperature.
‐ one densitometer (cadensicon) sensor in each wing inner tank permitting the calculation of the fuel
quantity.
‐ one Capacitance Index Compensator (CIC) in each inner tank giving the dielectric constant of the
fuel in case of cadensicon failure.
‐ a quantity indicator for each tank installed on the refuel/defuel panel.
‐ a preselector on the refuel/defuel panel that shows the preselected and actual total fuel quantity.
FUEL LEVEL SENSING CONTROL UNIT (FLSCU)
Ident.: DSC-28-10-80-00001124.0001001 / 16 MAR 15
Applicable to: ALL
The fuel level system generates fuel-level and fuel-temperature signals in order to operate the
appropriate switching functions for refueling and defueling and control the IDG cooling recirculation
system and the center-tank-to-wing-tank fuel transfer system.
The FLSCU comprises :
‐ fuel level sensors in the tanks to sense high, low, and overflow levels.
‐ a fuel temperature sensor to control the IDG cooling recirculation.
When fuel quantity in one wing tank goes below 750 kg (1 650 lb), the low-level sensor triggers
the LO LVL warning on ECAM. The LO LVL warning is totally independent from the displayed fuel
quantity indication of the tank.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-28-10-80 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - FUEL QUANTITY INDICATION AND LEVEL SENSING
FUEL SYSTEM ARCHITECTURE
Ident.: DSC-28-10-80-00001125.0001001 / 22 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-28-10-80 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Applicable to: ALL
Ident.: DSC-28-20-G-00020183.0001001 / 17 MAR 17
Ident.: DSC-28-20-G-00020239.0001001 / 17 MAR 17
L(R) TK PUMPS 1(2) pb-sw
On
:
OFF
FAULT light
:
:
Pump is on (but only fuel feeds) when the delivery pressure of the center tank
pumps drops below the threshold.
Pump is off, and the OFF button comes on white.
Amber light and ECAM caution come on, when the delivery pressure drops. It
does not come on when OFF is selected.
Ident.: DSC-28-20-G-00020240.0001001 / 17 MAR 17
MODE SEL pb-sw
AUTO
:
Control of center tank pumps is automatic:
‐ They run at engine start for 2 min,
‐ Before or after the engine start sequence, the pumps run if the slats are
retracted,
‐ They stop automatically 5 min after center tank low level is reached.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-28-20 P 1/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
MAN
:
FAULT light
:
CONTROLS AND INDICATORS
Flight crew manually controls the center tank pumps with the center tank
pumps' pushbutton.
Amber light comes on, and ECAM caution comes on when center tank has
more than 250 kg (550 lb) of fuel and the left or right wing tank has less than
5 000 kg (11 000 lb).
Ident.: DSC-28-20-G-00020256.0001001 / 17 MAR 17
CTR TK PUMP 1(2) pb-sw
On
:
OFF
FAULT light
:
:
Pump runs, if MAN mode is selected on the MODE SEL pb-sw.
Pump is automatically controlled when AUTO mode is selected.
Pump is off and OFF button comes on white.
Amber light and associated ECAM caution come on, when the pump is in
operation and the delivery pressure drops.
Ident.: DSC-28-20-G-00020257.0001001 / 17 MAR 17
X FEED pb-sw
ON
OFF
OPEN light
:
:
:
The valve opens, and the ON pushbutton comes on in white.
The valve closes, and the pushbutton does not come on.
This green light comes on, when the valve is fully open.
Ident.: DSC-28-20-G-00020258.0001001 / 17 MAR 17
ACT pb-sw
AUTO
:
FWD
:
FAULT light
:
Control of the ACT transfer is automatic.
‐ The automatic forward transfer occurs, if:
• The aircraft is in flight, and
• The slats are retracted, and
• At least one ACT low-level sensor is wet, and
• The center tank high-level sensor has been dry for at least 10 min.
‐ The automatic forward transfer stops, as soon as one of the above
conditions is not met.
The manual transfer to the center tank is initiated by opening:
‐ The ACT transfer valve,
‐ The ACT 1 or ACT 2 (if available) inlet valve.
The ACT transfer pump is then commanded on.
Amber light and associated ECAM caution come on, when:
‐ The center tank has less than 3 000 kg (6 614 lb) of fuel, and 1 ACT has
more than 250 kg (550 lb) of fuel, and
‐ The ACT pb-sw is on AUTO.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-28-20 P 2/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
Note:
When no ACT is installed, the pushbutton is inoperative.
REFUELING CONTROL PANEL
Applicable to: ALL
Ident.: DSC-28-20-C-00020185.0001001 / 17 MAR 17
Ident.: DSC-28-20-C-00020265.0001001 / 21 MAR 17
FUEL QUANTITY INDICATOR
The number shows the quantity of fuel in each tank.
Units may either be in kg × 1 000 or lb × 1 000 depending on the aircraft configuration.
Ident.: DSC-28-20-C-00020266.0001001 / 21 MAR 17
HI LVL light
This blue light comes on, when the system detects a high fuel level.
The corresponding refuel valve closes automatically.
Ident.: DSC-28-20-C-00020267.0001001 / 21 MAR 17
REFUEL VALVES selector (GUARDED IN NORM)
NORM
:
Automatic refueling logic controls the refuel valves.
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FCOM
← A to B →
DSC-28-20 P 3/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OPEN
:
SHUT
:
CONTROLS AND INDICATORS
Valves open when the MODE SELECT sw is set to the REFUEL or DEFUEL XFR
position. Each refuel valve closes, when the system detects a high level in the
associated tank.
Valves close.
Ident.: DSC-28-20-C-00020268.0001001 / 17 MAR 17
MODE SELECT sw (GUARDED AT OFF)
OFF
REFUEL
:
:
Refuel system is de-energized. Refuel valves are closed.
Refuel valves operate in automatic or in manual mode depending on the
position of REFUEL VALVES sw.
DEFUEL XFR : Refuel/Defuel transfer valve opens.
Refuel valve opens if the associated REFUEL VALVE sw is at OPEN.
Ident.: DSC-28-20-C-00020270.0001001 / 21 MAR 17
OPEN light
This amber light comes on when the defuel transfer valve is open.
Ident.: DSC-28-20-C-00020271.0001001 / 17 MAR 17
TEST sw
HI LVL
Note:
:
The HI LVL lights come on if high level sensors and associated circuits are
serviceable.
If tanks are full (HI LVL lights on) during this test, the HI LVL lights go out if high level
sensors and associated circuits are serviceable.
LTS
:
Lights on panel and all 8's on FQI and preselector come on.
Ident.: DSC-28-20-C-00020272.0001001 / 21 MAR 17
PRESELECTED DISPLAY
This display shows the preselected total fuel quantity in kg (lb) × 1 000 (multiply by 1 000 to get
actual amount).
Ident.: DSC-28-20-C-00020273.0001001 / 17 MAR 17
Preselector sw
Pressing the left or right side of the switch decreases or increases the preselected quantity.
Ident.: DSC-28-20-C-00020274.0001001 / 21 MAR 17
ACTUAL DISPLAY
This display shows the total fuel on board.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-28-20 P 4/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-28-20-C-00020275.0001001 / 21 MAR 17
END light
This green light comes on steady when automatic refueling is completed.
It flashes green if refueling is aborted.
Ident.: DSC-28-20-C-00020276.0002001 / 21 MAR 17
CKPT light
Indicates that cockpit refuel panel has priority.
Illuminates when electrical PWR pb-sw on cockpit refuel is pressed.
Ident.: DSC-28-20-C-00020277.0001001 / 21 MAR 17
BATT POWER TOGGLE SWITCH
ON
:
When the flight crew momentarily switches this to ON position and releases it, HOT
BUS 1 supplies the FQI.
After completion of the FQI tests (about 40 s), the fuel quantity indications appear
and refuel operation can be selected.
The electrical supply is automatically cut off:
‐ After 10 min, if no refuel operation is selected, or
‐ At the end of refueling.
NORM
:
The FQI is not supplied by batteries.
MAINTENANCE PANEL
Applicable to: ALL
Ident.: DSC-28-20-D-00020187.0007001 / 17 MAR 17
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-28-20 P 5/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
Ident.: DSC-28-20-D-00020286.0001001 / 21 MAR 17
PRESELECTED DISPLAY
This display shows the preselected total fuel quantity in KG (or in LB depending on aircraft
configuration) × 1 000 (multiply by 1 000 to get actual amount).
Ident.: DSC-28-20-D-00020287.0001001 / 21 MAR 17
ACTUAL DISPLAY
This display shows the total fuel on board.
Ident.: DSC-28-20-D-00020288.0001001 / 17 MAR 17
Preselector sw
Pressing the left or the right side of the switch decreases or increases the preselected quantity.
Ident.: DSC-28-20-D-00020289.0001001 / 21 MAR 17
END light
This green light comes on steady when automatic refueling is achieved (associated with the green
refuel light on wing extinguishing ).
It flashes green if refueling is aborted.
Ident.: DSC-28-20-D-00020290.0001001 / 17 MAR 17
PWR pb-sw
ON
:
OFF
:
FAULT
:
‐ Refuel system is energized
‐ Cockpit refuel control/preselector panels takes priority (cockpit lights illuminate
on cockpit and external refuel control panels)
‐ Automatic high level test
‐ REFUEL caption is displayed on ECAM.
‐ Refuel system is deenergized
‐ ECAM “REFUEL” caption is cleared
‐ Priority is cleared.
This amber light comes on when auto high level test not satisfied.
Ident.: DSC-28-20-D-00020291.0001001 / 17 MAR 17
CTL pb-sw
ON
:
‐ Start of refuel, (associated with refuel green light illumination on wing )
‐ Auto shut off occurs when the selected load is reached or in case of HI level
detection
‐ VALVE light comes amber if REFUEL VALVE CTL switch are not at NORM
position (on refueling control panel).
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FCOM
←C→
DSC-28-20 P 6/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
Off
:
Refuel stops. The selected load can be reset.
Ident.: DSC-28-20-D-00020294.0001001 / 21 MAR 17
CKPT light
Comes on when PWR pb-sw switch is ON associated with the CKPT light on the external refuel
control panel.
ECAM FUEL PAGE
Applicable to: ALL
Ident.: DSC-28-20-F-00020188.0004001 / 17 MAR 17
Ident.: DSC-28-20-F-00020213.0001001 / 17 MAR 17
WING PUMP INDICATIONS
Inline - Green
“LO” - Amber
Crossline - Amber
:
:
:
Pump pressure is normal (pump contactor on).
Pump pressure is low (pump contactor on).
Pump contactor is off.
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FCOM
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DSC-28-20 P 7/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-28-20-F-00020214.0002001 / 17 MAR 17
CTR TANKS PUMPS INDICATIONS
Inline - Green
“LO” - Amber
Crossline - Green
Crossline - Amber
:
:
:
:
Pump pressure is normal (pump contactor on).
Pump pressure is low (pump contactor on).
Pump contactor is off, and auto shut-off is required.
Pump contactor is off, and auto shut-off is not required.
Ident.: DSC-28-20-F-00020216.0001001 / 17 MAR 17
LP VALVE (ENG) INDICATIONS
Inline - Green
Inline - Amber
Crossline - Amber
Transit - Amber
:
:
:
:
The valve is open.
The valve is open, with the ENG MASTER switch OFF.
The ENG valve is fully closed.
The valve is in transit.
Ident.: DSC-28-20-F-00020217.0001001 / 17 MAR 17
X FEED INDICATIONS
Inline - Green
Inline - Amber
Crossline - Green
Crossline - Amber
Transit - Amber
:
:
:
:
:
The valve is open.
The valve is open, with X Feed pb off.
The valve is closed.
The valve is closed with X feed pb ON.
The valve is in transit.
Ident.: DSC-28-20-F-00020218.0002001 / 17 MAR 17
TRANSFER VALVE INDICATIONS
Outer to Inner Transfer
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-28-20 P 8/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
Ident.: DSC-28-20-F-00020219.0001001 / 17 MAR 17
APU INDICATIONS
Ident.: DSC-28-20-F-00020220.0001001 / 17 MAR 17
FUEL TEMPERATURE INDICATION
This appears when its associated temperature sensor is wet. It is normally in green.
An advisory only appears in phases 2 and 6, when the fuel temperature is:
‐ Above 45 °C for the inner cell, or 55 °C for the outer cell.
‐ Below -40 °C.
It becomes amber, and the ECAM displays a caution, if the temperature goes above the high limit
or below the low limit.
Ident.: DSC-28-20-F-00020221.0002001 / 17 MAR 17
FUEL QUANTITY INDICATION
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FCOM
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DSC-28-20 P 9/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
‐ It is normally in green.
‐ The units may either be in KG or LB, depending on the DMC pin program.
‐ Two dashes appear across the last two digits when the FQI is inaccurate (Refer to DSC-28-20
Total Fuel Indication).
Ident.: DSC-28-20-F-00020340.0001001 / 17 MAR 17
FUEL QUANTITY - BOXED INDICATIONS
‐ The outer indication is boxed amber, if both transfer valves fail to open when the inner is at low
level.
‐ The center tank indication is boxed amber, if both center tank pumps are failed, or are switched
OFF.
Ident.: DSC-28-20-F-00020345.0001001 / 17 MAR 17
FUEL QUANTITY - ADVISORY
An advisory appears in flight phases 2 and 6, when the difference between the fuel quantities in
the two wings is greater than 1 500 kg (3 300 lb). The wing inner and outer tank indications pulse
with the highest fuel level.
Ident.: DSC-28-20-F-00020346.0003001 / 17 MAR 17
FUEL ON BOARD (FOB) INDICATION
It is normally in green. It indicates the total of all tanks (Including the ACTs ).
Two dashes appear across the last two digits when the FQI is inaccurate (Refer to DSC-28-20
Total Fuel Indication).
Units may either be in KG or LB, depending on the DMC pin program.
The indication is half-boxed in amber, if:
‐ Center tank pumps fail, or are switched OFF.
‐ Both transfer valves fail to open, when the inner tank is at low level.
‐ Any ACT is not usable.
Ident.: DSC-28-20-F-00020347.0001001 / 17 MAR 17
FUEL USED INDICATION
‐ The engine identification number is in amber, when the engine is below idle. It is in white color,
when it is at, or above, idle.
‐ The fuel used indication is green from flight phase 2, until electrical power is cut off at the end of
the flight. It is automatically reset, when the engine is started on ground.
‐ Units may either be in KG or LB, depending on the DMC pin program.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-28-20 P 10/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
Ident.: DSC-28-20-F-00020348.0002001 / 17 MAR 17
ACT TO CENTER TANK FUEL TRANSFER INDICATION
‐
‐
‐
‐
‐
‐
It is normally in green.
The ACT quantity is displayed in a grey box.
This box becomes amber in case of a transfer fault.
ACT 1 is indicated on the left and ACT 2 is indicated on the right.
Units may either be in KG or LB, depending on the DMC pin program.
A triangle indicates that the fuel transfer to the center tank has started:
▵
: Green, when the automatic transfer begins.
▴
: Fully green, when the manual transfer begins.
Ident.: DSC-28-20-F-00020351.0001001 / 17 MAR 17
FUEL FLOW INDICATION
The Total Fuel Flow is displayed in KG/MIN or LB/MIN.
Units may either be in KG or LB, depending on the DMC pin program.
‐ It is normally in green.
‐ It is replaced by an amber XX if there is no valid data.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
DSC-28-20 P 11/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
ECAM UPPER DISPLAY
Applicable to: ALL
Ident.: DSC-28-20-E-00020189.0002001 / 17 MAR 17
Ident.: DSC-28-20-E-00020193.0001001 / 17 MAR 17
TOTAL FUEL INDICATION
An amber half box appears around FOB, when the displayed quantity is not all usable (intercell
transfer valve failure or loss of center tank pumps).
Units may either be in KG or LB, depending on the DMC pin program.
If the FOB indication is displayed with two dashes across the two least significant digits, the FQI
is in degraded mode. In this case, the ECAM FUEL page can be called on ECAM lower display to
determine which tank is affected.
The loss of accuracy resulting from the loss of FQI normal mode is as follows :
Wing outer tank affected : +20 kg (+44 lb), –200 kg (–440 lb).
Wing inner tank affected : ±110 kg (240 lb).
Center tank affected
: ±130 kg (290 lb).
All tanks affected
: +390 kg (+860 lb), –750 kg (–1660 lb).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
DSC-28-20 P 12/14
22 MAR 17
AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-28-20-E-00020194.0001001 / 17 MAR 17
MEMO DISPLAY
Memos are normally in green color, but they may be in amber color in abnormal situations.
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-28-20-A-00016777.0001001 / 21 MAR 16
CTR TK FEEDG
:
This memo appears in green, if at least one center tank pump is
energized.
Ident.: DSC-28-20-A-00016778.0001001 / 21 MAR 16
FUEL X FEED
:
This memo appears in green, if the fuel X FEED pb-sw is ON, and
the X FEED valve is not fully closed. It appears in amber in flight
phases 3,4, or 5.
Ident.: DSC-28-20-A-00016776.0001001 / 21 MAR 16
OUTR TK FUEL XFRD
:
This memo appears in green, if at least one transfer valve is open
in one wing tank.
Ident.: DSC-28-20-A-00016779.0001001 / 21 MAR 16
REFUELG
:
This memo appears in green, when :
‐ The door of the refuel control panel on the fuselage or on
the wing is open, or
‐ The PWR pb-sw of the refuel control panel in the cockpit is
ON.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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← E to F
DSC-28-20 P 13/14
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AIRCRAFT SYSTEMS
FUEL
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
HYDRAULIC
Intentionally left blank
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-29-10 Description
DSC-29-10-10 General
General.....................................................................................................................................................................A
DSC-29-10-20 Generation
Green System Pump............................................................................................................................................... A
Blue System Pumps................................................................................................................................................ B
Yellow System Pumps.............................................................................................................................................C
Power Transfer Unit (PTU)......................................................................................................................................D
Ram Air Turbine (RAT)........................................................................................................................................... E
System Accumulators.............................................................................................................................................. F
Priority Valves..........................................................................................................................................................G
Fire Shutoff Valves.................................................................................................................................................. H
Leak Measurement Valves....................................................................................................................................... I
Filters........................................................................................................................................................................ J
Generation................................................................................................................................................................K
Reservoir Pressurization.......................................................................................................................................... L
Indications................................................................................................................................................................M
DSC-29-10-30 Distribution
Distribution............................................................................................................................................................... A
DSC-29-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Maintenance Panel.................................................................................................................................................. B
ECAM HYD Page.................................................................................................................................................... C
Memo Display.......................................................................................................................................................... D
GLG A318/A319/A320/A321 For A/C: HC-CRU
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DSC-29-PLP-TOC P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
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24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-29-10-10-00001133.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft has three continuously operating hydraulic systems : blue, green, and yellow. Each
system has its own hydraulic reservoir. Normal system operating pressure is 3 000 PSI (2 500 PSI
when powered by the RAT). Hydraulic fluid cannot be transferred from one system to another.
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AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW
OPERATING MANUAL
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DSC-29-10-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
DESCRIPTION - GENERATION
FLIGHT CREW
OPERATING MANUAL
GREEN SYSTEM PUMP
Ident.: DSC-29-10-20-00001134.0001001 / 21 MAR 16
Applicable to: ALL
A pump driven by engine 1 pressurizes the green system.
BLUE SYSTEM PUMPS
Ident.: DSC-29-10-20-00001135.0001001 / 21 MAR 16
Applicable to: ALL
An electric pump pressurizes the blue system. A pump driven by a ram air turbine (RAT) pressurizes
this system in an emergency.
YELLOW SYSTEM PUMPS
Ident.: DSC-29-10-20-00001136.0001001 / 21 MAR 16
Applicable to: ALL
A pump driven by engine 2 pressurizes the yellow system.
An electric pump can also pressurize the yellow system, which allows yellow hydraulics to be used
on the ground when the engines are stopped.
Crew members can also use a hand pump to pressurize the yellow system in order to operate the
cargo doors when no electrical power is available.
POWER TRANSFER UNIT (PTU)
Ident.: DSC-29-10-20-00001137.0001001 / 21 MAR 16
Applicable to: ALL
A bidirectional power transfer unit enables the yellow system to pressurize the green system and vice
versa.
The power transfer unit comes into action automatically when the differential pressure between the
green and the yellow systems is greater than 500 PSI.
The PTU therefore allows the green system to be pressurized on the ground when the engines are
stopped.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to D →
DSC-29-10-20 P 1/6
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
DESCRIPTION - GENERATION
FLIGHT CREW
OPERATING MANUAL
RAM AIR TURBINE (RAT)
Ident.: DSC-29-10-20-00001138.0001001 / 21 MAR 16
Applicable to: ALL
A drop-out RAT coupled to a hydraulic pump allows the blue system to function if electrical power is
lost or both engines fail. The RAT deploys automatically if AC BUS 1 and AC BUS 2 are both lost. It
can be deployed manually from the overhead panel. It can be stowed only when the aircraft is on the
ground.
SYSTEM ACCUMULATORS
Ident.: DSC-29-10-20-00001139.0001001 / 21 MAR 16
Applicable to: ALL
An accumulator in each system helps to maintain a constant pressure by covering transient demands
during normal operation.
PRIORITY VALVES
Ident.: DSC-29-10-20-00001141.0001001 / 21 MAR 16
Applicable to: ALL
Priority valves cut off hydraulic power to heavy load users if hydraulic pressure in a system gets low.
FIRE SHUTOFF VALVES
Ident.: DSC-29-10-20-00001142.0001001 / 21 MAR 16
Applicable to: ALL
Each of the green and yellow systems has a fire shutoff valve in its line upstream of its engine-driven
pump. The flight crew can close it by pushing the ENG 1(2) FIRE pushbutton.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-29-10-20 P 2/6
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
DESCRIPTION - GENERATION
FLIGHT CREW
OPERATING MANUAL
LEAK MEASUREMENT VALVES
Ident.: DSC-29-10-20-00001143.0001001 / 21 MAR 16
Applicable to: ALL
Each system has a leak measurement valve upstream of the primary flight controls.
These valves, which measure the leakage in each circuit, are closed by operation of the LEAK
MEASUREMENT VALVES pushbutton switch on the maintenance panel.
FILTERS
Ident.: DSC-29-10-20-00001144.0001001 / 21 MAR 16
Applicable to: ALL
L3
Filters clean the hydraulic fluid as follows :
‐ HP filters on each system and on the reservoir filling system and the normal braking system
‐ return line filters on each line
‐ case drain filters on engine pumps and the blue electric pump (which permit maintenance crew to
monitor pump wear by inspecting the filters for the presence of metallic particles).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I to J
DSC-29-10-20 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
DESCRIPTION - GENERATION
FLIGHT CREW
OPERATING MANUAL
GENERATION
Ident.: DSC-29-10-20-00001145.0001001 / 08 FEB 13
Applicable to: ALL
RESERVOIR PRESSURIZATION
Ident.: DSC-29-10-20-00001146.0001001 / 08 FEB 13
Applicable to: ALL
Normally, HP bleed air from engine 1 pressurizes the hydraulic reservoirs automatically.
If the bleed air pressure is too low, the system takes bleed air pressure from the crossbleed duct.
The systems maintain a high enough pressure to prevent their pumps from cavitating.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K to L →
DSC-29-10-20 P 4/6
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DESCRIPTION - GENERATION
←L
DSC-29-10-20 P 5/6
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
DESCRIPTION - GENERATION
FLIGHT CREW
OPERATING MANUAL
INDICATIONS
Ident.: DSC-29-10-20-00001147.0002001 / 09 OCT 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
M
DSC-29-10-20 P 6/6
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
DESCRIPTION - DISTRIBUTION
FLIGHT CREW
OPERATING MANUAL
DISTRIBUTION
Ident.: DSC-29-10-30-00001148.0003001 / 08 FEB 13
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-29-10-30 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
DESCRIPTION - DISTRIBUTION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-29-20-00001149.0001001 / 21 MAR 16
Applicable to: ALL
(1)
ENG 1 (2) PUMP pb
On
: The pump pressurizes the system when the engine is running.
OFF
: The pump is depressurized. The generation of hydraulic power stops.
FAULT lt : This amber light comes on, and the ECAM caution appears, if :
‐ The reservoir level is low
‐ The reservoir overheats
‐ The reservoir air pressure is low
‐ The pump pressure is low (inhibited on the ground, when the engine is
stopped).
This light goes out, when the crew selects OFF, except during an overheat. (The
light stays on as long as the overheat lasts).
(2)
BLUE ELEC PUMP pb (guarded)
AUTO
: If AC power is available, the electric pump operates :
‐ In flight
‐ On the ground, if one engine is running or if the crew has pressed the BLUE
PUMP OVRD pushbutton on the maintenance panel.
OFF
: The pump is de-energized.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-29-20 P 1/8
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
FAULT lt :
This amber light comes on, and a caution appears on the ECAM, if :
‐ The reservoir level is low
‐ The reservoir overheats
‐ The air pressure in the reservoir is low
‐ The pump is delivering low pressure (inhibited on the ground, when the
engines are stopped)
‐ The pump overheats.
The light goes out, when the crew selects OFF, except during an overheat. (The
light stays on as long as the overheat lasts).
(3)
YELLOW ELEC PUMP pb sw (springloaded)
ON
: The electric pump is ON.
If the electrical power supply is removed, the pump will remain off when
electrical power is applied again.
Off
: The pump is off.
It comes on automatically when a crewman sets the lever of the cargo door
manual selector valve to OPEN or CLOSE.
This inhibits the operation of other yellow system functions (except alternate
braking and engine 2 reverse).
FAULT lt : This amber light, accompanied by an ECAM caution, comes on if :
‐ the reservoir level is low
‐ air pressure in the reservoir is low
‐ the reservoir overheats
‐ pump pressure is low
‐ the pump overheats.
The light goes out when the crew selects OFF, except during an overheat. (The
light stays on as long as the overheat lasts).
(4)
PTU pb sw
AUTO
:
The bidirectional power transfer unit is armed and both the yellow and the green
electrohydraulic valves are open.
The power transfer unit runs automatically when the differential pressure
between the green and yellow systems is more than 500 PSI.
Note:
OFF
:
The PTU is inhibited during the first engine start and automatically
tested during the second engine start.
Both the green and the yellow PTU electrohydraulic valves close. Power transfer
stops.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←A→
DSC-29-20 P 2/8
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AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FAULT lt :
(5)
CONTROLS AND INDICATORS
This amber light comes on, and a caution appears on the ECAM, if :
‐ the green or the yellow reservoir overheats
‐ the green or the yellow reservoir has low air pressure
‐ the green or the yellow reservoir has a low flluid level.
The light goes out when the crew selects OFF, except during an overheat. (The
light stays on as long as the overheat lasts).
RAT MAN ON pb
The flight crew may extend the RAT at any time by pressing the RAT MAN ON pushbutton.
Note:
The RAT extends automatically if AC BUS 1 and AC BUS 2 are lost. (Refer to
DSC-24-20 Overhead Panel (Cont'd)).
MAINTENANCE PANEL
Ident.: DSC-29-20-00001150.0001001 / 21 MAR 16
Applicable to: ALL
(1)
BLUE PUMP OVRD pb sw (guarded)
ON : The blue electric pump is on if the ELEC PUMP pushbutton switch on the HYD panel
is at AUTO.
Off : The blue electric pump is off.
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DSC-29-20 P 3/8
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AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(2)
CONTROLS AND INDICATORS
LEAK MEASUREMENT VALVES pb sw (guarded)
OFF: The corresponding electrohydraulic valve closes and shuts off hydraulic supply to the
primary flight controls.
On : The corresponding electrohydraulic valve opens to go back to normal hydraulic
supply.
ECAM HYD PAGE
Ident.: DSC-29-20-00001151.0002001 / 23 JUN 15
Applicable to: ALL
(1)
Reservoir quantity
It is in green, unless the fluid level goes below the warning level, in which case it becomes
amber.
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FCOM
← B to C →
DSC-29-20 P 4/8
24 JAN 17
AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(2)
Reservoir LO AIR PRESS
This appears in amber, and a caution appears on ECAM, if the air pressure for the indicated
reservoir drops below normal.
(3)
Reservoir OVHT
This appears in amber, and a caution appears on ECAM, if the temperature of returning
hydraulic fluid temperature at the inlet to its reservoir is above normal.
(4)
FIRE VALVE
Cross line - Amber :
In line - Green
:
(5)
OVHT
This appears in amber if the electric pump for that system (blue or yellow) overheats.
(6)
RAT
RAT ▹ White
RAT Green
RAT ▸ Amber
The valve is fully closed.
The valve is not fully closed.
:
:
The RAT is stowed.
The RAT is not stowed.
:
Pressure for stowing the RAT has been applied, or the RAT pump is
not available.
(7)
ELEC
This legend, normally white, becomes amber if the associated power supply fails.
(8)
YELLOW ELEC PUMP control
◃ White
: The electric pump is off.
:
The electric pump is ON.
Green
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DSC-29-20 P 5/8
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AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
◂ Amber
(9)
:
The electric pump is ON and the yellow system has low pressure.
PTU control
(1)
(2)
(3)
Green :
Amber :
The power transfer unit (PTU ) pushbutton switch is in AUTO and the PTU is
not transferring pressure.
The PTU pb-sw is OFF.
Green :
The PTU is supplying the green hydraulic system.
Green :
The PTU is supplying the yellow hydraulic system.
(10) ENG PUMP control and low pressure indication
In line (Green)
: The pushbutton switch for the designated PUMP is on and hydraulic
pressure is normal.
Cross line (Amber) : The pushbutton switch for the designated PUMP is OFF.
“LO” (Amber)
: The pushbutton switch for the designated PUMP is on and hydraulic
pressure is low.
(11) System label
YELLOW
▵
pressure > 1 450 PSI
white
green
pressure < 1 450 PSI
amber
amber
(12) System pressure
This legend, normally green, becomes amber when system pressure is below 1 450 PSI.
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DSC-29-20 P 6/8
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AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(13) PUMP
This legend, normally white, becomes amber when N2 is below idle.
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-29-20-A-00016787.0001001 / 21 MAR 16
HYD PTU
:
This memo appears in green, when the power transfer unit is running.
Ident.: DSC-29-20-A-00016786.0001001 / 21 MAR 16
RAT OUT
:
This memo appears in green, if the Ram Air Turbine is not fully stowed. The
color changes to amber during flight phases 1 and 2.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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DSC-29-20 P 7/8
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AIRCRAFT SYSTEMS
HYDRAULIC
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
ICE AND RAIN PROTECTION
Intentionally left blank
AIRCRAFT SYSTEMS
ICE AND RAIN PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-30-10 General
DSC-30-10-10 Description
General.....................................................................................................................................................................A
Anti-Ice..................................................................................................................................................................... B
Rain Removal.......................................................................................................................................................... C
DSC-30-20 Wing Anti-Ice
DSC-30-20-10 Description
Description............................................................................................................................................................... A
DSC-30-20-20 Controls And Indicators
Overhead Panel....................................................................................................................................................... A
ECAM BLEED Page................................................................................................................................................ B
Memo Display.......................................................................................................................................................... C
DSC-30-30 Engine Anti-Ice
DSC-30-30-10 Description
Description............................................................................................................................................................... A
DSC-30-30-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Memo Display.......................................................................................................................................................... B
DSC-30-40 Window Heat
DSC-30-40-10 Description
Description............................................................................................................................................................... A
DSC-30-40-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
DSC-30-50 Probes Heat
DSC-30-50-10 Description
Description............................................................................................................................................................... A
DSC-30-50-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Continued on the following page
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AIRCRAFT SYSTEMS
ICE AND RAIN PROTECTION
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FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-30-60 Rain Removal
DSC-30-60-10 Description
Continued from the previous page
Wipers...................................................................................................................................................................... A
Rain Repellent ................................................................................................................................................B
DSC-30-60-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Rain Repellent System Indicators..................................................................................................................B
DSC-30-70 Ice Detection System
DSC-30-70-10 Description
Visual Ice Indicator.................................................................................................................................................. A
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GENERAL - DESCRIPTION
GENERAL
Ident.: DSC-30-10-10-00001154.0001001 / 16 MAR 11
Applicable to: ALL
The ice and rain protection system allows unrestricted operation of the aircraft in icing conditions and
heavy rain.
ANTI-ICE
Ident.: DSC-30-10-10-00001155.0001001 / 29 MAR 12
Applicable to: ALL
Either hot air or electrical heating protects critical areas of the aircraft as follows:
HOT AIR
‐ Three outboard leading-edge slats of each wing
‐ Engine air intakes.
ELECTRICAL HEATING
‐ Flight compartment windows
‐ Sensors, pitot probes and static ports
‐ Waste-water drain mast.
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GENERAL - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
RAIN REMOVAL
Ident.: DSC-30-10-10-00017416.0001001 / 21 MAR 16
Applicable to: ALL
Wipers and fluid rain repellent , remove rain from the front windshield panels.
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ICE AND RAIN PROTECTION
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WING ANTI-ICE - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-30-20-10-00017417.0001001 / 21 MAR 16
Applicable to: ALL
In flight, hot air from the pneumatic system heats the three outboard slats (3-4-5) of each wing.
Air is supplied through one valve in each wing.
The WING pushbutton on the ANTI ICE panel controls the valves.
When the aircraft is on ground, the flight crew can initiate a 30 s test sequence by turning the system
ON.
If the system detects a leak during normal operation, the affected side’s wing anti-ice valve
automatically closes (Refer to DSC-36-10-50 Leak Detection).
When wing anti-ice is selected, the N1 or EPR limit is automatically reduced, and the idle N1 or EPR
is automatically increased.
If the electrical power supply fails, the valves close.
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←A
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AIRCRAFT SYSTEMS
ICE AND RAIN PROTECTION
A318/A319/A320/A321
WING ANTI-ICE - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-30-20-20-00017418.0001001 / 21 MAR 16
Applicable to: ALL
(1)
WING ANTI ICE pb sw
This switch controls the wing anti ice system on the left and right sides simultaneously.
Off
: ON light goes off.
Wing anti-icing control valves close.
FAULT : Light comes on amber, and caution appears on ECAM, if:
‐ The position of the anti-icing control valve is not the required position, or
‐ Low pressure is detected.
Note:
ON
:
The amber FAULT light comes on briefly as the valves transit.
Light comes on blue.
WING A. ICE appears on the ECAM MEMO page.
Wing anti ice control valves open if a pneumatic supply is available.
On the ground the wing anti-icing control valves open for 30 s only (test sequence).
ECAM BLEED PAGE
Ident.: DSC-30-20-20-00001159.0001001 / 21 MAR 16
Applicable to: ALL
Refer to DSC-36-20 ECAM Bleed Page
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-30-20-20-A-00016939.0001001 / 21 MAR 16
WING A.ICE
:
This memo appears in green, if the WING ANTI ICE pb-sw is ON.
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ICE AND RAIN PROTECTION
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ENGINE ANTI-ICE - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-30-30-10-00017422.0001001 / 21 MAR 16
Applicable to: ALL
An independent air bleed from the high pressure compressor protects each engine nacelle from ice.
Air is supplied through a two-position (open and closed) valve that the flight crew controls with two
pushbuttons, one for each engine.
The valve automatically closes, if air is unavailable (engine not running).
When an engine anti-ice valve is open, the N1 or EPR limit is automatically reduced and, if
necessary, the idle N1 or EPR is automatically increased for both engines in order to provide the
required pressure.
If electrical power fails, the valves open.
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ENGINE ANTI-ICE - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-30-30-20-00017425.0003001 / 21 MAR 16
Applicable to: ALL
(1)
ENG 1 (2) ANTI ICE pb-sw
Off
: ON light goes off.
Engine anti-ice valve closes.
FAULT : Light comes on amber, and caution message appears on ECAM, if the position of
the anti-ice valve disagrees with the ENG 1 (2) pushbutton selection.
Note:
ON
:
The amber FAULT light comes on briefly as valve transits.
Light comes on blue.
ECAM MEMO displays “ENG A. ICE”.
Engine anti-icing valve opens if bleed air is available from the engine.
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-30-30-20-A-00016945.0001001 / 21 MAR 16
ENG A.ICE
:
This memo appears in green, if one or both ENG ANTI ICE pb-sw are ON.
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WINDOW HEAT - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-30-40-10-00017458.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft uses electrical heating for anti-icing each windshield and defogging the cockpit side
windows.
Two independent Window Heat Computers (WHCs), one on each side, automatically regulate the
system, protect it against overheating, and indicate faults.
Window heating comes on:
‐ automatically when at least one engine is running, or when the aircraft is in flight.
‐ manually, before engine start, when the flight crew switches ON the PROBE/WINDOW HEAT
pushbutton switch.
Windshield heating operates at low power on the ground and at normal power in flight. The
changeover is automatic.
Only one heating level exists for the windows.
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FLIGHT CREW
OPERATING MANUAL
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WINDOW HEAT - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-30-40-20-00001165.0001001 / 21 MAR 16
Applicable to: ALL
Refer to DSC-30-50-20 Overhead Panel
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PROBES HEAT - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-30-50-10-00017459.0001001 / 21 MAR 16
Applicable to: ALL
Electrical heating protects:
‐ Pitot probes
‐ Static ports
‐ Angle-Of-Attack (AOAs) probes
‐ Total Air Temperature (TAT) probes.
Three independent Probe Heat Computers (PHCs) automatically control and monitor:
‐ Captain probes
‐ F/O probes
‐ STBY probes.
They protect against overheating and indicate faults.
The probes are heated:
‐ Automatically when at least one engine is running, or when the aircraft is in flight.
‐ Manually, when the flight crew switches ON the PROBE/WINDOW HEAT pb.
On the ground, the TAT probes are not heated and pitot heating operates at a low level (the
changeover to normal power in flight is automatic).
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FLIGHT CREW
OPERATING MANUAL
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OPERATING MANUAL
PROBES HEAT - CONTROLS AND INDICATORS
OVERHEAD PANEL
Ident.: DSC-30-50-20-00017460.0001001 / 21 MAR 16
Applicable to: ALL
(1)
PROBE/WINDOW HEAT pb
AUTO : Probes/Windows are heated automatically :
‐ In flight, or
‐ On the ground (except TAT probes) provided one engine is running.
ON
: Light comes on blue. Probes and windows are heated permanently.
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RAIN REMOVAL - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
WIPERS
Ident.: DSC-30-60-10-00017461.0001001 / 21 MAR 16
Applicable to: ALL
Each front windshield has an electrical wiper with two speeds, and with an intermittent sweep
function . A rotary selector controls each wiper.
RAIN REPELLENT
Ident.: DSC-30-60-10-00017462.0001001 / 01 JUN 17
Applicable to: ALL
In moderate to heavy rain, the flight crew can spray a rain repellent liquid on the windshield to
improve visibility.
After about 30 s, the windows are covered with spray.
Separate pushbuttons control rain repellent application on each side of the windshield.
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FLIGHT CREW
OPERATING MANUAL
RAIN REMOVAL - CONTROLS AND INDICATORS
OVERHEAD PANEL
Ident.: DSC-30-60-20-00017466.0001001 / 21 MAR 16
Applicable to: ALL
(1)
WIPER rotary selector
Each rotary selector controls its wiper at low speed, high speed, or intermittent sweeping .
When turned off, the wiper stops out of view.
(2)
RAIN RPLNT pb-sw
Each of these buttons controls the application of rain repellent fluid to the corresponding side of
the front windshield.
When the flight crew pushes the button, the timer applies a measured quantity of rain repellent
to the windshield. To repeat the cycle, the flight crew must push the button again.
This function is inhibited when the aircraft is on the ground and the engines are stopped.
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OPERATING MANUAL
RAIN REMOVAL - CONTROLS AND INDICATORS
RAIN REPELLENT SYSTEM INDICATORS
Ident.: DSC-30-60-20-00017587.0001001 / 21 MAR 16
Applicable to: ALL
(1)
Rain Repellent pressure indicator
This gauge shows the nitrogen pressure and therefore the remaining fluid in the rain repellent
bottle. When the needle is in the yellow sector the bottle should be replaced.
(2)
Rain Repellent low level indicator (depending on aircraft configuration)
When the REFILL float is in view the bottle should be replaced.
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ICE DETECTION SYSTEM - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
VISUAL ICE INDICATOR
Ident.: DSC-30-70-10-00017471.0001001 / 21 MAR 16
Applicable to: ALL
An external visual ice indicator is installed between the two windshields.
There can be also an external ice detector light
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FLIGHT CREW
OPERATING MANUAL
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INDICATING/RECORDING SYSTEMS
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-31-05 EIS General
DSC-31-05-10 Introduction
Introduction...............................................................................................................................................................A
DSC-31-05-20 Cockpit Arrangement
Cockpit Arrangement............................................................................................................................................... A
DSC-31-05-30 Architecture
Display Unit (DU).....................................................................................................................................................A
Display Management Computer (DMC).................................................................................................................. B
System Data Acquisition Concentrator (SDAC)......................................................................................................C
Flight Warning Computer (FWC).............................................................................................................................D
Attention - Getters................................................................................................................................................... E
Loudspeaker.............................................................................................................................................................F
EIS Block Diagram.................................................................................................................................................. G
DSC-31-05-40 Controls and Switching
ECAM Control Panel (ECP).................................................................................................................................... A
EIS DMC Switching Selector...................................................................................................................................B
ECAM/ND Switching................................................................................................................................................C
EFIS Switching........................................................................................................................................................ D
DSC-31-05-50 Reconfiguring the DMC
Reconfiguring the Display Management Computer (DMC).....................................................................................A
DSC-31-05-60 Reconfiguring DUs
Failure of Upper ECAM DU (or CTL/Brightness Knob Turned to Off).................................................................... A
Failure of Lower ECAM DU (or CTL/Brightness Knob Turned to Off).................................................................... B
Failure of both ECAM DUs..................................................................................................................................... C
PFDU/NDU Reconfiguration.................................................................................................................................... D
DU Reconfiguration..................................................................................................................................................E
General.....................................................................................................................................................................F
Failure of a DU........................................................................................................................................................G
Feedback Messages................................................................................................................................................H
Side1/Side2 Discrepancy Messages.........................................................................................................................I
DU Reset.................................................................................................................................................................. J
Continued on the following page
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
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OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-31-10 ECAM Description
Continued from the previous page
ECAM DU Arrangement.......................................................................................................................................... A
Color Code...............................................................................................................................................................B
Warning/Caution Classification................................................................................................................................C
Priority Rules........................................................................................................................................................... D
Types of Failures..................................................................................................................................................... E
Audio Indicators....................................................................................................................................................... F
DSC-31-15 Indications on E/WD
General.....................................................................................................................................................................A
Independent Failure................................................................................................................................................. B
Primary and Secondary Failure...............................................................................................................................C
Flight Phases........................................................................................................................................................... D
Memos......................................................................................................................................................................E
Configuration Warnings............................................................................................................................................F
DSC-31-20 Indications on SD
General.....................................................................................................................................................................A
System Pages..........................................................................................................................................................B
Status Page............................................................................................................................................................. C
Permanent Data.......................................................................................................................................................D
Amber Crosses "XX" on the SD..............................................................................................................................E
Amber dashes on the SD........................................................................................................................................F
DSC-31-25 ECAM Sequence
DSC-31-25-10 General
General.....................................................................................................................................................................A
DSC-31-25-20 Example
1 - The Ecam Detects No Failure........................................................................................................................... A
2 - The ECAM Detects a Failure............................................................................................................................ B
3 - The Flight Crew Follows the Instruction Displayed on the E/WD......................................................................C
4 - One of the Pilots Pushes the CLR Pushbutton on the ECP............................................................................. D
5 - One of the Pilots Pushes the CLR Pushbutton a Second Time........................................................................E
6 - One of the Pilots Pushes the CLR Pushbutton a Third Time............................................................................F
DSC-31-27 OEB Reminder
General.....................................................................................................................................................................A
Description............................................................................................................................................................... B
OEB Database.........................................................................................................................................................C
Continued on the following page
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INDICATING/RECORDING SYSTEMS
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OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-31-30 ECAM Controls
Continued from the previous page
ECAM Control Panel............................................................................................................................................... A
Switching Panel....................................................................................................................................................... B
Attention Getters......................................................................................................................................................C
Memo Display.......................................................................................................................................................... D
DSC-31-40 Indications on PFD
General.....................................................................................................................................................................A
Specific Ground Indications.....................................................................................................................................B
Attitude Data............................................................................................................................................................ C
Airspeed................................................................................................................................................................... D
Altitude..................................................................................................................................................................... E
Altitude (CONT'D).................................................................................................................................................... F
Vertical Speed......................................................................................................................................................... G
Heading....................................................................................................................................................................H
Flight Path Vector..................................................................................................................................................... I
Guidance...................................................................................................................................................................J
Trajectory Deviation................................................................................................................................................. K
Flight Mode Annunciator.......................................................................................................................................... L
Tailstrike Pitch Limit Indicator ........................................................................................................................M
Altitude Alert............................................................................................................................................................ N
Flags and Messages Displayed on PFD................................................................................................................ O
DSC-31-45 Indications on ND
General.....................................................................................................................................................................A
ROSE Modes........................................................................................................................................................... B
ROSE LS Mode.......................................................................................................................................................C
Rose VOR Mode..................................................................................................................................................... D
ROSE NAV Mode/ARC Mode................................................................................................................................. E
Plan Mode................................................................................................................................................................ F
Weather Radar indications......................................................................................................................................G
PWS indications............................................................................................................................................. H
EGPWS..................................................................................................................................................................... I
Flags and Messages Displayed on ND................................................................................................................... J
DSC-31-50 EFIS Controls
EFIS Control Panel..................................................................................................................................................A
Other EFIS Controls................................................................................................................................................ B
Chronometer............................................................................................................................................................ C
Continued on the following page
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PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-31-55 Clock
DSC-31-55-10 General
Continued from the previous page
General.....................................................................................................................................................................A
DSC-31-55-20 Controls and Indicators
General.....................................................................................................................................................................A
Operation in Internal Mode......................................................................................................................................B
DSC-31-60 FLT Recorders
DSC-31-60-10 Flight Data Recording System
Description............................................................................................................................................................... A
DSC-31-60-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Pedestal................................................................................................................................................................... B
DSC-31-60-30 Aircraft Integrated Data System
Description............................................................................................................................................................... A
Controls On Pedestal.............................................................................................................................................. B
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EIS GENERAL - INTRODUCTION
FLIGHT CREW
OPERATING MANUAL
INTRODUCTION
Ident.: DSC-31-05-10-00001182.0001001 / 21 MAR 16
Applicable to: ALL
The Electronic Instrument System (EIS ) presents data on six identical Display Units (DUs):
‐ The Electronic Flight Instrument System (EFIS ) displays mostly flight parameters and navigation
data on the Primary Flight Displays (PFD s) and Navigation Displays (NDs).
‐ The Electronic Centralized Aircraft Monitor (ECAM ) presents data on the Engine/Warning Display
(E/WD ) and System Display (SD) :
• Primary engine indications, fuel quantity, flap and slat position
• Warning and caution alerts, or memos
• Synoptic diagrams of aircraft systems, and status messages
• Permanent flight data
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EIS GENERAL - COCKPIT ARRANGEMENT
FLIGHT CREW
OPERATING MANUAL
COCKPIT ARRANGEMENT
Ident.: DSC-31-05-20-00001183.0001001 / 09 OCT 12
Applicable to: ALL
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EIS GENERAL - ARCHITECTURE
FLIGHT CREW
OPERATING MANUAL
DISPLAY UNIT (DU)
Ident.: DSC-31-05-30-00001184.0002001 / 21 MAR 16
Applicable to: ALL
The instrument panels have six identical units.
These DUs are full-color Liquid Crystal Displays (LCD).
DISPLAY MANAGEMENT COMPUTER (DMC)
Ident.: DSC-31-05-30-00001185.0002001 / 20 DEC 10
Applicable to: ALL
Three identical Display Management Computers (DMC s) obtain data from the different sensors
and computers, and send it to the display units. The display units then generate and display the
applicable images. Each DMC has a single DMC channel, and can simultaneously supply one PFD ,
one ND and both ECAM display units (E/WD and SD).
SYSTEM DATA ACQUISITION CONCENTRATOR (SDAC)
Ident.: DSC-31-05-30-00001186.0001001 / 21 MAR 16
Applicable to: ALL
The two identical SDAC s acquire data, then generate signals. Some of these signals go to the three
DMC s, which use them to generate displays of system pages and engines parameters. Others go to
the flight warning computers, which use them to generate ECAM messages and aural alerts.
FLIGHT WARNING COMPUTER (FWC)
Ident.: DSC-31-05-30-00001187.0001001 / 13 JAN 14
Applicable to: ALL
The two identical FWCs generate alert messages, memos, aural alerts, and synthetic voice
messages. For this purpose they acquire data:
‐ Directly from aircraft sensors, or systems, to generate red warnings
‐ Through the SDACs to generate amber cautions.
The ECAM display units display the alert messages generated by the FWCs.
The FWCs also generate:
‐ Radio height callouts
‐ Decision height callouts
‐ Landing distance and landing speed increments.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to D
DSC-31-05-30 P 1/4
05 SEP 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EIS GENERAL - ARCHITECTURE
FLIGHT CREW
OPERATING MANUAL
ATTENTION - GETTERS
Ident.: DSC-31-05-30-00001188.0001001 / 21 MAR 16
Applicable to: ALL
The FWCs also drive the attention-getters. Each pilot has a set of these on the panel under the
glareshield. They are :
‐ A master warning light, that flashes “MASTER WARN” in red, for red warnings.
‐ A master caution light, that illuminates “MASTER CAUT” in amber, for amber cautions.
LOUDSPEAKER
Ident.: DSC-31-05-30-00001189.0001001 / 21 MAR 16
Applicable to: ALL
The communications loudspeakers announce aural alerts and voice messages, and do so even
when they are turned off.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E to F
DSC-31-05-30 P 2/4
05 SEP 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EIS GENERAL - ARCHITECTURE
FLIGHT CREW
OPERATING MANUAL
EIS BLOCK DIAGRAM
Ident.: DSC-31-05-30-00001190.0002001 / 06 JUL 17
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
DSC-31-05-30 P 3/4
05 SEP 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EIS GENERAL - ARCHITECTURE
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-31-05-30 P 4/4
05 SEP 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EIS GENERAL - CONTROLS AND SWITCHING
FLIGHT CREW
OPERATING MANUAL
ECAM CONTROL PANEL (ECP)
Ident.: DSC-31-05-40-00001191.0001001 / 21 MAR 16
Applicable to: ALL
The ECAM Control Panel, located on the pedestal, includes :
‐ Such E/WD controls, as CLR , STS, and the brightness control knob.
‐ Such SD controls, as ENG, BLEED, PRESS..., system page selector, and the brightness control
knob.
EIS DMC SWITCHING SELECTOR
Ident.: DSC-31-05-40-00001192.0001001 / 22 MAR 16
Applicable to: ALL
A switch near the center of the SWITCHING panel which is located just above the ECAM control
panel, enables the flight crew to replace the Captain or First Officer's Display Management Computer
(DMC 1, or DMC 2) by DMC 3.
ECAM/ND SWITCHING
Ident.: DSC-31-05-40-00001193.0001001 / 21 MAR 16
Applicable to: ALL
A switch on the right-hand side of the SWITCHING panel enables the flight crew to transfer the
ECAM System Display to either the Captain or First Officer's Navigation Display.
EFIS SWITCHING
Ident.: DSC-31-05-40-00001194.0001001 / 21 MAR 16
Applicable to: ALL
A PFD/ND XFR pushbutton on each side console enables the pilot to swap displays to the respective
onside DUs.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to D
DSC-31-05-40 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EIS GENERAL - CONTROLS AND SWITCHING
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-31-05-40 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EIS GENERAL - RECONFIGURING THE DMC
RECONFIGURING THE DISPLAY MANAGEMENT COMPUTER (DMC)
Ident.: DSC-31-05-50-00001195.0002001 / 21 MAR 16
Applicable to: ALL
In normal operation, each DMC drives the following Display Units :
‐ DMC 1 drives the CAPT PFD, CAPT ND and the ECAM DUs.
‐ DMC 2 drives the F/O PFD and F/O ND.
‐ DMC 3 is on standby, ready to drive any DU.
If DMC 1 or 2 fails (the “INVALID DATA” message is displayed on the DU s), the crew manually
selects the DMC 3 source (“CAPT 3” or “F/O 3”).
If DMC 1 fails (or DMC 3, if “CAPT 3” was selected), DMC 2 automatically drives the ECAM.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-31-05-50 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EIS GENERAL - RECONFIGURING THE DMC
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-31-05-50 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EIS GENERAL - RECONFIGURING DUS
FLIGHT CREW
OPERATING MANUAL
FAILURE OF UPPER ECAM DU (OR CTL/BRIGHTNESS KNOB TURNED TO OFF)
Ident.: DSC-31-05-60-00001196.0001001 / 21 MAR 16
Applicable to: ALL
If the upper ECAM display fails, or is switched off :
‐ The engine/warning page automatically replaces the system/status page on the lower ECAM DU.
The flight crew can display the system/status page by :
‐ Using the “ECAM/ND XFR“ switch, on the SWITCHING panel, to move it to a Navigation Display
Unit (NDU), or
‐ Pushing and holding (for a maximum of 3 min) the related system page pushbutton, on the ECAM
control panel, to temporarily display it on the lower ECAM DU (instead of the engine/warning
page).
FAILURE OF LOWER ECAM DU (OR CTL/BRIGHTNESS KNOB TURNED TO OFF)
Ident.: DSC-31-05-60-00001197.0001001 / 21 MAR 16
Applicable to: ALL
If the lower ECAM display fails, or is switched off, the flight crew can display the system/status page
by :
‐ Using the "ECAM/ND XFR" switch, on the SWITCHING panel, to display it on the NDU, or
‐ Pushing and holding (for a maximum of 3 min) the related system page pushbutton, on the ECAM
control panel, to temporarily display it on the upper ECAM DU (instead of the engine/warning
page).
FAILURE OF BOTH ECAM DUs
Ident.: DSC-31-05-60-00001198.0001001 / 21 MAR 16
Applicable to: ALL
If both ECAM displays fail, the flight crew may :
‐ Use the "ECAM/ND XFR", on the SWITCHING panel, to display the engine/warning page on a
navigation display and, if needed,
‐ Push and hold (for a maximum of 3 min) the related system page pushbutton, on the ECAM
control panel, to temporarily display the system/status page on an ND.
PFDU/NDU RECONFIGURATION
Ident.: DSC-31-05-60-00001199.0001001 / 21 MAR 16
Applicable to: ALL
If a PFDU fails, the system automatically transfers the PFD image to the NDU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to D →
DSC-31-05-60 P 1/6
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EIS GENERAL - RECONFIGURING DUS
The pilot can also make this transfer manually by :
‐ turning the PFD ON-OFF/brightness control OFF, or
‐ pressing the PFD/ND/XFR pushbutton, which cross-changes the images between the PFDU and
the NDU.
If an NDU fails, the pilot can use the PFD/ND/XFR pushbutton to transfer the ND image to the PFDU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
DSC-31-05-60 P 2/6
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EIS GENERAL - RECONFIGURING DUS
FLIGHT CREW
OPERATING MANUAL
DU RECONFIGURATION
Ident.: DSC-31-05-60-00001200.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
DSC-31-05-60 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EIS GENERAL - RECONFIGURING DUS
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-31-05-60-00012844.0001001 / 20 DEC 10
Applicable to: ALL
These messages are displayed on either the EFIS or the ECAM Display Unit (DU ) depending on the
current EFIS or ECAM configuration.
FAILURE OF A DU
Ident.: DSC-31-05-60-00012846.0001001 / 20 DEC 10
Applicable to: ALL
If a DU fails, the flight crew may find one of the following displays:
‐ A blank screen with an “F” letter in amber, or
‐ A distorted display, or
‐ A blank screen with the “INVALID DISPLAY UNIT” message in amber.
FEEDBACK MESSAGES
Ident.: DSC-31-05-60-00012847.0001001 / 20 DEC 10
Applicable to: ALL
The DU displays the following messages in amber when the Display Management Computer (DMC )
detects a discrepancy between the parameters obtained by the DMC and the operational parameters
displayed on the DU:
‐ ”CHECK CAPT PFD ” (“CHECK F/O PFD ”) if the discrepancy concerns the PFD parameters
‐ ”CHECK CAPT ND ” (“CHECK F/O ND ”) if the discrepancy concerns the ND parameters
‐ ”CHECK EWD ” if the discrepancy concerns the E/WD parameters
‐ ”CHECK SD ” if the discrepancy concerns the SD parameters.
In addition, if the aircraft is on ground, the “DU NOT MONITORED” message is displayed in amber
when there is only one DMC , instead of two DMC s, that provides the affected DU with feedback
information.
This message means that there is either a DMC test in progress or that there is an EIS failure.
In the case of an EIS failure, a maintenance action is necessary.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F to H
DSC-31-05-60 P 4/6
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EIS GENERAL - RECONFIGURING DUS
FLIGHT CREW
OPERATING MANUAL
SIDE1/SIDE2 DISCREPANCY MESSAGES
Ident.: DSC-31-05-60-00012848.0001001 / 20 DEC 10
Applicable to: ALL
The DU displays the following messages along with a caution on the ECAM E/WD when there is a
discrepancy between the parameters displayed on the Captain’s EFIS and the First Officer’s EFIS:
‐ Both PFD s display the message “CHECK ATT” if there is a discrepancy of at least 5 ° between
the attitude values, pitch and/or roll
‐ Both PFD s display the message “CHECK ALT ” if there is a discrepancy between the altitude
values greater than 250 ft when the flight crew selects a QNH different from STD , or 500 ft when
the flight crew selects a QNH STD
‐ Both PFD s and ND s display the message “CHECK HDG” if there is a discrepancy of at least 5 °
between the heading values.
Note:
The message “CHECK HDG ” flashes for a few seconds on the ND s, and then it remains
steady. If the flight crew selects the PLAN mode on the ND s the message “CHECK HDG”
does not appear.
DU RESET
Ident.: DSC-31-05-60-00012849.0001001 / 20 DEC 10
Applicable to: ALL
In the case of a DU reset, the message “SELF TEST IN PROGRESS” can be displayed in green
and/or the message “WAITING FOR DATA” may be displayed in green during the EIS initialization.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I to J
DSC-31-05-60 P 5/6
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EIS GENERAL - RECONFIGURING DUS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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FCOM
DSC-31-05-60 P 6/6
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
ECAM DU ARRANGEMENT
Ident.: DSC-31-10-00017519.0001001 / 21 MAR 16
Applicable to: ALL
The ECAM has two display units:
‐ One for the engine/warning display (E/WD).
‐ One for the system/status display (SD).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-31-10 P 1/8
12 APR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
COLOR CODE
Ident.: DSC-31-10-00001202.0001001 / 21 MAR 16
Applicable to: ALL
The ECAM display uses a color code that indicates the importance of the failure or the indication.
RED
: The configuration or failure requires immediate action.
AMBER
: The flight crew should be aware of the configuration or failure, but need not take
immediate action.
GREEN
: The item is operating normally.
WHITE
: These titles and remarks guide the flight crew, as they execute various
procedures.
BLUE
: These are actions to be carried out, or limitations.
MAGENTA : These are particular messages that apply to particular pieces of equipment or
situations (inhibition messages, for example).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
DSC-31-10 P 2/8
12 APR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
WARNING/CAUTION CLASSIFICATION
Ident.: DSC-31-10-00001203.0001001 / 21 MAR 16
Applicable to: ALL
FAILURE MODE
LEVEL
Level 3
SIGNIFICATION
AURAL
VISUAL
Continuous
Red warning : The configuration, or
‐ MASTER WARN
Repetitive
failure requires immediate action :
light red flashing or
Chime (CRC) or
‐ Aircraft in dangerous configuration,
specific red light
specific sound or
or limit flight conditions (eg: stall,
‐ Warning message
synthetic voice
o/speed)
(red) on E/WD
‐ Automatic call of
‐ System failure altering flight safety
the relevant system
(eg : Eng fire, excess cab alt)
page on the S/D (1).
Level 2
Amber caution :
The flight crew should be aware of the
configuration or failure, but does not
need to take any immediate action.
However, time and situation permitting,
these cautions should be considered
without delay to prevent any further
degradation of the affected system :
‐ System failure without any direct
consequence on the flight safety
(eg: HYD G SYS LO PR)
Level 1
INFORMATION
ADVISORY
MEMO
(1)
Amber caution : Requires crew
monitoring :
‐ Failures leading to a loss of
redundancy or system degradation
(eg : FCDC fault)
System parameters monitoring
Single Chime
(SC)
NONE
NONE
Information : Recalls normal or
NONE
automatic selection of functions which
are temporarily used
‐ MASTER CAUT
light amber steady
‐ Caution message
(amber) on E/WD
‐ Automatic call of
the relevant system
page on the S/D (1).
‐ Caution message
(amber) on E/WD
generally without
procedure.
‐ Automatic call of
the relevant system
page on the S/D.
The affected
parameter pulses
green.
‐ Green, Amber, or
Magenta message
on E/WD
except in some cases
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-31-10 P 3/8
12 APR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
PRIORITY RULES
Ident.: DSC-31-10-00001204.0001001 / 17 MAR 17
Applicable to: ALL
There are three priority levels for warnings and cautions :
- A level 3 warning has priority over a level 2 caution which has priority over a level 1 caution.
The FWC observes these priorities.
INFORMATION PROVIDED WHEN NEEDED
One of the main advantages of the ECAM is that it displays applicable information to the flight
crew, on an "as needed" basis. The following outlines the ECAM’s operating modes:
• Normal Mode:
Automatically displays systems and memos, in accordance with the flight phase.
• Failure Mode:
Automatically displays the appropriate emergency/abnormal procedures, in addition to their
associated system synoptic.
• Advisory Mode:
Automatically displays the appropriate system synoptic, associated with a drifting parameter.
• Manual Mode:
Enables the flight crew to manually select any system synoptic via the ECAM Control Panel
(ECP).
Most warnings and cautions are inhibited during critical phases of flight (T/O INHIBIT – LDG
INHIBIT), because most system failures will not affect the aircraft’s ability to continue a takeoff or
landing.
TYPES OF FAILURES
Ident.: DSC-31-10-00001205.0001001 / 21 MAR 16
Applicable to: ALL
Independent :
Primary
:
Secondary
:
a failure that affects an isolated system or item of equipment without degrading the
performance of others in the aircraft.
a failure of a system or an item of equipment that costs the aircraft the use of other
systems or items of equipment.
the loss of a system or an item of equipment resulting from a primary failure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-31-10 P 4/8
12 APR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
AUDIO INDICATORS
Applicable to: ALL
AUDIO INDICATORS
MEANING
DURATION
AUDIO INDICATOR
CANCELLATION (a)
PERMANENT
Press MASTER WARN lt
Ident.: DSC-31-10-A-00015446.0001001 / 22 JUL 16
CONTINUOUS
REPETITIVE CHIME
RED WARNINGS
Ident.: DSC-31-10-A-00015447.0001001 / 22 JUL 16
SINGLE CHIME
AMBER CAUTION
0.5 s
Ident.: DSC-31-10-A-00015448.0001001 / 04 FEB 14
CAVALRY CHARGE
A/P DISCONNECTION
BY TAKE OVER pb
1.5 s
A/P DISCONNECTION
DUE TO FAILURE
PERMANENT
Second push on
TAKE OVER pb
Press
MASTER WARN lt
or TAKE OVER pb
Ident.: DSC-31-10-A-00015449.0006001 / 22 JUL 16
TRIPLE CLICK
Landing capability
downgrade or some
cases of mode reversion
0.5 s (3 pulses)
Ident.: DSC-31-10-A-00015450.0001001 / 04 FEB 14
CRICKET
+
“STALL” message
(synthetic voice)
STALL
Ident.: DSC-31-10-A-00015451.0001001 / 23 JUN 15
BUZZER
CABIN CALL
EMER CABIN CALL
MECH CALL
PERMANENT
NIL
3s
3 s REPEATED
3 TIMES
As long as outside
pb pressed
NIL
NIL
Ident.: DSC-31-10-A-00015452.0001001 / 23 JUN 15
CONTINUOUS BUZZER
SELCAL CALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PERMANENT
F→
Press MASTER CAUT pb
Press
RESET key on ACP
or press
MASTER CAUT pb
Continued on the following page
DSC-31-10 P 5/8
12 APR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
AUDIO INDICATORS
MEANING
DURATION
Continued from the previous page
AUDIO INDICATOR
CANCELLATION (a)
Ident.: DSC-31-10-A-00015453.0002001 / 06 APR 17
"WINDSHEAR" (synthetic
voice)
"GO AROUND
WINDSHEAR AHEAD"
(synthetic voice)
"WINDSHEAR
AHEAD" (twice)
(synthetic voice)
"MONITOR
RADAR DISPLAY"
(synthetic voice)
WINDSHEAR
REPEATED 3 TIMES
NIL
Windshear ahead detected
during the landing phase
PERMANENT
NIL
Windshear ahead detected
during the takeoff phase
PERMANENT
NIL
Windshear ahead
detected caution message
PERMANENT
NIL
1.5 s
or
PERMANENT
new ALTITUDE selection or
press MASTER WARN pb
PERMANENT
NIL
PERMANENT
NIL
1s
NIL
ONE TIME at 20 ft
(10 ft in autoland
with A/THR ON),
Then PERMANENT
All Thrust levers are set
to IDLE or REVERSE
Ident.: DSC-31-10-A-00015454.0001001 / 04 FEB 14
C CHORD
ALTITUDE ALERT
(Refer to DSC-31-40
Altitude Alert)
Ident.: DSC-31-10-A-00015455.0001001 / 21 MAR 16
AUTO CALL OUT
(synthetic voice)
HEIGHT ANNOUNCEMENT
BELOW 2 500 ft
(Refer to DSC-34-NAV-40-10
Automatic Callout)
Ident.: DSC-31-10-A-00015456.0001001 / 21 MAR 17
GROUND PROXIMITY
WARNING
(synthetic voice)
(Refer to
DSC-34-SURV-40-10
Overview)
Ident.: DSC-31-10-A-00015457.0001001 / 04 FEB 14
“PRIORITY
LEFT” ”PRIORITY
RIGHT“ (synthetic voice)
A/P TAKE OVER pb
Ident.: DSC-31-10-A-00015458.0001001 / 04 FEB 14
“RETARD"
(synthetic voice)
Thrust levers not in
IDLE or REVERSE
position for landing
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
Continued on the following page
DSC-31-10 P 6/8
12 APR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
AUDIO INDICATORS
MEANING
DURATION
Ident.: DSC-31-10-A-00015459.0001001 / 04 FEB 14
"RETARD-RETARD"
(synthetic voice)
Continued from the previous page
AUDIO INDICATOR
CANCELLATION (a)
At least one Thrust Lever
Above 40 kt, PERMANENT
above IDLE after touchdown
All Thrust levers are set
to IDLE or REVERSE
Ident.: DSC-31-10-A-00015460.0001001 / 04 FEB 14
TCAS
(synthetic voice)
(Refer to
DSC-34-SURV-60-20
Aural Messages)
PERMANENT
NIL
Every 5 s until
thrust is increased
THRUST LEVER(s)
Every 5 s
One sidestick deactivated
Ident.: DSC-31-10-A-00015461.0001001 / 04 FEB 14
″SPEED, SPEED, SPEED″
(Synthetic voice)
Current thrust is not sufficient
to recover a positive flight
through pitch control
Ident.: DSC-31-10-A-00015463.0001001 / 04 FEB 14
"DUAL INPUT"
(synthetic voice)
(a)
Both sidesticks are
moved simultaneously
The pilot can cancel any audio indicator, by pressing:
‐ The EMER CANC pb on the ECAM control panel, or
‐ The MASTER WARN pushbutton, except for OVERSPEED or L/G NOT DOWN warnings.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←F
DSC-31-10 P 7/8
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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DSC-31-10 P 8/8
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON E/WD
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-31-15-00001207.0003001 / 21 MAR 17
Applicable to: ALL
The Engine Warning Display (E/WD ) appears on the ECAM 's upper Display Unit (DU).
‐ The upper part of this DU displays:
• Engine parameters (Refer to DSC-70-90-40 Engine Warning Display)
• Feedback messages (Refer to DSC-31-05-60 Feedback Messages)
• Fuel On Board (FOB) (Refer to DSC-28-20 ECAM Upper Display)
• Slats/Flaps' position (Refer to DSC-27-20-30 ECAM F/CTL Page)
‐ The lower part of this DU displays messages generated by the FWC:
• Warning and caution messages, when a failure occurs
• Memos when there is no failure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON E/WD
FLIGHT CREW
OPERATING MANUAL
The lower part of the DU , dedicated to ECAM messages, is divided into two sections that have
several lines each.
Bottom left : ‐ Primary or independent warnings and cautions, or
‐ Memo information.
Bottom right : ‐ Title of the system affected by a primary or independent warning or caution,
in the case of overflow on the bottom left part, or
‐ Secondary failure, or
‐ Memo, or
‐ Special lines (such as “AP OFF”, “LAND ASAP”).
As soon as the FWC detects a failure, and if there is no flight phase inhibition active, the E/WD
displays the title of the failure and actions that the flight crew must perform.
The action line automatically clears, when the flight crew has performed the necessary action.
Note:
Some action lines do not disappear from the E/WD even after the flight crew performs the
necessary action.
INDEPENDENT FAILURE
Ident.: DSC-31-15-00001208.0001001 / 03 FEB 11
Applicable to: ALL
If there are too many ECAM messages for the amount of space available in the lower part of
the E/WD, a green arrow appears at the bottom of the display, pointing down to show that the
information has overflowed off the screen. The pilot can scroll down to view additional messages
by pushing the CLR pushbutton on the ECAM control panel (on the pedestal, just below the lower
ECAM DU).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B
DSC-31-15 P 2/6
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON E/WD
FLIGHT CREW
OPERATING MANUAL
PRIMARY AND SECONDARY FAILURE
Ident.: DSC-31-15-00001209.0001001 / 03 FEB 11
Applicable to: ALL
The ECAM DU displays a primary failure as a boxed title.
It identifies a secondary failure by putting a star in front of the title of the affected system.
Note:
The DU displays the overflow symbol, if primary or secondary failures overflow. In case of
ELEC EMER CONFIG, the secondary failures are inhibited.
FLIGHT PHASES
Ident.: DSC-31-15-00001210.0001001 / 21 MAR 16
Applicable to: ALL
GENERAL
The FWC divides its functions according to these ten flight phases :
To improve its operational efficacy, the computer inhibits some warnings and cautions for certain
flight phases. It does so to avoid alerting the pilots unnecessarily at times when they have high
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D →
DSC-31-15 P 3/6
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
INDICATIONS ON E/WD
workloads, such as during takeoff or landing. In these two phases, the DU displays magenta
memos : “T.O. INHIBIT” (flight phases 3, 4, and 5), and “LDG INHIBIT” (flight phases 7 and 8).
These flight phases are different from and independent of the ones that the FMGC uses.
Note:
FLIGHT PHASE INHIBITION
Two cases are possible (for instance) :
Effect on E/WD :
(a)
The failure occurs during phase 1. The E/WD displays the warning immediately and
continues to display it as long as the failure is present, even in phase 2.
(b)
The failure occurs during phase 2. The E/WD displays the warning only when the aircraft has
entered phase 3, where it is not inhibited. Then the warning remains displayed as long as the
failure is present.
MEMOS
Applicable to: ALL
Ident.: DSC-31-15-A-00001211.0001001 / 21 MAR 16
DISPLAY
Memos appear in the lower part of the E/WD. They are normally in green, but may be amber in
abnormal situations.
Memos list functions or systems that are temporarily used in normal operations.
Ident.: DSC-31-15-A-00001212.0002001 / 22 APR 16
TO AND LDG MEMOS
During the takeoff and landing phases, the right side of the memo area displays specific TO
INHIBIT or LDG INHIBIT (magenta) memos.
Takeoff and landing memos are displayed, as follows, during the related flight phases:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
DSC-31-15 P 4/6
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON E/WD
FLIGHT CREW
OPERATING MANUAL
(*)
This line disappears when the test is completed. It is replaced by “TO CONFIG NORMAL”, if
aircraft configuration is correct.
The test is requested again, if the configuration becomes abnormal.
(*)
“CONF 3” is displayed in alternate or direct law, or if the GPWS LDG FLAP 3 pushbutton is
ON.
Note:
After a go-around, if the aircraft does not climb above 2 200 ft RA, the landing memo
appears only below 800 ft RA during the subsequent approach.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
DSC-31-15 P 5/6
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON E/WD
FLIGHT CREW
OPERATING MANUAL
CONFIGURATION WARNINGS
Ident.: DSC-31-15-00001214.0015001 / 16 MAR 11
Applicable to: ALL
The following warnings and cautions appear in the lower part of the E/WD if the aircraft is not in
takeoff configuration when the flight crew presses the TO CONFIG pushbutton on the ECAM control
panel or applies takeoff power.
WARNINGS/CAUTIONS
TO CONFIG TEST
CONFIG RUD TRIM NOT IN TO RANGE (R)
CONFIG PITCH TRIM NOT IN TO RANGE (R)
CONFIG FLAPS NOT IN TO CONFIG (R)
CONFIG SPD BRK NOT RETRACTED (R)
CONFIG SLATS NOT IN TO CONFIG (R)
CONFIG L SIDESTICK FAULT (R)
CONFIG R SIDESTICK FAULT (R)
DOOR (A)
FWS OEB /FWC DISCREPANCY (A)
BRAKES HOT (A)
FUEL R(L) TK PUMP 1+2 LO PR (A)
HYD G(Y) ENG 1(2) PUMP LO PR (A)
HYD G(Y)(B) SYS LO PR (A)
ELEC IDG 1(2) DISCONNECTED (A)
ELEC GEN 1(2) FAULT (A)
ELEC GEN 1(2) OFF (A)
CONFIG PARK BRK ON (R)
ENG THR LEVERS NOT SET (A)
(R)
(A)
TO POWER
TRIGGERED
TRIGGERED
NOT TRIGGERED
TRIGGERED if the
two GENs are inop.
NOT TRIGGERED
TRIGGERED
Red warning
Amber caution
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
DSC-31-15 P 6/6
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-31-20-00001215.0001001 / 21 MAR 16
Applicable to: ALL
The system/status display (SD) uses the lower ECAM DU to display :
‐ pages showing synoptic diagrams of the aircraft systems, or
‐ the status page.
SYSTEM PAGES
Ident.: DSC-31-20-00001216.0002001 / 21 MAR 16
Applicable to: ALL
The lower ECAM DU can display 12 system pages (For description see relevant FCOM chapter):
‐ ENGINE (secondary engine parameters)
‐ BLEED (air bleed)
‐ CAB PRESS (cabin pressurization)
‐ ELEC (electric power)
‐ HYD (hydraulic)
‐ FUEL (fuel)
‐ APU (auxiliary power unit)
‐ COND (air conditioning)
‐ DOOR/OXY (doors/oxygen)
‐ WHEEL (landing gear, braking, ground spoilers, etc.)
‐ F/CTL (flight controls)
‐ CRUISE (cruise)
The pilot may manually call up a system page for display on the lower ECAM DU, or the system may
automatically display a page.
‐ Manual:
• The pilot can, at any time, use the pushbutton on the ECAM's control panel to call up and
display any system page, except the CRUISE page.
• The corresponding pushbutton on the ECAM control panel lights up.
• A failure-related or advisory display automatically replaces a page the pilot has manually called
up.
‐ Automatic, related to a failure:
• The relevant system page automatically appears, as soon as any fault or malfunction triggers a
caution or warning message.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-31-20 P 1/8
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW
OPERATING MANUAL
‐ Automatic, advisory:
• The relevant system page automatically appears, when a parameter drifts out of its normal
range.
• The value (shown in green) pulses, as long as it is outside its limits.
• The advisory mode is inhibited in some flight phases.
Note:
If an advisory is triggered, when the ECAM is in the single-display configuration, an
advisory message appears on the upper part of the E/WD , and the associated key on
the ECAM control panel flashes to identify the appropriate system page.
‐ Automatic, flight phase mode
• If no other mode is engaged, the SD displays the system page related to the present flight
phase, as shown in the following diagram.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-31-20 P 2/8
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW
OPERATING MANUAL
• Phase 2 : The F/CTL page replaces the WHEEL page for 20 s when either pilot moves his
sidestick (more than 3 ° in pitch or roll) or when the rudder pedal deflection is more than 22 °.
• The APU page appears when the APU MASTER switch is ON. It disappears when APU RPM
has been above 95 % for 10 s, or when the APU MASTER switch is switched OFF.
• The ENGINE page appears at the beginning of start sequence or when a pilot selects “CRANK”.
It disappears 10 s after the end of the start sequence, when the ENG MODE sel is set to
NORM.
For a description of the ENGINE and AIR indications that appear when the SD is displaying the
CRUISE page, see the relevant FCOM chapter.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-31-20 P 3/8
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
INDICATIONS ON SD
STATUS PAGE
Ident.: DSC-31-20-00001217.0001001 / 12 APR 16
Applicable to: ALL
PURPOSE
The STATUS page provides an operational summary of the state of the aircraft. As illustrated in
the following image, this operational summary includes all of the following:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-31-20 P 4/8
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW
OPERATING MANUAL
(1)
Limitations (speed, flight level): Blue
(2)
Approach procedures: White (Red) (Amber)
(3)
Procedures (corrections to apply for landing): Blue
(4)
Information: Green
(5)
Cancelled caution: White
(6)
Inoperative system: Amber
(7)
Maintenance status: White
(8)
The arrow appears if the data on the STATUS page overflows the left or right area of the
page.
The flight crew can press the CLR pb, in order to scroll the display to view the overflow.
Note:
The titles of the different parts of the display appear in white and underlined.
STATUS PAGE DISPLAY
The STATUS page appears when the flight crew presses the STS pb on the ECAM Control Panel
(ECP).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-31-20 P 5/8
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW
OPERATING MANUAL
The STATUS page automatically appears in abnormal operations if one of the following applies:
‐ The STATUS page is not empty, and the flight crew clears the last alert on the E/WD, or
‐ The STATUS page is not empty, and the flight crew selects the CONF1 for approach.
BLANK LINES
Each block that is described above (limitation block (1), approach procedure block (2), etc.) is
separated by a blank line.
Therefore, a condition that is included in a limitation block (1) and the associated action line that is
included in the procedure block (3) are separated by a blank line.
Example : Illustration with the ECAM alert ENG 1(2) SHUTDOWN.
In this example, the action line “LDG DIST PROC … APPLY” applies only in the case of severe ice
accretion.
STS REMINDER
The STS reminder appears on the E/WD if both the following conditions apply:
‐ The STATUS page is not empty: The STATUS page displays message other than
“CANCELLED CAUTION” or MAINTENANCE status.
‐ There is a MAINTENANCE status at engines shutdown.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-31-20 P 6/8
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
INDICATIONS ON SD
The MAINTENANCE status can appear only when the aircraft is on the ground, before engine start
or after engine shutdown.
PERMANENT DATA
Ident.: DSC-31-20-00017520.0011001 / 25 JUL 16
Applicable to: ALL
(1)
Temperature
The screen displays the Total Air Temperature (TAT ) and Static Air Temperature (SAT) in
green.
The difference between the SAT and the International Standard Atmosphere temperature (ISA
) temperature (Delta ISA ) is displayed in green, in standard altitude mode and when the
SAT is valid.
(2)
G LOAL - ALT SEL
The screen displays one of the following items:
‐ Load factor (G LOAD) in amber, when the value is above 1.4 g or below 0.7 g for more
than 2 s. The G LOAD amber indication remains displayed 5 s after the excessive load
occurrence. The display of the load factor is inhibited during flight phases 1, 2, 3, 9 and 10.
‐ Altitude in green selected via the Flight Control Unit (FCU), if the flight crew selects metric
units, and provided the load factor is not displayed.
‐ “CHECK CAPT (F/O ) PFD ”, “CHECK CAPT (F/O ) ND ” or “CHECK SD” all in amber (Refer
to DSC-31-05-20 Cockpit Arrangement).
Note:
(3)
The display of the feedback messages takes priority over the load factor indication.
UTC
The screen displays the Universal Time Coordinated (UTC), synchronized with the cockpit
clock, in green.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
DSC-31-20 P 7/8
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON SD
FLIGHT CREW
OPERATING MANUAL
(4)
GW
The screen displays the Gross Weight (GW) in green, as soon as the flight crew starts the first
engine. The last two digits are dashed, if accuracy is degraded. On ground, blue dashes are
displayed instead of the indication, if no computed data is available.
AMBER CROSSES "XX" ON THE SD
Ident.: DSC-31-20-00013602.0001001 / 18 MAR 11
Applicable to: ALL
If a parameter value on any SD page is not available for display, amber crosses "XX" appear instead
of the value.
AMBER DASHES ON THE SD
Ident.: DSC-31-20-00015526.0001001 / 01 APR 14
Applicable to: ALL
If the accuracy of a parameter value on any SD page is degraded, amber dashes are displayed over
the last digits.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to F
DSC-31-20 P 8/8
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ECAM SEQUENCE - GENERAL
GENERAL
Ident.: DSC-31-25-10-00001219.0001001 / 22 MAR 16
Applicable to: ALL
If ECAM detects a failure :
‐ The E/WD displays warning or caution messages.
‐ The master warning or master caution lights light up (except in the case of a level 1 caution).
‐ The system sounds an aural signal (except in the case of a level 1 caution).
‐ The system display (SD) shows the system page for the affected system.
‐ The CLR pushbutton on the ECAM control panel lights up.
In addition, a local warning light controlled directly by the affected system can light up.
After completing remedial procedures, the flight crew must push the CLR pushbutton repeatedly until
the displays return to their normal configurations :
‐ MEMO messages on the E/WD
‐ The system page related to the present flight phase on the SD.
‐ The CLR light on the ECAM control panel turned off.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-31-25-10 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM SEQUENCE - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-31-25-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM SEQUENCE - EXAMPLE
FLIGHT CREW
OPERATING MANUAL
1 - THE ECAM DETECTS NO FAILURE
Ident.: DSC-31-25-20-00001220.0004001 / 09 OCT 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-31-25-20 P 1/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM SEQUENCE - EXAMPLE
FLIGHT CREW
OPERATING MANUAL
2 - THE ECAM DETECTS A FAILURE
Ident.: DSC-31-25-20-00001221.0004001 / 09 OCT 12
Applicable to: ALL
For example, a hydraulic reservoir is overheat.
COCKPIT INDICATIONS
‐
‐
‐
‐
A single chime sounds
Both MASTER CAUTION lights come on, and stay on
A FAULT light, on the overhead HYD panel, comes on
The memo space on the E/WD displays the “HYD B RSVR OVHT ” message, and the “BLUE
ELEC PUMP . . . . . OFF” instruction
‐ The lower ECAM display (SD ) automatically calls up the hydraulic system's diagram, and
displays “OVHT” in amber next to the blue system
‐ The ECAM 's CLR pushbutton lights up.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
DSC-31-25-20 P 2/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
3 - THE FLIGHT CREW FOLLOWS THE INSTRUCTION DISPLAYED ON THE E/WD
Ident.: DSC-31-25-20-00001222.0002001 / 09 OCT 12
Applicable to: ALL
The flight crew switches off the BLUE ELEC PUMP pushbutton, depressurizing the blue hydraulic
circuit.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-31-25-20 P 3/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
COCKPIT INDICATIONS
‐
‐
‐
‐
‐
A single chime sounds.
Both MASTER CAUTION lights stay on.
A FAULT/OFF light, on the overhead panel, comes on.
The second part of the message on the E/WD changes to “B SYS LO PR”.
The SD 's system diagram shows an amber zero for the pressure in the blue system, along with
the amber “OVHT”.
‐ The right side of the memo area indicates a secondary failure in the flight control system.
‐ The ECAM control panel's CLR pushbutton remains on.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-31-25-20 P 4/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
ECAM SEQUENCE - EXAMPLE
←C
DSC-31-25-20 P 5/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
4 - ONE OF THE PILOTS PUSHES THE CLR PUSHBUTTON ON THE ECP
Ident.: DSC-31-25-20-00001223.0003001 / 09 OCT 12
Applicable to: ALL
COCKPIT INDICATIONS
‐ The CLR pushbutton stays on.
‐ The FAULT/OFF light stays on.
‐ Hydraulic system messages disappear from the E/WD, and the right side of the memo area
indicates a secondary failure in the flight control system.
‐ The SD automatically calls up the flight control system page, with surface actuator indications
(associated with the blue hydraulic system) shown in amber.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
DSC-31-25-20 P 6/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
ECAM SEQUENCE - EXAMPLE
←D
DSC-31-25-20 P 7/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
5 - ONE OF THE PILOTS PUSHES THE CLR PUSHBUTTON A SECOND TIME
Ident.: DSC-31-25-20-00001224.0003001 / 09 OCT 12
Applicable to: ALL
COCKPIT INDICATIONS
‐
‐
‐
‐
The ECP 's CLR and STS pushbuttons light up.
The FAULT/OFF lights stay on.
The E/WD's memo area returns to normal.
The STATUS page automatically appears on the SD, displaying the procedures for completing
the flight with a faulty blue system.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
DSC-31-25-20 P 8/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
ECAM SEQUENCE - EXAMPLE
←E
DSC-31-25-20 P 9/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ECAM SEQUENCE - EXAMPLE
6 - ONE OF THE PILOTS PUSHES THE CLR PUSHBUTTON A THIRD TIME
Ident.: DSC-31-25-20-00001225.0003001 / 09 OCT 12
Applicable to: ALL
COCKPIT INDICATIONS
‐
‐
‐
‐
The CLR pushbutton light goes off.
The FAULT/OFF lights stay on.
A status reminder appears at the bottom of the E/WD.
The SD automatically displays the system page corresponding to the flight phase.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
DSC-31-25-20 P 10/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
ECAM SEQUENCE - EXAMPLE
←F
DSC-31-25-20 P 11/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM SEQUENCE - EXAMPLE
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-31-25-20 P 12/12
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
OEB REMINDER
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-31-27-00001226.0001001 / 21 MAR 16
Applicable to: ALL
The OEB reminder function provides operational help to the crew by enabling them to clearly identify
(on the ECAM) all procedures and status messages affected by an OEB.
When a situation leading to a warning/caution occurs, a message informs the crew in real time that
an OEB exists for the displayed warning and/or status and, consequently, that the procedure and/or
status presented on the ECAM is not applicable.
Then the crew must refer to the QRH where the correct information is provided.
DESCRIPTION
Ident.: DSC-31-27-00001227.0003001 / 22 MAY 12
Applicable to: ALL
The OEB reminder flag may apply to the:
‐ ECAM procedure only,
‐ ECAM procedure and corresponding status messages,
‐ Status message only.
PROCEDURE ONLY AFFECTED
‐ The ECAM warning title remains unaltered,
‐ All corresponding actions are suppressed and replaced by the “REFER TO QRH /OEB PROC”
message,
‐ The related status messages on the ECAM system display remains unaltered.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-31-27 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
OEB REMINDER
FLIGHT CREW
OPERATING MANUAL
COCKPIT INDICATION
PROCEDURE AND STATUS AFFECTED
‐ The ECAM warning title remains unaltered,
‐ All corresponding actions are suppressed and replaced by the “REFER TO QRH /OEB PROC”
message,
‐ The related status messages on the ECAM system display remains unchanged, except for the
additional “REFER TO QRH /OEB PROC” title.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-31-27 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
OEB REMINDER
FLIGHT CREW
OPERATING MANUAL
COCKPIT INDICATION
STATUS MESSAGE ONLY AFFECTED
‐ The ECAM warning title remains unaltered,
‐ The corresponding procedure remains unchanged, except for the additional “FOR STS REFER
TO OEB" line.
‐ The related status messages on the ECAM system display remains unchanged, except for the
additional " REFER TO QRH /OEB PROC" title.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-31-27 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
OEB REMINDER
FLIGHT CREW
OPERATING MANUAL
COCKPIT INDICATION
OEB DATABASE
Ident.: DSC-31-27-00001228.0001001 / 21 MAR 16
Applicable to: ALL
The OEB database lists the warnings and cautions affected by an OEB.
The OEB database can be :
• Loaded manually on the aircraft via the MCDU , and stored in both FWCs.
• Crossloaded from one FWC to the other FWC.
• Updated by entering a code via the MCDU.
• Checked via the MCDU.
Note:
The code provided on the OEB is designed to ensure that the OEB database is not updated
before the OEB is available.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C
DSC-31-27 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW
OPERATING MANUAL
ECAM CONTROL PANEL
Ident.: DSC-31-30-00001229.0002001 / 26 JUL 17
Applicable to: ALL
(1)
OFF / BRT knobs
Used to turn the ECAM DUs on and off, and to control their brightness (automatic adjustment of
brightness for ambient light conditions is superimposed on this manual control).
Note:
(2)
When the pilot turns the UPPER DISPLAY knob to OFF, the engine/warning (E/W)
display appears on the lower display unit (automatic transfer).
System page pushbuttons
‐ Call up the corresponding system pages on the SD
‐ Light up, when pushed for manual selection, or when an advisory is detected
‐ Call up the aircraft system page corresponding to the present flight phase or the current
warning when pushed a second time.
When only one ECAM display is on, the pilot can display a system page for up to 3 min by
pushing and holding the system page pushbutton.
• If an advisory condition arises, the relevant system page is not automatically displayed,
but the pushbutton light pulses
• If an ECAM warning is triggered, the relevant system page is not automatically displayed,
and the system page pushbutton does not light up.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-31-30 P 1/6
05 SEP 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW
OPERATING MANUAL
(3)
RCL pb
‐ When pressed, the E/WD displays all alerts previously cleared via the CLR pb that are still
active.
‐ When pressed for more than 3 s, the E/WD displays:
• All alerts previously cleared via the CLR pb that are still active
• All alerts previously cancelled via the EMER CANC pb.
Note:
(4)
1. If there is no alert to recall, the “NORMAL” message appears for 3 s on the E/WD.
2. This action on the RCL pb also suppresses the flight phase inhibition function until
the next flight phase. As a consequence, all new alerts that should normally be
inhibited will be displayed.
STS pb
The pilot pushes this pushbutton to display the STATUS page on the lower SD . The
pushbutton remains lit, as long as the SD displays the STS page. If the system has no status
messages, the status page displays “NORMAL” for 3 s.
The pilot can clear the STATUS page by pushing the CLR pb, or by pushing the STS pb a
second time.
When only one ECAM display is on :
‐ It displays the STATUS page only when the pilot pushes the STATUS pushbutton and holds
it. He can display the next STATUS page, if any, by releasing the pushbutton and pushing it
again (before 2 s have elapsed). The new page then appears after a short delay.
‐ The pilot can keep the STS pb pressed to display the STATUS page for a maximum of
3 min, after which the ECAM automatically displays the engine/warning page.
(5)
CLR pb
This pushbutton remains lit as long as the E/WD is displaying a warning or caution message, or
a status message on the SD.
If it is lit, pressing it changes the ECAM display.
(6)
ALL pb
When this pushbutton is pressed and held down, the SD successively displays all the system
pages at 3 s intervals.
If the ECAM control panel fails, the pilot can use this pushbutton to page through the system
pages until he comes to the one he wants to look at. He then releases the pushbutton to select
that page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-31-30 P 2/6
05 SEP 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW
OPERATING MANUAL
(7)
EMER CANC pb
This pushbutton affects the following :
‐ Warnings :
• Cancels (stops) an aural warning for as long as the failure condition continues
• Extinguishes the MASTER WARNINGS lights
• Does not affect the ECAM message display.
‐ Cautions :
• Cancels any present caution (single chime, MASTER CAUTION lights, ECAM message)
for the rest of the flight.
The flight crew can press the RCL pb for more than 3 s in order to restore all the alerts
previously canceled via the EMER CANC pb.
All the alerts previously canceled via the EMER CANC pb automatically reappear on the E/WD
in flight phase 1 or 2, immediately after the alignment of IRs 1 and 2.
Note:
(8)
This pushbutton should only be used to suppress spurious MASTER CAUTIONS.
T.O CONFIG pb
This pushbutton simulates the application of takeoff power. This is a test that triggers a
warning, if the aircraft is not in takeoff configuration. (Refer to DSC-31-15 Configuration
Warnings).
If the configuration is correct, the E/WD displays the “TO CONFIG NORMAL” message in the
TO MEMO section.
Note:
If the ECAM control panel fails, the CLR, RCL, STS, EMER CANC, and ALL
pushbuttons remain operative, because their contacts are directly wired to the flight
warning and display management computers.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-31-30 P 3/6
05 SEP 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW
OPERATING MANUAL
SWITCHING PANEL
Ident.: DSC-31-30-00001230.0002001 / 17 MAR 11
Applicable to: ALL
ON PEDESTAL
(1)
EIS DMC rotary selector
NORM : DMC 1 supplies the CAPT's PFD, the CAPT's ND, and the ECAM's DUs.
DMC 2 supplies the F/O's PFD and the F/O's ND.
CAPT 3 : DMC 3 replaces DMC 1.
F/O 3 : DMC 3 replaces DMC 2.
Note:
(2)
If a DMC fails, each of its associated DUs displays an “INVALID DATA” message.
ECAM/ND XFR rotary selector
Transfers the system/status display to either the Captain's or the First Officer's ND.
The “ECAM ON ND” message is displayed on the lower ECAM display.
Note:
If both ECAM DU s (E/WD and SD ) fail, the flight crew may use this switch to
transfer the E/WD display to either navigation display. In this case, the “ECAM ON
ND” message is not displayed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
DSC-31-30 P 4/6
05 SEP 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW
OPERATING MANUAL
ATTENTION GETTERS
Ident.: DSC-31-30-00001231.0001001 / 09 OCT 12
Applicable to: ALL
(1)
MASTER WARN lights
‐ Flash red for level 3 warning
‐ Accompanied by an aural warning (continuous repetitive chime, specific sounds or synthetic
voice).
(2)
MASTER CAUT lights
‐ Light up steady amber for a level 2 caution
‐ Accompanied by a single chime.
These lights go out when :
‐ One pilot presses the light (except for some red warnings, such as the overspeed and stall
warnings)
‐ The warning/caution situation is over
‐ The pilot presses the CLR pb on the ECAM control panel (except for some red warnings,
such as the overspeed and stall warnings).
‐ The pilot presses the EMER CANC pb on the ECAM control panel.
The aural warnings cease when :
‐ One pilot presses the MASTER WARN light (except for some red warnings, such as the
overspeed and stall warnings)
‐ The warning situation is over
‐ The pilot presses the EMER CANC pb on the ECAM control panel.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-31-30 P 5/6
05 SEP 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
ECAM CONTROLS
FLIGHT CREW
OPERATING MANUAL
MEMO DISPLAY
Ident.: DSC-31-30-00018053.0001001 / 21 MAR 16
Applicable to: ALL
SWITCHING :
PNL
This memo appears in green, when:
1. PFD/ND XFR pb is pressed and ECAM/ND XFR rotary selector is selected at
CAPT or F/O side simultaneously, or
2. ATT HDG rotary selector is selected at CAPT or F/O side, or
3. AIR DATA rotary selector is selected at CAPT or F/O side, or
4. EIS DMC rotary selector is selected at CAPT or F/O side.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
DSC-31-30 P 6/6
05 SEP 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-31-40-00017531.0003001 / 21 MAR 16
Applicable to: ALL
The Primary Flight Display (PFD) provides the following information to the flight crew:
‐ Attitude and guidance
‐ Airspeed
‐ Altitude (BARO and radio) and vertical speed
‐ Heading and track
‐ FMGS modes (Flight Mode Annunciator)
‐ Vertical and lateral deviations
‐ Radio navigation information (ILS , MLS , FLS , GLS , DME).
The FWC monitors main parameters such as attitude, heading, and altitude. For more information,
Refer to DSC-31-40 Flags and Messages Displayed on PFD.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-31-40 P 1/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
SPECIFIC GROUND INDICATIONS
Ident.: DSC-31-40-00001233.0001001 / 13 JAN 14
Applicable to: ALL
(1)
Sidestick order indication
This symbol is in white, and appears as soon as one engine is started.
It indicates the total of the Captain’s and First Officer’s sidestick orders (shown here as left
wing down, pitch up).
(2)
Max Sidestick Deflection
This symbol is in white, and appears as soon as one engine is started.
(3)
Ground Roll Guidance Command Bar
This symbol is in green, and appears when the aircraft is on ground, or below 30 ft radio
height, provided that a localizer signal is available. It indicates the Flight Director yaw orders, to
maintain the aircraft on the runway centerline.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
DSC-31-40 P 2/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
ATTITUDE DATA
Ident.: DSC-31-40-00001234.0003001 / 09 OCT 12
Applicable to: ALL
(1)
Fixed Aircraft Symbol
This symbol is in black, and outlined in yellow. The yellow outline is dimmed if the crew selects
TRK -FPA , unless the FMA is in the TOGA or FLX mode.
(2)
Roll Scale
This scale is in white, and has markers at 0, 10, 20, 30, and 45 ° of bank.
(3)
Roll Index (yellow)
This pointer indicates the bank angle. When the bank angle exceeds 45 °, all the PFD symbols,
except those for attitude, speed, heading, altitude, and vertical speed, disappear. The display
returns to normal when the bank angle decreases below 40 °.
(4)
Pitch Scale (white)
This scale has markers every 10 ° between 80 ° nose up and 80 ° nose down (every 2.5 °
between 10 ° nose down and 30 ° nose up). When pitch angle exceeds 25 ° nose up or 13 °
nose down, all the PFD displays except attitude, speed, speed trend, heading, altitude, and
vertical speed disappear. Beyond 30 °, large red arrowheads indicate that the attitude has
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
DSC-31-40 P 3/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
become excessive and show the direction to move the nose in order to reduce it. The display
returns to normal when pitch angle becomes less than 22 ° nose up or 10 ° nose down.
(5)
Flight Control Protection Symbols
The display shows these symbols (=) in green:
• On the roll scale to mark the bank angle protection availability.
• On the pitch scale at 15 ° nose down or 30 ° nose up to mark the pitch limits.
An amber x replaces these symbols if the corresponding protection is lost.
(Refer to DSC-27-20-10-20 Protections - General)
(6)
Sideslip Index (yellow)
This trapezoidal index moves beneath the roll index. On ground, it represents the lateral
acceleration of the aircraft. In flight, it shows sideslip (as computed by the FAC). One
centimeter of displacement indicates 0.2 g. The sideslip index is against its stop at 0.3 g.
In case of engine failure at takeoff or go around, the sideslip index changes from yellow to blue.
Note:
The sideslip target is blue, if:
‐ CONF 1, 2, or 3 is selected, and
‐ Any ENG N1 > 80 %or one Thrust Lever > MCT (≥ FLX if FLX or DERATED TO),
and
‐ The difference between the ENG N1’s exceeds 35 %.
In this case, the sideslip index is called β target.
When this index is centered with the roll index, the sideslip equals the sideslip target for
optimum aircraft performance.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
DSC-31-40 P 4/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
AIRSPEED
Ident.: DSC-31-40-00001235.0004001 / 21 MAR 17
Applicable to: ALL
(1)
Actual Airspeed Reference Line and Scale
A white scale, on a grey background, moves in front of a fixed yellow reference line (next to a
yellow triangle) to indicate airspeed. The minimum airspeed indication is 30 kt.
(2)
Speed Trend (yellow)
This pointer starts at the speed symbol. The tip indicates the speed the aircraft will reach in
10 s, if its acceleration remains constant. The pointer only appears, when it is greater than 2 kt,
and disappears when it is less than 1 kt.
It also disappears, if the FACs fail.
(3)
Target Airspeed (magenta or blue)
This symbol gives the target airspeed, or the airspeed corresponding to the target Mach
number.
The target airspeed is the airspeed computed by FMGC in managed speed mode (magenta),
or the airspeed manually entered on the FCU in selected speed mode (blue). The target speed
is indicated by a magenta or blue triangle.
When the target speed is off the speed scale, its value is displayed as numbers, either above
or below the speed scale.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
DSC-31-40 P 5/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(4)
Mach Number (green)
It is displayed, when it is greater than0.5.
(5)
Speed Protection (green)
This symbol indicates the speed (VMO +6 kt or MMO +0.01) at which overspeed protection
becomes active (Refer to DSC-27-20-10-20 Protections - General).
(6)
ECON Speed Range (magenta)
In descent mode with the ECON /AUTO SPD mode active, these two thick lines replace the
selected speed symbol. It shows the upper and lower limits, calculated by the FMGC.
‐ The upper speed is target speed +20 kt, limited to VMAX or VMO -3 kt or MMO -0.006,
whichever is lowest.
If a speed limit or a speed constraint applies, the upper margin is limited to ECON SPD
+5 kt.
‐ The lower speed margin is the target speed -20 kt, limited to green dot, F, S, or VLS,
whichever is higher.
(1)
Minimum Selectable Speed (VLS)
The top of the amber strip along the speed scale indicates this speed. It represents the
lowest selectable speed providing an appropriate margin to the stall speed. (Refer to
DSC-27-20-10-20 Protections - High Speed Protection)
VLS information is inhibited from touchdown until 10 s after liftoff.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-31-40 P 6/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(2)
Alpha Protection Speed
The top of a black and amber strip along the speed scale indicates this speed.
It represents the speed corresponding to the angle of attack at which alpha protection becomes
active (Refer to DSC-27-20-10-20 Protections - General).
It is displayed when in pitch normal law.
(3)
Alpha MAX Speed
The top of a red strip along the speed scale indicates this speed. It represents the speed
corresponding to the maximum angle of attack that the aircraft can attain in pitch normal law
(Refer to DSC-27-20-10-20 Protections - General).
It is displayed when in pitch normal law.
(4)
VMAX
The lower end of a red and black strip along the speed scale defines this speed.
It is the lowest of the following:
‐ VMO or the speed corresponding to MMO
‐ VLE
‐ VFE
(Refer to DSC-27-20-10-20 Protections - High Speed Protection)
(5)
Stall Warning Speed (VSW)
The top of a red and black strip along the speed scale defines this speed.
It is the speed corresponding to the stall warning. (Refer to DSC-27-20-10-20 Protections General).
VSW information is inhibited from touchdown until 5 s after liftoff.
It is displayed when operating in pitch alternate or pitch direct law.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-31-40 P 7/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(1)
Decision Speed (V1)
This is a blue symbol (numeral one) that the crew manually inserts via the MCDU. When it is off
the scale, the upper part of the scale shows it in numbers.
It disappears after liftoff (Refer to DSC-22_10-50-50 Other Speeds).
(2)
Minimum Flap Retraction Speed
This is a green symbol (letter F).
It appears when the flap selector is in position 3 or 2. (Refer to DSC-27-20-10-20 Protections High Speed Protection).
(3)
Minimum Slat Retraction Speed
This is a green symbol (letter S).
It appears when the flap selector is in position 1. (Refer to DSC-27-20-10-20 Protections - High
Speed Protection).
(4)
VFE NEXT
The VFE next symbol is an amber equal sign showing the VFE corresponding to the next flap
lever position.
It appears when the aircraft altitude is below 15 000 ft or 20 000 ft, depending upon the FAC
standard (Refer to DSC-22_10-50-30 Limit Speeds).
(5)
Green Dot (Engine-out operating speed in clean configuration)
This green dot appears, when the aircraft is flying in the clean configuration.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-31-40 P 8/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
INDICATIONS ON PFD
It shows the speed corresponding to the best lift-to-drag ratio.
(6)
Rotation speed: (VR)
VR is entered on the PERF takeoff page of the MCDU, and is indicated by a cyan circle.
This cyan circle is visible during takeoff.
Note:
V2 is represented by the target speed index during takeoff.
V2 is manually inserted by the crew via the MCDU.
ALTITUDE
Ident.: DSC-31-40-00001237.0023001 / 29 OCT 13
Applicable to: ALL
(1)
Altitude Indication
This appears both as a white moving scale, and as a green digital readout on a grey
background. Small white marks are positioned on the scale against the round values (e.g.
280, 290...). “NEG” appears in the window in white for negative values. The altitude window
changes from yellow to amber, if the aircraft deviates from the FCU-selected altitude or flight
level.
On any approach for which an minimum is entered in the FMGS, the altitude numbers change
from green to amber, when the aircraft goes below the minimum.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
DSC-31-40 P 9/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(2)
Vertical Deviation (magenta)
This symbol appears next to the altitude corresponding to the theoretical vertical profile
computed by the FMGC . It is displayed from the top of descent down to the MAP altitude.
The pilot can read the VDEV directly from the altitude scale. The range is ±500 ft. When the
VDEV value exceeds ±500 ft, the symbol stays at the range limit and the PROG page displays
the exact value.
(3)
Target Altitude or Selected Flight Level Symbol (blue)
This symbol shows the FCU selected altitude (if QNH BARO reference is selected) or the
selected flight level (if STD BARO reference is selected.)
When the FMGC operates in the vertical managed mode, this symbol is magenta if it
represents a flight plan altitude constraint that the FMGC will follow. If the target altitude or
flight level is on the scale, the symbol is displayed and the numerical value appears inside the
symbol.
If it is off the scale, the symbol is not displayed, and the numerical value appears above or
underneath the scale.
(4)
Barometric Reference
The display shows “STD ” or it shows “QNH” and the numerical setting in hectoPascals or
inches of mercury.
It pulses when the selection made by the pilot is not correct (STD not selected above transition
altitude in climb or STD still selected in approach below transition level).
APPROACH MINIMUM INDICATION
Approach minimum is displayed on the altitude scale by an amber indication.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
DSC-31-40 P 10/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
ALTITUDE (CONT'D)
Ident.: DSC-31-40-00006121.0002001 / 13 JAN 14
Applicable to: ALL
(1)
Radio Height
A value appears, when the aircraft is lower than 2 500 ft.
‐ If a DH has been entered, the radio height appears:
• In green, when DH +100 ft < RA < 2 500 ft
• In amber, when RA < DH +100 ft
If “NO” is entered as the DH on the MCDU APPROACH page, 0 ft becomes a default value.
When the aircraft reaches the decision height selected on the MCDU , DH letters flash
amber for 9 s, then remain amber above the radio height indication.
‐ If no DH has been entered, or if both FMGCs fail, the radio height appears:
• In green, when 400 ft < RA < 2 500 ft
• In amber, when RA ≤ 400 ft
The radio height indication changes every 10 ft down to 50 ft, then every 5 ft down to 10 ft, then
every foot.
(2)
Landing Elevation (brown)
The top of the brown surface on the altitude scale represents the landing elevation at the
flight-planned destination.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
DSC-31-40 P 11/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
It is displayed:
‐ during flight phases 7 and 8 and
‐ if the STD reference mode is not selected.
(3)
Ground reference
A red ribbon on the right of the altitude scale represents the field elevation. This ribbon, which
is driven by the radio altimeter signal, is displayed below 570 ft.
It moves up, as does the lower line of the attitude sphere, with the altitude scale as the aircraft
descends. When the aircraft has touched down, the top of this ribbon is at the middle of the
altitude window.
VERTICAL SPEED
Ident.: DSC-31-40-00001239.0002001 / 21 MAR 17
Applicable to: ALL
The displayed vertical speed information is normally based on both inertial and barometric data. If
inertial data is not available, it is automatically replaced by barometric information.
In this case, the window around the numerical value becomes amber.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G →
DSC-31-40 P 12/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
INDICATIONS ON PFD
(1)
Analog pointer
This pointer, which is normally in green, points to a white vertical speed scale, displayed on a
grey background and graduated at intervals of 500 ft/min.
If the V/S is greater than 6 000 ft/min, the pointer stays at the end of the scale.
(2)
Digital indication
This number, normally in green, is the vertical speed in hundreds of feet per minute.
It disappears, if the vertical speed is less than 200 ft/min.
The analog pointer and the digital indication become amber, if:
• V/S is greater than 6 000 ft/min, (climb or descent)
• V/S is greater than 2 000 ft/min, during descent when 1 000 ft < RA < 2 500 ft, or
• V/S is greater than 1 200 ft/min, during descent and RA < 1 000 ft.
Note:
For TCAS, Refer to DSC-34-SURV-60-20 TCAS Messages.
HEADING
Ident.: DSC-31-40-00001240.0002001 / 07 MAY 13
Applicable to: ALL
(1)
Heading Reference Line and Scale
A white scale on a grey background moves in front of a fixed yellow reference line to indicate
the actual magnetic heading.
“TRUE” appears, when the display indicates the true heading, rather than the magnetic
heading (latitude above 73 ° North or below 60 ° South).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← G to H →
DSC-31-40 P 13/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(2)
Selected Heading or Track Index (blue)
This pointer is in blue, and indicates the heading or track displayed on the FCU HDG-TRK
window.
The index is replaced by digits on the right or left side of the scale, when the selected value is
off the scale.
If the FD pushbutton is OFF, a second heading/track symbol appears on the horizon line, and
markers are displayed every 10 °.
(3)
Actual Track Symbol
This symbol is a small green diamond.
FLIGHT PATH VECTOR
Ident.: DSC-31-40-00001241.0001001 / 17 MAR 17
Applicable to: ALL
The Flight Path Vector (FPV ) is the flight reference with the TRK and FPA as basic guidance
parameters. When the TRK /FPA is selected on the FCU , the FPV appears on the PFD.
INFORMATION PRESENTATION
The FPV appears on the PFD as a symbol, known as the "bird". The bird indicates the track and
flight patch angle in relation to the ground.
The track is indicated on the PFD by a green diamond on the compass, in addition to the lateral
movement of the bird in relation to the fixed aircraft symbol. On the ND, the track is indicated
by a green diamond on the compass scale. The difference in angle between track and heading
indicates the drift.
The flight path angle is indicated on the PFD by the vertical movement of the bird in relation to the
pitch scale.
With the flight directors (FD ) ON, the Flight Path Director (FPD ) replaces the HDG -VS Flight
Director (FD ). With both FD pb set to OFF, the blue track index appears on the PFD horizon.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← H to I →
DSC-31-40 P 14/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(1)
Flight Path Vector (FPV)
This symbol appears, when the pilot selects TRK /FPA on the FCU.
The flight path vector represents the lateral and vertical trajectory of the aircraft with respect
to the ground.
‐ On the lateral scale, it indicates the aircraft’s track.
‐ On the vertical scale, it indicates the aircraft’s flight path angle.
Example :
The aircraft flies a track of 009 ° (heading 360 °, wind from west) and descends
with a flight path angle of minus 7.5 °.
USE OF FPV
The bird is the flying reference that should be used when flying a stabilized segment of trajectory,
e.g.: non-precision approach when the FLS function is not used or visual circuit.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
DSC-31-40 P 15/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
INDICATIONS ON PFD
In dynamic manoeuvres, the bird is directly affected by the aircraft inertia and has a delayed
reaction. As a result, the bird should not be used as a flight reference in dynamic manoeuvres.
Refer to FCTM/AS-BIRD Introductionfor more information.
GUIDANCE
Ident.: DSC-31-40-00001242.0001001 / 13 JAN 14
Applicable to: ALL
Two completely different flight director modes are available, each with its own characteristic symbols.
The symbol displayed corresponds to the basic operating reference the pilot has selected – either
HDG V/S or TRK FPA.
In normal operation, PFD 1 displays FD1 orders.
If FD 1 fails, PFD 1 automatically displays FD 2 orders on PFD 1, the FD 2 indication in the right
column of the FMA flashes for a few seconds.
This is also applicable to FD 2 orders, that are displayed on PFD2.
IF THE CREW HAS SELECTED HDG V/S TO BE THE BASIC REFERENCE:
The PFD displays FD bars in green. They automatically move out of view at touchdown in ROLL
OUT mode.
They flash for 10 s, and then remain steady, if the following occur:
‐ A reversion to the HDG V/S basic mode (manual or automatic), or
‐ The selected flight level is changed, when ALT CAPTURE mode is engaged, or
‐ The loss of LOC or G/S in LAND mode or loss of LAND mode, or
‐ At the first AP or FD engagement.
The PFD displays a yaw bar in green below 30 ft radio height, if a localizer signal is available:
‐ During takeoff (in RWY mode)
‐ Upon landing (in FLARE and ROLL OUT mode).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← I to J →
DSC-31-40 P 16/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(1)
FD Crossed Bars (green)
(2)
Yaw Bar (green)
THE CREW HAS SELECTED TRK FPA AS THE BASIC REFERENCE:
An inertial flight path vector defines the aircraft's horizontal and vertical track, taking wind effect
into account.
An associated flight path director symbol guides the flight crew onto the vertical and horizontal
flight path targets.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←J→
DSC-31-40 P 17/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(1)
Flight Path Vector (green)
(2)
Flight Path Director (green)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←J
DSC-31-40 P 18/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
TRAJECTORY DEVIATION
Applicable to: ALL
Ident.: DSC-31-40-A-00017532.0001001 / 21 MAR 16
ILS/GLS /MLS APPROACH
(1)
Localizer Deviation Scale and Index
(2)
Glide slope Deviation Scale and Index
Deviation scales appear as soon as the flight crew presses an LS/ILS pb on the EFIS control
panel. Deviation indexes appear when the glide slope and localizer signals of the ILS/GLS
(or the elevation and azimuth signals of the MLS ) are valid, if deviation scales are
displayed.
When a deviation index is out of the displayed range, only half a symbol appears at the end
of the scale.
The LOC scale flashes and continues to flash if the deviation exceeds 1/4 dot for two
seconds while the aircraft is between 15 ft and 1 000 ft, and CAT 2 or CAT 3 capability
displayed on the FMA , and either LOC , LAND, or FLARE is engaged. The glideslope scale
flashes and continues to flash if the deviation exceeds one dot for two seconds (above 100 ft
RA).
“LOC” and the glideslope scale half index symbols flash, and continue to flash, when the
deviation exceeds two dots for two seconds.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K→
DSC-31-40 P 19/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
One dot represents a deviation of ± 0.8 ° on the localizer scale, and ± 0.4 ° on the glideslope
scale.
Ident.: DSC-31-40-A-00017533.0004001 / 21 MAR 16
ILS/GLS /MLS APPROACH (CONT'D)
(1)
ILS/GLS /MLS information (magenta)
The following information appears on the PFD , when the crew has selected an ILS
frequency/GLS channel/MLS channel and course, and pressed the LS pb:
‐ ILS /GLS /MLS identification, as decoded by the ILS /GLS /MLS receiver;
‐ ILS frequency/GLS channel/MLS channel;
‐ For ILS /MLS : DME distance, if the ILS /MLS has a DME . For GLS : distance to runway
threshold computed by the MMR.
(2)
ILS/GLS /MLS course Pointer (magenta)
This pointer appears on the PFD , when the crew has selected an ILS frequency/GLS
channel/MLS channel and course, and pressed the LS pb.
It is a dagger-shaped symbol on the heading scale.
The ILS /GLS /MLS course pointer is replaced by digits on the right or left hand of the
heading scale (in a white box) when the ILS /GLS /MLS course value is outside the
displayed portion of the heading scale.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←K→
DSC-31-40 P 20/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(3)
Marker Indications
OM appears in blue, when the aircraft flies over the outer marker.
MM appears in amber, when it flies over the middle marker.
IM appears in white, when it flies over an airways marker beacon or the ILS/GLS inner
marker.
(4)
LS Message
This flashes amber, when the APPR mode is armed, but the LS pb has not been selected.
(5)
Selected approach
The ILS /GLS /MLS indication is displayed in magenta according to the approach selected by
the crew.
Ident.: DSC-31-40-A-00001245.0022001 / 09 OCT 12
NON PRECISION APPROACH
(1)
Vertical Deviation Scale and Index
These symbols appear when in the approach phase and, when either FINAL is
armed/engaged or a non-LS approach has been entered. They are displayed in the
approach or go-around phase, until the MDA has been reached, or the MAP or the runway
has been sequenced. They give the vertical deviation from the trajectory defined by the
FMGC. Each index scale graduation represents 100 ft. The range is ± 200 ft.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←K→
DSC-31-40 P 21/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
Note:
If the LS pb is pressed, glide deviation has priority over vertical deviation
information. As long as VDEV display conditions are met, and the LS pb is
selected, an amber VDEV message flashes above the glide scale.
FLIGHT MODE ANNUNCIATOR
Ident.: DSC-31-40-00001246.0002001 / 09 OCT 12
Applicable to: ALL
For a detailed discussion of legends and messages that may appear during FMGS operations, see
FLIGHT GUIDANCE chapter (Refer to DSC-22_30-100 Flight Mode Annunciator (FMA) - General).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← K to L
DSC-31-40 P 22/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
TAILSTRIKE PITCH LIMIT INDICATOR
Ident.: DSC-31-40-00017534.0003001 / 21 MAR 16
Applicable to: ALL
(1)
Tailstrike Pitch Limit
The pitch limit indicates the maximum pitch attitude to avoid the tailstrike risk at landing. The
indication is a fixed value corresponding to the main landing gear compressed. The indication
appears at 400 ft radio height. The indication disappears, when there is no longer a risk of
tailstrike.
ALTITUDE ALERT
Ident.: DSC-31-40-00001247.0002001 / 22 MAY 12
Applicable to: ALL
The FWC generates an altitude warning (C chord sound and PFD’s altitude window pulses in yellow
or flashes in amber), when the aircraft approaches a preselected altitude or flight level, or when it
deviates from its selected altitude or flight level.
This warning results from a comparison between the altitude (ADIRS ) and the preselected altitude
displayed on FCU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
M to N →
DSC-31-40 P 23/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
‐ Selecting a new altitude, or pushing the ECAM’s EMER CANC pushbutton, or pressing either
MASTER WARN pushbutton, cancels the continuous C chord.
‐ Selecting a new altitude stops the flashing of the altitude window.
‐ The altitude alert is inhibited:
• When the slats are out, with the landing gear is selected down, or
• In approach after the aircraft captures the glideslope, or
• When the landing gear is locked down.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←N
DSC-31-40 P 24/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
FLAGS AND MESSAGES DISPLAYED ON PFD
Ident.: DSC-31-40-00001248.0012001 / 21 MAR 17
Applicable to: ALL
(1)
ATT flag (red)
If the PFD loses all attitude data, its entire sphere is cleared to display the ATT flag.
(2)
CHECK ATT , CHECK CAPT (F/O ) PFD , CHECK EWD , DU NOT MONITORED (amber)
For CHECK ATT, Refer to DSC-31-05-60 Side1/Side2 Discrepancy Messages
For more information, Refer to DSC-31-05-10 Introduction
(3)
SI flag (red)
If the sideslip information is lost or any reverse is deployed in flight, the index disappears and a
red SI flag appears.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
O→
DSC-31-40 P 25/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(4)
FPV flag (red)
In the TRK FPA mode, when the drift angle or flight path angle is not valid, an FPV flag
appears.
(5)
FD flag (red)
If both FMGC s fail, or if both FD s are disengaged and the FD pushbutton is on and the
attitude is valid, a red FD flag appears.
(6)
SPD flag (red)
If the speed information fails, a SPD flag replaces the speed scale.
(7)
SPD SEL flag (red)
If the selected speed information fails, a SPD SEL flag appears.
(8)
SPD LIM flag (red)
This flag appears when both FAC s are inoperative, or in case of SFCC dual flap/slat channel
failure.
In this case, the following PFD information is lost : VLS , S, F, Green Dot, Vtrend, Vmax, VFE
next, VSW.
(9)
V1 INOP flag (red)
When the V1 signal is not valid, a V1 INOP flag replaces the digital value.
(10) ALT flag (red)
If the altitude information fails, the ALT flag replaces the altitude scale.
(11) CHECK ALT flag (amber)
For more information, Refer to DSC-31-05-60 Side1/Side2 Discrepancy Messages
(12) ALT SEL flag (red)
If the selected altitude information fails, an ALT SEL flag appears.
(13) V/S flag (red)
If the vertical speed information fails, the V/S flag replaces the vertical speed scale.
(14) LOC and G/S flags (red)
If the localizer or glideslope receiver fails, a LOC or G/S flag appears on the deviation scale.
(15) VDEV flag (red)
If the vertical deviation information fails, and the LS pb is not pressed, a VDEV flag replaces
the VDEV scale.
(16) RA flag (red)
If both radio altimeters fail, this flag appears in place of the radio height indication.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←O→
DSC-31-40 P 26/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
(17) DH flag (amber)
A DH flag appears, when the aircraft reaches the selected DH.
(18) HDG flag (red)
If the heading information fails, the HDG flag replaces the heading scale.
(19) CHECK HDG flag (amber)
For more information, Refer to DSC-31-05-60 Side1/Side2 Discrepancy Messages
(20) MACH flag (red)
This flag appears, if the Mach data fails.
(21) VDEV (amber)
At the top of the glide scale, this message flashes in approach phase and, when either
the FINAL mode is armed/engaged, or a non-LS approach has been selected, and the LS
pushbutton is selected.
(22) DME 1 flag (red)
When the DME distance is not valid, a DME 1 (on PFD 1) or DME 2 (on PFD 2) flag replaces
the DME distance indication.
(23) ILS1 flag (red)
If an ILS frequency fails, or if either the LOC or G/S signals fail, an ILS 1 (on PFD 1) or ILS 2
(on PFD 2) flag replaces the ILS frequency indication.
(24) WINDSHEAR warning (red)
This message is displayed, when windshear is detected (reactive windshear warning) by the
FAC.
Refer to DSC-22_40-40 Windshear Detection Function
(25) W/S AHEAD
This message is displayed, when the predictive windshear system has detected windshear
ahead of the aircraft.
The message is in amber or red, depending on the alert level.
Refer to DSC-34-SURV-30-20 Windshear Alerts Inhibition
Note:
1. All flags, except, V1 INOP which is steady, flash for 9 s, then remain steady.
2. For information on the TCAS flag, Refer to DSC-34-SURV-60-20 PFD Indications.
(26) CHECK SD , CHECK CAPT (F/O ) ND (amber)
For more information, Refer to DSC-31-05-10 Introduction.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←O
DSC-31-40 P 27/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON PFD
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-31-40 P 28/28
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-31-45-00001249.0003001 / 21 MAR 16
Applicable to: ALL
There are five different displays (five modes to display navigation information) :
‐ ROSE LS
‐ ROSE VOR
‐ ROSE NAV
‐ ARC
‐ PLAN
The Navigation Display (ND) can provide a weather radar image in all modes, except PLAN.
ROSE MODES
Ident.: DSC-31-45-00001250.0002001 / 19 MAY 14
Applicable to: ALL
(1)
Aircraft symbol (yellow)
Fixed and centered in the display, this symbol points to the yellow lubber line.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-31-45 P 1/22
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(2)
Aircraft heading
The fixed yellow lubber line points to the aircraft magnetic heading on the moving white
compass rose. Small white triangles are fixed at 45 ° intervals on the circumference of the
compass rose.
“TRUE” appears at the top of the compass rose, when it is displaying true heading instead of
magnetic heading (latitude above 73 ° North or 60 ° South).
(3)
Selected heading or track (blue)
This pointer shows the heading or track indicated on the FCU 's HDG TRK counter.
(4)
Actual aircraft track (green)
This symbol is a small green diamond.
(5)
Ground speed and true air speed (green)
ADIRS furnishes these speeds.
(6)
Wind direction and speed
ADIRS provides the wind direction and speed. The digital direction and the analog direction
(indicated by the green arrow) both reflect the true north reference. The green arrow only
appears, if the wind speed is above two knots.
If the display does not receive either wind speed or direction, dashes replace the numbers on
the display.
(7)
NAVAIDs
When the ADF -OFF-VOR selector switch on either the pilot's or copilot's EFIS control panel is
set to ADF or VOR , the onside ND displays the following characteristics of the corresponding
NAVAID in white for VOR or in green for ADF (left side for receiver 1 and right side for receiver
2):
‐ Type of NAVAID (ADF or VOR)
‐ Shape and color of the associated bearing pointer (if the bearing pointer is in view).
‐ NAVAID identification (or frequency by default)
‐ DME distance if a DME is collocated with the selected VOR . ADF and DME distance are
never displayed at the same time.
‐ Mode of tuning
• M for a NAVAID tuned manually by the pilot through the MCDU (underlined and dimmed),
• R for a NAVAID tuned from an RMP (Radio Management Panel) (underlined and
dimmed),
• Nothing for a NAVAID tuned automatically by the FMGC.
If reception fails, the ND stops displaying the associated data (except for the identification or
frequency).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-31-45 P 2/22
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(8)
Bearing pointer (green for ADF , white for VOR)
This pointer appears when bearing data is available.
If the aircraft is not receiving the beacon or if a receiver fails, the associated bearing pointer
disappears.
(9)
Chronometer Indication (white)
These numbers appear when the onside chronometer is started.
They display the elapsed time.
The indication is in minutes and seconds from 0 to 59 min 59 s, and in hours and minutes from
1 h to 99 h 59 min (Seconds are not displayed beyond 59 min 59 s).
(10) Range marks
The range scale value selected on the EFIS control panel (10 to 320 NM) governs the scale of
the ND.
ROSE LS MODE
Ident.: DSC-31-45-00009584.0065001 / 24 NOV 15
Applicable to: ALL
(1)
ILS Course Pointer (Magenta)
This symbol points at the selected ILS course.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-31-45 P 3/22
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
The ILS is either selected by the FMGC (autotuned or manually) or manually selected by the
flight crew via the RMP backup mode. If no course has been entered, the default value is 360 °.
(2)
Localizer Deviation Bar (Magenta)
This bar moves laterally with respect to the course pointer. Its scale has two white dots on each
side of the zero deviation. Each dot corresponds to a deviation of approximately ±0.8 °.
If the lateral deviation exceeds 1/4 dot (0.2 °) above 15 ft RA, both the bar and the scale flash.
(3)
Glide Deviation (Magenta)
This diamond moves on a vertical scale that has two white dots on each side of the yellow
reference line. Each dot corresponds to a deviation of approximately ±0.4 °.
If the deviation exceeds one dot above 100 ft RA, both the scale and the diamond flash.
(4)
Selected ILS Information
This area displays the ILS frequency (magenta), selected course (magenta), and identification
(magenta).
(5)
ILS Message (Green)
This message indicates the full runway name of the selected approach. This message appears:
‐ The flight crew selects an ILS approach on the MCDU, and
‐ The FMS flight phase is DES , APP or GA , or the FMS phase is CRZ and the along track
distance to destination is less than 250 NM.
Note:
ILS 1 information appears on PFD 1 and ND 2.
ILS 2 information appears on PFD 2 and ND 1.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
DSC-31-45 P 4/22
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
ROSE VOR MODE
Ident.: DSC-31-45-00001252.0029001 / 05 NOV 15
Applicable to: ALL
(1)
VOR Course Pointer (Cyan)
This symbol points at the selected VOR course.
The VOR course is either automatically selected by the FMGC or manually selected by the
flight crew via the MCDU pages or the RMP backup mode.
(2)
Lateral Deviation Bar (Cyan)
This bar indicates the VOR deviation on a lateral scale.
Each dot corresponds to 5 ° of lateral deviation. When the lateral deviation exceeds 10 °, the
bar remains displayed on the outer dot.
The arrow on the bar provides the TO/FROM indication.
(3)
VOR Information (White and cyan)
This area displays the frequency and identification (if decoded by the receiver) of the selected
VOR in white, the selected course in cyan, and the tuning mode in white.
(4)
VOR or GPS Message (Green)
VOR 14L appears when the flight crew selects a VOR approach on the MCDU.
GPS 14L appears when the flight crew selects a GPS approach.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
DSC-31-45 P 5/22
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
ROSE NAV MODE/ARC MODE
Ident.: DSC-31-45-00001253.0017001 / 08 FEB 13
Applicable to: ALL
ROSE NAV and ARC modes give the pilot the same information, but ARC mode limits it to the
forward 90 ° sector.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
DSC-31-45 P 6/22
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(1)
Range Marks and Values
The values displayed on the ND are:
In ROSE NAV mode 1/4 of the selected range for the inner circle.
1/2 of the selected range for the heading scale circle.
In ARC mode
1/4 of the selected range for the first inner arc.
1/2 of the selected range for the second inner arc.
3/4 of the selected range for the third inner arc.
(2)
Flight Plan
The crew can use the MCDU to select various types of flight plan:
‐ The active flight plan (the flight plan the aircraft is actually following when the NAV mode is
engaged) is represented by a continuous green line. The ND shows only the part of the flight
plan that is ahead of the aircraft, as well as the waypoints that are still to be overflown and
the waypoint from which the aircraft is coming.
The ND does not show a SID or a STAR , except for the last waypoint of the SID and the first
waypoint of the STAR, when the selected range is 160 or 320 NM.
If the primary flight plan is not active, it is represented by a dotted green line.
‐ A continuous blue line portrays the missed approach procedure , and a dashed blue line
portrays the flight plan to the alternate.
The missed approach and the alternate flight plan are displayed when:
• In ARC or ROSE NAV mode, a missed approach waypoint or an alternate flight plan
waypoint is displayed on the onside MCDU.
• In PLAN mode a missed approach or alternate waypoint is displayed in the 2L field of the
onside MCDU.
‐ The secondary flight plan is represented by a continuous white line. The ND continues to
display the active flight plan
‐ Temporary flight plan
The revised portion of the flight plan is represented by a dotted yellow line
‐ Flight plan capture
When the aircraft is off the primary flight plan and is flying toward it in HDG mode with the
NAV mode armed, the ND shows the new active flight plan as a continuous green line if the
FMGC has computed the intercept path.
The part of the flight plan before the interception point shows as a dotted green line.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
DSC-31-45 P 7/22
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(3)
Waypoint
The ND can display various kinds of waypoints:
Flight plan waypoints
The ND displays these as green diamonds (white, for TO waypoints). When the flight
crew selects the WPT option on his EFIS control panel, all waypoints other than flight plan
waypoints are displayed in magenta.
Pseudo waypoint
Point of the flight path where the aircraft is predicted to reach a selected altitude or speed.
Pseudo
waypoint
Definition
Level symbol (top of climb or level-off position), when the aircraft reaches:
‐ The FCU-selected altitude (blue arrow), or
‐ The constrained altitude, if it is more restrictive than the FCU altitude and if appropriate modes are
engaged (magenta)
‐ It does not appear when the aircraft is within 100 ft above, or below, the selected altitude.
Top of descent symbol, or continue descent symbol:
‐ White, if DES is not armed
‐ Blue, if DES is armed.
Continued on the following page
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
Pseudo
waypoint
Continued from the previous page
Definition
Start of CLIMB symbol:
‐ White, if CLB is not armed
‐ Blue, if CLB is armed.
Intercept point symbol:
‐ White, if only the NAV mode is engaged
‐ Blue, if DES mode is engaged
‐ Indicates the point at which the aircraft is predicted to intercept the descent path, if there is any
vertical deviation while the aircraft is in DES mode.
Speed change symbol (magenta):
Indicates the point at which the aircraft will start an automatic acceleration or deceleration from the
current speed to a new computed speed for SPD LIM , SPD CSTR , or HOLDING SPD.
Decelerate point symbol:
‐ Indicates the point at which the aircraft is predicted to decelerate for approach (and thus switch to
the approach phase)
‐ Magenta, if in managed speed and NAV or approach mode is engaged
‐ White, if in selected speed or HDG /TRK mode
‐ Automatic decelerations only occur when displayed in magenta.
ALT CSTR symbol set around the constrained waypoint:
‐ Magenta, when the ALT CSTR is predicted to be met
‐ Amber, when the ALT CSTR is predicted to be missed
‐ White, when the ALT CSTR is not taken into account by the FMGS , and NAV mode is engaged.
Energy circle symbol (green arc) centered on the aircraft position and oriented to the current track line.
Represents the Required Distance to Land.
Only displayed if the lateral guidance mode is heading or track, and the current FMS flight phase is in
cruise, descent or approach, and the aircraft is within 180 NM of the destination.
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(4)
TO waypoint
This is the next waypoint to be overflown.
This area of the screen also shows:
‐ Waypoint identification (white)
‐ Track to go (green)
‐ Distance to go (green)
‐ Estimated time of arrival (green), assuming the aircraft will fly directly from its present
position to the TO waypoint at the current ground speed.
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FCOM
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DSC-31-45 P 10/22
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(5)
NAVAIDs
The display uses specific symbols for NAVAIDs:
DME or TACAN
VOR
VOR /DME
NDB
The symbol appears:
‐ In green if the NAVAID is a current waypoint of the flight plan
‐ In white if it is the TO waypoint
‐ In blue when the NAVAID is tuned for display either automatically by the FMGC or manually
through the MCDU
‐ In magenta when the NAVAID is not part of the flight plan and is called for display as an
option (corresponding option pushbutton pressed on the FCU EFIS control panel).
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(6)
Airport
Airport included in the flight plan:
‐ If the runway is not specified, the airport is represented by a star and the identification is
displayed in white.
Example: * LSGG
‐ If the runway is specified, it is represented by an oriented runway symbol in white.
Optional airport information
The airports that are not displayed as part of the flight plan may be called for display (ARPT pb
on the EFIS control panel).
They are represented by a star and the identification in magenta.
(7)
ILS Course (Magenta)
When the pilot pushes the LS pb-sw on the EFIS control panel, and if an ILS station has been
selected, the display shows an ILS course symbol.
(8)
ILS Marker Beacons
The screen shows these as waypoints (diamonds).
When the aircraft overflies a marker beacon, the corresponding symbol flashes:
Blue for the outer marker.
Amber for the middle marker.
White for the inner marker.
(9)
Cross Track Error
This is the aircraft's lateral deviation from the active leg of the flight plan (related to the great
circle route). It is indicated in nautical miles (NM), with the letter R (right) or L (left), according to
the position of the aircraft with respect to the flight plan.
(10) Track Line
This line appears in green only in the ROSE NAV or ARC mode when HDG or TRK has been
selected on the FCU.
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(11) Procedure turns and holding patterns
These only appear when they are part of the flight plan. For the 160 and 320 NM range scales,
each one is represented by a white arrow that originates at the associated fix and indicates the
direction of the turn.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
INDICATIONS ON ND
For shorter range scales, and if the procedure turn or the holding pattern is in the next or the
active leg, the display shows the full circuit or pattern.
PLAN MODE
Ident.: DSC-31-45-00001254.0002001 / 24 FEB 11
Applicable to: ALL
This mode statically displays the flight plan legs on a map oriented to true north. The map is centered
on a map reference point, that the pilot selects by scrolling to it on his MCDU.
The map reference point is the waypoint displayed on the second line of the MCDU 's F-PLN page. It
can either be the active waypoint (next waypoint to be overflown), or any other waypoint of the flight
plan.
The pilot can scroll through the overall flight plan, and display it in PLAN mode.
The pilot chooses the scale of the map with the range selector (the diameter of the outer circle
corresponds to the selected range).
Data on NAVAIDs and on their characteristics and associated bearing pointers are not available in
this mode.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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← E to F →
DSC-31-45 P 14/22
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(1)
Aircraft Position and True Track
The orientation of the yellow aircraft symbol always indicates the true track of the aircraft. Its
position represents the aircraft position given by the FMGS.
(2)
Map Reference Point
If the CSTR option is not selected, the track and distance from the map reference point to the
next F-PLN waypoint is displayed in magenta.
(3)
Cross Track Error
Refer to DSC-31-45 ROSE NAV Mode/ARC Mode.
WEATHER RADAR INDICATIONS
Ident.: DSC-31-45-00015503.0001001 / 21 MAR 17
Applicable to: ALL
Refer to DSC-34-SURV-30-30 Weather Radar indication on ND.
PWS INDICATIONS
Ident.: DSC-31-45-00015504.0001001 / 21 MAR 17
Applicable to: ALL
Refer to DSC-34-SURV-30-30 PWS (if installed) indication on PFD and ND
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to H
DSC-31-45 P 15/22
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
EGPWS
Ident.: DSC-31-45-00009586.0013001 / 08 AUG 13
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(1)
EGPWS terrain picture
The ND displays the EGPWS terrain picture, when the TERR ON ND switch is selected ON,
and the ND is not in PLAN mode. The terrain picture replaces the weather radar image. Terrain
data is displayed independently of the aircraft relative altitude.
The terrain appears in different colors and densities, in accordance with its relative height:
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INDICATIONS ON ND
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OPERATING MANUAL
Note:
(2)
‐ Areas without available terrain data in the EGPWS database appear in magenta
‐ The reference altitude is computed based on the current aircraft altitude or, if
descending more than 1 000 ft/min, the altitude expected in 30 s
‐ In case of flight above the maximum elevation number, the relief between the
minimum and maximum displayed elevations is displayed by using three different
green levels.
Center Part Messages
‐ The “TERR CHANGE MODE” indication is displayed in red (or amber), in the case of a
Terrain Awareness Display (TAD) warning (or caution) alert, if the current selected display
mode is PLAN
‐ The “TERR REDUCE RANGE” indication is displayed in red (or amber), in the case of a
Terrain Awareness Display (TAD) warning (or caution) alert, if the selected range is 160 NM
or 320 NM.
(3)
TERR indication
To differentiate between the terrain and the weather display, the weather radar TILT is replaced
by a blue TERR, and the terrain display sweeps from the center outward to both ND sides.
(4)
Warning and caution messages
TERRAIN or OBST (amber)
: For a caution.
TERRAIN or OBST (red)
: For a warning.
When triggered, these messages flash for 9 s, then remain steady until the caution or warning
alert condition disappears.
TERR RNG (red)
: For a RANGE error warning.
TERR TST (amber)
: Appears during the EGPWS test, when the terrain pattern
is displayed, and there is no failure.
(5)
Terrain or obstacle caution alert
Generated when a conflict exists between the terrain caution envelope, ahead of the aircraft,
and database-stored terrain/obstacles. The conflict area is shown in solid yellow.
(6)
Terrain or obstacle warning alert
Generated when a conflict exists between the terrain warning envelope, ahead of the aircraft,
and terrain/obstacles data stored in the database. The conflict area is shown in solid red.
Note:
When an alert is generated (either caution or warning) and TERR ON ND is not
selected, the terrain is automatically displayed and the TERR ON ND’s pushbutton
ON light comes on.
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(7)
INDICATIONS ON ND
Lowest and highest elevations
Minimum and maximum elevations encountered ahead of the aircraft, within the selected ND
range. The color code of the elevation figures is the same as for the EGPWS terrain picture.
Note:
The elevations shown on the ND correspond to the terrain included in the selected
ND range, ahead of the aircraft. In ARC mode, the elevations are linked with the
terrain displayed on the ND . In ROSE mode, the elevations may not represent the
lowest and highest terrain currently displayed on the ND.
FLAGS AND MESSAGES DISPLAYED ON ND
Ident.: DSC-31-45-00001256.0425001 / 21 MAR 17
Applicable to: ALL
(1)
HDG Flag (red)
If the heading data fails, the rose, arc and associated symbols disappear.
A HDG flag flashes for 9 s, then remains steady in the upper part of the ND.
(2)
CHECK HDG Flag (amber)
For more information: Refer to DSC-31-05-60 Side1/Side2 Discrepancy Messages
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DSC-31-45 P 19/22
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(3)
Center Part Messages
‐ The screen displays a MODE CHANGE message in green if there is a discrepancy between
the selected mode on the EFIS control panel and the mode sent from the onside FMGC , or
while the DMC is preparing a new page for display
‐ The screen displays a RANGE CHANGE message in green if there is a discrepancy
between the range selected on the EFIS control panel and the range sent from the onside
FMGC. A MODE CHANGE message has priority over a RANGE CHANGE message
‐ The screen displays a MAP NOT AVAIL message in red for several reasons:
• The MODE CHANGE or RANGE CHANGE message has been displayed more than 6 s,
or
• The FMGC has failed, or
• The FMGC has delivered an invalid aircraft position.
‐ The screen displays a W/S SET RNG 10 NM message if a predictive windshear alert is
triggered and the range is above 10 NM.
The message is displayed in the color corresponding to the windshear alert: red for a
warning, amber for a caution
‐ The screen displays a W/S CHANGE MODE message if a predictive windshear alert is
triggered and the ND is not in ARC or ROSE mode. The message appears in red for a
warning, or amber for a caution.
(4)
LOC Flag (red)
If LOC data fails, this flag flashes for 9 s, then remains steady.
(5)
G/S Flag (red)
If G/S data fails, this flag flashes for 9 s, then remains steady.
(6)
VOR Flag (red)
In ROSE VOR mode, when the VOR bearing is not valid, this flag flashes for 9 s, then remains
steady.
(7)
VOR 1(2) or ADF 1(2) or DME 1(2) Flag (red)
If a navigation receiver fails, the appropriate one of these flags flashes for 9 s, then remains
steady.
(8)
VOR Course Flag
If the VOR course fails, a red CRSXXX flag appears.
If there is non-computed data (NCD ), a blue CRS - - - flag appears.
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
(9)
Other messages
MAP PARTLY
DISPLAYED (amber)
:
NAV ACCUR UPGRAD, :
or (white) NAV ACCUR
DOWNGRAD (amber)
SPECIFIC VOR/D
:
UNAVAIL (amber)
BACK-UP NAV (amber) :
SET OFFSIDE
RNG/MODE (amber)
:
OFFSIDE FM CONTROL :
(amber)
GPS PRIMARY (white, :
boxed white)
GPS PRIMARY LOST
(amber, boxed white)
↓ (green)
:
:
In case of incomplete data transmission between the FMGC
(priority criteria) and the DMC , or if the DMC cannot draw the
complete MAP.
This message is also displayed when a very long leg exists
in the flight plan. A leg is considered as “very long” when the
starting point (or endpoint) is located at more than 45 ° from the
aircraft location (45 ° of longitude or latitude).
This DMC limitation results from a compromise between
accurate drawing precision and maximum leg length that can be
displayed.
Signals a change in navigation accuracy.
If the NAVAID, that is tuned for the selected approach or
departure, is not available.
If the MCDU back-up navigation mode is activated (Refer to
DSC-22_10-40-10 MCDU - MCDU Interface)
Displayed on ND 1(2), in case of an FMGC 1(2) failure when the
two ND ranges or modes selected on the EFIS control panels
are different.
If the offside FM supplies the onside ND.
This message appears when GPS PRIMARY mode is available,
or has been recovered. The pilot can clear this message by
pressing the CLR key on the MCDU.
This message appears when GPS PRIMARY is not available,
and not clearable by pilot action.
Overflow arrow, displayed when more than one of the following
messages are present at the same time:
‐ NAV ACCUR DOWNGRAD
‐ NAV ACCUR UPGRAD
‐ SPECIF VOR-D UNAVAIL
‐ MAP PARTLY DISPLAYED
‐ SET OFFSIDE RNG/MODE
‐ GPS PRIMARY
‐ GPS PRIMARY LOST
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DSC-31-45 P 21/22
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
INDICATIONS ON ND
FLIGHT CREW
OPERATING MANUAL
Note:
For information about the TCAS messages: Refer to DSC-34-SURV-60-20 TCAS
Messages.
(10) OFST R(L) XX message (yellow)
The screen displays this message, when a temporary or an offset flight plan is entered.
The offset value is given in NM.
Note:
For information about the TCAS messages: Refer to DSC-34-SURV-60-20 TCAS
Messages.
(11) PRED W/S flag (amber)
The WINDSHEAR sw on the weather radar panel is set to AUTO, and a Predictive Windshear
System fault is detected. This message appears on ground, or when flaps and slats are
extended.
It is associated with a single chime. The radar image remains available, provided that the fault
does not affect the radar mode.
(12) GPS message (green)
This message shows the full runway name of the selected approach. It is displayed, when the
flight crew selects a GPS approach.
(13) CHECK EWD , CHECK CAPT (F/O ) PFD , CHECK SD , CHECK CAPT (F/O ) ND (amber)
For more information: Refer to DSC-31-05-60 Feedback Messages
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←J
DSC-31-45 P 22/22
22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EFIS CONTROLS
FLIGHT CREW
OPERATING MANUAL
EFIS CONTROL PANEL
Ident.: DSC-31-50-00001257.0003001 / 09 OCT 12
Applicable to: ALL
(1)
Barometer Reference Display Window
Range : 745 hPa to 1 100 hPa.
(2)
Barometer Reference Selector
a. Outer ring
Note:
:
For selection of the units for the barometer reference-either hectoPascals
or inches of mercury.
The unit selected does not appear on the PFD.
b. Inner knob
:
For selection of the reference value displayed in the barometer reference
display window and on the PFD below the altitude scale.
At FCU initialization, the window displays 1 013 or 29.92, depending on the unit selected.
‐ Pulling the knob selects the standard BARO reference setting. The PFD then displays
“STD.” (Rotating the knob has no effect.)
‐ Pushing the knob from the STD position makes the last selected QNH BARO setting
available.
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EFIS CONTROLS
FLIGHT CREW
OPERATING MANUAL
(3)
FD pb
Pushing this button removes the FD bars from the associated PFD (or removes the flight path
director symbol if the TRK FPA reference is selected).
The pushbutton light goes out.
Pushing it again restores the FD bars (or the FPD symbol) and the green pushbutton light
comes on.
(4)
LS pb
Pushing this button displays the localizer and glide slope scales on the PFD.
Deviation symbols appear if there is a valid ILS signal.
The green pushbutton light comes on.
(5)
Mode Select Switch
This switch selects a navigation display for the onside ND.
(6)
Range Select Switch
This switch selects a range scale for the onside ND.
Note:
If the mode or the range data fails, the default selection is the ROSE NAV mode and
80 NM range.
(7)
ADF -VOR Select Switches
These switches select ADF or VOR bearing pointers and DME distance on the onside ND , as
well as the corresponding NAVAID data characteristics in any mode except PLAN mode.
(8)
Optional Data Display Pushbutton
Pushing this button displays optional data in addition to the data permanently displayed in
PLAN, ARC, or ROSE NAV modes. The green pushbutton light comes on.
Only one option can be activated at a time.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-31-50 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EFIS CONTROLS
FLIGHT CREW
OPERATING MANUAL
OTHER EFIS CONTROLS
Ident.: DSC-31-50-00001258.0002001 / 15 FEB 11
Applicable to: ALL
(1)
OFF/BRT knobs
• These knobs turn the PFD and ND display units on and off, and control their brightness.
• The display brightness adjusts automatically for changing light conditions, and is also
adjusted manually.
PFD Brightness Control Knob
Rotating this knob all the way counterclockwise switches off the PFD . In this case, the PFD
image is automatically displayed on the NDU, but the pilot may recover the ND by means of the
PFD -ND XFR pushbutton .
ND Brightness Control Knob
The outer knob controls the brightness of both the weather radar image and EGPWS terrain
display.
The inner knob controls the general brightness of the ND symbols.
Rotating this knob all the way counterclockwise switches off the NDU.
(2)
PFD /ND Pushbutton
Pushing this button interchanges the PFD and the ND.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
DSC-31-50 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
EFIS CONTROLS
FLIGHT CREW
OPERATING MANUAL
If the PFDU fails, the PFD automatically transfers to the NDU.
CHRONOMETER
Ident.: DSC-31-50-00001259.0001001 / 15 FEB 11
Applicable to: ALL
(1)
CHRONO Pushbutton
Pushing this button displays chronometer time on the onside ND.
Pushing it again freezes the displayed value.
Pushing it a third time resets the chronometer, and the chronometer time disappears from the
display.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C
DSC-31-50 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
CLOCK - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-31-55-10-00001260.0002001 / 21 MAR 16
Applicable to: ALL
A fully independent clock is on the right side of the control panel.
It sends time to the centralized fault data interface unit, the flight data interface unit, and the flight
management and guidance computer.
The clock has two electrical supplies, one of which is a direct connection to the aircraft battery hot
bus.
The clock performs four functions :
‐ It displays “UTC” (GMT) time in hours, minutes and seconds on the center counter.
‐ It displays elapsed time (ET) (from engine startup) in hours and minutes on the lower counter.
‐ It drives the chronometer (CHR), which measures a time interval (from the pushing of the
CHRONO button) in minutes and seconds.
‐ It can replace the UTC with the date.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-31-55-10 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
CLOCK - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-31-55-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CLOCK - CONTROLS AND INDICATORS
GENERAL
Ident.: DSC-31-55-20-00001261.0003001 / 16 MAR 11
Applicable to: ALL
(1)
UTC (GMT) counter
This counter displays the present time in 24 h format from 0 to 23 h 59 min 59 s.
(2)
Elapsed Time (ET)
This counter registers the elapsed time up to 99 h and 59 min.
(3)
Chrono (CHR) counter
This Counter registers elapsed time from 0 to 99 min 59 s. It is controlled by the CHR
pushbutton.
(4)
CHR pushbutton
First push
: starts the CHR counter
Second push : stops the CHR counter, keeps the display at its last indication.
(5)
Reset (RST) pushbutton
When pressed, the CHR counter restarts from 0 if the chrono is running.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-31-55-20 P 1/4
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
CLOCK - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(6)
ET selector
“RUN”
“STP”
spring loaded “RST”
Note:
(7)
the ET counter starts
the ET counter stops counting
the ET counter is blanked. The selector returns to its STP position
when the selector is released.
A cumulative elapsed time can be realized by alternatively setting this switch in “RUN”
and “STP” position.
DATE/SET pushbutton
First push
: sets the clock to date mode. The UTC time display is replaced by the date
(day month year).
Second push : sets the clock to time mode. The date display disappears.
Note:
(8)
:
:
:
in order to select the date mode, the UTC selector must be set on “GPS” or “INT”
position.
UTC selector
“GPS” : Time (or date, if selected) is displayed, and this data is synchronized on GPS
information.
Note:
“INT” :
Note:
“SET” :
‐ If the signal between the GPS and the clock is not detected, dashes are displayed.
Only the “INT” and “SET” positions are then available.
‐ If the signal is detected, but GPS data is invalid, the clock automatically runs on its
internal time.
‐ The clock will automatically resynchronize on the GPS information, as soon as the
GPS data becomes available.
Internal time (or date, if selected) is displayed.
‐ The clock’s internal time is initialized with the latest valid GPS information.
‐ If there is no valid GPS information at power up, the internal time will be 00:00:00,
until the clock is initialized.
Allows the internal time and date to be initialized.
OPERATION IN INTERNAL MODE
Ident.: DSC-31-55-20-00007126.0001001 / 21 MAR 17
Applicable to: ALL
DATE INITIALIZATION
Set the UTC selector on “SET”. The minute digits flash, and the seconds’ digits are blank.
To increase data, turn the DATE/SET button clockwise.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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22 MAR 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
CLOCK - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
To decrease data, turn the DATE/SET button counterclockwise.
‐
‐
‐
‐
First, push on DATE/SET
Second, push on DATE/SET
Third, push on DATE/SET
Fourth, push on DATE/SET
:
:
:
:
To set the hour.
To set the year.
To set the month.
To set the day.
Switch the UTC selector to the “INT” position, and the clock starts with the seconds’ digits at 00.
Note:
This process must be completed in less than one minute. Otherwise, it will be necessary
to reset the CFDS in order to synchronize the lower ECAM time display with the cockpit
clock display. Resetting the CFDS is a maintenance operation.
PRECAUTION IN CASE OF ATC DATALINK COMMUNICATION
If the clock is set to internal (INT) mode and the flight crew manually sets the time and date, the
clock does not comply with the time precision required for ATC datalink communication (+/-1 s
UTC). This may lead to the rejection of messages, or to the acceptance of obsolete messages:
‐ The CPDLC function will send CPDLC messages with an erroneous date/time
‐ The CPDLC function will accept obsolete uplink messages and may reject uplink messages with
a correct date/time
‐ The uplink messages for oceanic and departure clearance will be displayed in the Datalink
Control and Display Unit (DCDU) with an erroneous time
‐ The ADS-C function will continue to operate, but in a degraded mode.
To comply with the time precision requirement for ATC datalink communication, the flight crew
must either:
‐ Use the clock in GPS mode, or
‐ Use the clock in INT mode and synchronize the clock with the GPS at least one time per day.
This synchronization ensures that the UTC time drift is below +/- 1 s UTC.
GPS SYNCHRONIZATION IN INTERNAL MODE
When the clock is set to INT mode, the UTC time is only based on the internal clock and is not
synchronized with the GPS. To reset the drift that results from the UTC internal time, the flight
crew must perform the following actions:
‐ Set the UTC selector of the clock to the GPS mode and keep this setting during at least 10
seconds
‐ Then reset the UTC selector of the clock to INT mode.
These actions result in a resynchronization of the internal clock with the GPS.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
CLOCK - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLT RECORDERS - FLIGHT DATA RECORDING SYSTEM
DESCRIPTION
Ident.: DSC-31-60-10-00001262.0002001 / 09 OCT 12
Applicable to: ALL
The Flight Data Recording System, which records the mandatory parameters, consists of the
following components:
‐ A Flight Data Interface and Management Unit (FDIMU)
‐ A Digital Flight Data Recorder (DFDR)
‐ A three-axis Linear Accelerometer (LA)
The FDIMU collects and processes parameters from the SDAC s, DMC s, FWC s, FCDC s, BSCU ,
the DFDR event pushbutton, the GND CTL pushbutton and the Clock.
It stores the mandatory flight parameters in the DFDR.
The DFDR can store the last 25 h data, at least. It stores this data on a fireproof and shockproof
device. An underwater locator beacon is attached to the DFDR.
The linear accelerometer measures the acceleration of the aircraft along each of the three axes.
The QAR is an operational recorder that stores the same data as the DFDR . However the QAR is
more accessible for the maintenance crew.
The recording system is automatically active:
‐ On the ground, during the first five minutes after the aircraft electric network is energized.
‐ On the ground, after the first engine start.
‐ In flight (whether the engines are running or not).
On the ground, the recording system stops automatically five minutes after the second engine shuts
down.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLT RECORDERS - FLIGHT DATA RECORDING SYSTEM
On the ground, the crew can start the recording system manually by pressing the GND CTL
pushbutton.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-31-60-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLT RECORDERS - CONTROLS AND INDICATORS
OVERHEAD PANEL
Ident.: DSC-31-60-20-00001263.0001001 / 09 OCT 12
Applicable to: ALL
(1)
GND CTL pushbutton (springloaded)
ON : The Cockpit Voice Recorder (CVR) and the Flight Data Recorders are active. The
ON light is on.
AUTO : The Cockpit Voice Recorder (CVR) and the Flight Data Recorders are active,
according to the logic.
The system automatically switches from ON to AUTO at the first engine start, and also in case
of an electrical transient.
PEDESTAL
Ident.: DSC-31-60-20-00001264.0001001 / 22 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-31-60-20 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
FLT RECORDERS - CONTROLS AND INDICATORS
DFDR EVENT pushbutton
Pressing this button (briefly) sets an event mark on the Flight Data records.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-31-60-20 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLT RECORDERS - AIRCRAFT INTEGRATED DATA SYSTEM
DESCRIPTION
Ident.: DSC-31-60-30-00005369.0002001 / 09 OCT 12
Applicable to: ALL
The AIDS is used to monitor various aircraft system parameters in order to make maintenance easier
and to allow formulating operational recommendations.
The AIDS can generate system reports. The Airbus Standard Reports are preprogrammed reports
available at aircraft delivery. The operator can create its own reports.
The AIDS uses the Flight Data Interface and Management Unit (FDIMU) to acquire the relevant
aircraft system parameters. The FDIMU is connected to the rest of the AIDS as shown below.
The system may be programmed using the MCDU s. The crew can select any report to be displayed
on the MCDUs.
The Printer prints the flight phase programmed reports or any report selected on the MCDU.
This printing may be automatic or in response to the AIDS PRINT pushbutton.
The AIDS may send automatic reports via ACARS .
An optional Digital Recorder may be installed to extend the recording capacity.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
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AIRCRAFT SYSTEMS
INDICATING/RECORDING SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLT RECORDERS - AIRCRAFT INTEGRATED DATA SYSTEM
CONTROLS ON PEDESTAL
Ident.: DSC-31-60-30-00005370.0001001 / 20 DEC 10
Applicable to: ALL
(1)
AIDS PRINT pushbutton
Pushing this pushbutton causes the immediate printing of a specific report, depending on the
flight phase. The crew may then use the MCDU to select another report for immediate printing.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
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AIRCRAFT SYSTEMS
LANDING GEAR
Intentionally left blank
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-32-10 Gears and Doors
DSC-32-10-10 Description
General.....................................................................................................................................................................A
Main Landing Gear (MLG)...................................................................................................................................... B
Nose Landing Gear (NLG)...................................................................................................................................... C
Landing Gear Extension and Retraction Equipment...............................................................................................D
Landing Gears and Doors Operation...................................................................................................................... E
DSC-32-10-20 Landing Gear System/Interface
Landing Gear Control Interface Unit (LGCIU).........................................................................................................A
Proximity Detector Output Signals.......................................................................................................................... B
Proximity Detector Output Signals (Cont'd)............................................................................................................ C
DSC-32-10-30 Interactions between Landing Gear and Aircraft Systems
GENERAL................................................................................................................................................................ A
Proximity Detectors on Shock Absorbers................................................................................................................B
Proximity Detectors on Uplocks.............................................................................................................................. C
Proximity Detectors on Doors................................................................................................................................. D
Proximity Detectors on Downlocks..........................................................................................................................E
Proximity Detectors on Cargo Doors.......................................................................................................................F
Proximity Detectors on Flaps Attachments.............................................................................................................G
DSC-32-10-40 Controls and Indicators
Landing Gear Indicator Panel..................................................................................................................................A
Landing Gear Selector Lever.................................................................................................................................. B
Landing Gear Gravity Extension............................................................................................................................. C
WHEEL SD Page.................................................................................................................................................... D
Memo Display.......................................................................................................................................................... E
DSC-32-20 Nose Wheel Steering
DSC-32-20-10 Description
Description............................................................................................................................................................... A
Architecture.............................................................................................................................................................. B
DSC-32-20-20 Controls and Indicators
Side Consoles..........................................................................................................................................................A
WHEEL SD Page.................................................................................................................................................... B
Memo Display.......................................................................................................................................................... C
Continued on the following page
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AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-32-30 Brakes and Antiskid
DSC-32-30-10 Description
Continued from the previous page
General.....................................................................................................................................................................A
Anti-Skid System......................................................................................................................................................B
Auto Brake............................................................................................................................................................... C
Braking Modes.........................................................................................................................................................D
Braking Schematic................................................................................................................................................... E
DSC-32-30-20 Controls and Indicators
Center Instrument Panel..........................................................................................................................................A
Auto BRK Panel.......................................................................................................................................................B
Brake Fan .......................................................................................................................................................C
Pedestal................................................................................................................................................................... D
WHEEL SD Page.................................................................................................................................................... E
Memo Display.......................................................................................................................................................... F
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AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-32-10-10-00018598.0001001 / 21 MAR 16
Applicable to: ALL
The landing gear consists of :
‐ Two main landing gears that retract inboard
‐ One nose landing gear that retracts forward.
Doors enclose the landing gear bays. Gear and doors are electrically controlled and hydraulically
operated.
The doors, which are fitted to the landing gear struts, are operated mechanically by the gear and
close at the end of gear retraction.
All gear doors open while the gear is retracting or extending.
Two Landing Gear Control and Interface Units (LGCIU s) control the extension and retraction of the
gear and the operation of the doors. They also supply information about the landing gear to ECAM
for display, and send signals indicating whether the aircraft is in flight or on the ground to other
aircraft systems.
A hand crank on the center pedestal allows the flight crew to extend the landing gear if the aircraft
loses hydraulic systems or electrical power.
MAIN LANDING GEAR (MLG)
Ident.: DSC-32-10-10-00018599.0001001 / 21 MAR 16
Applicable to: ALL
Each main gear has twin wheels and an oleopneumatic shock absorber.
Each main wheel has an antiskid brake.
NOSE LANDING GEAR (NLG)
Ident.: DSC-32-10-10-00018600.0001001 / 21 MAR 16
Applicable to: ALL
The two-wheeled nose gear has an oleopneumatic shock strut and a nose wheel steering system.
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24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - DESCRIPTION
LANDING GEAR EXTENSION AND RETRACTION EQUIPMENT
Ident.: DSC-32-10-10-00018601.0001001 / 21 MAR 16
Applicable to: ALL
MAIN LANDING GEAR
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
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24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - DESCRIPTION
NOSE LANDING GEAR
LANDING GEARS AND DOORS OPERATION
Applicable to: ALL
Ident.: DSC-32-10-10-A-00018602.0001001 / 21 MAR 16
NORMAL OPERATION
The flight crew normally operates the landing gear by means of the lever on the center instrument
panel.
The LGCIU s control the sequencing of gear and doors electrically. One LGCIU controls one
complete gear cycle, then switches over automatically to the other LGCIU at the completion of the
retraction cycle. It also switches over in case of failure.
The green hydraulic system actuates all gear and doors. When the aircraft is flying faster than
260 kt, a safety valve automatically cuts off hydraulic supply to the landing gear system. Below
260 kt, the hydraulic supply remains cut off as long as the landing gear lever is up.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - DESCRIPTION
Ident.: DSC-32-10-10-A-00018603.0001001 / 21 MAR 16
LANDING GEAR GRAVITY EXTENSION
If the normal system fails to extend the landing gear hydraulically, the flight crew can use a crank
to extend it mechanically.
When a crew member turns the crank, it :
‐ Isolates the landing gear hydraulics from the green hydraulic system
‐ Unlocks the landing gear doors and the main and nose main gear
‐ Allows gravity to drop the gear into the extended position.
Locking springs help the crew to crank the main gear into the locked condition, and aerodynamic
forces assist in the locking of the nose gear.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - DESCRIPTION
The gear doors remain open.
The flight crew can reset the emergency extension system in flight after using it for training (if
green hydraulic pressure is available).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
DSC-32-10-10 P 5/6
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AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - LANDING GEAR SYSTEM/INTERFACE
LANDING GEAR CONTROL INTERFACE UNIT (LGCIU)
Applicable to: ALL
Ident.: DSC-32-10-20-A-00018604.0001001 / 21 MAR 16
GENERAL
The LGCIUs receive position information from the landing gear, cargo door, and landing flap
systems.
Ident.: DSC-32-10-20-A-00018605.0001001 / 21 MAR 16
LANDING GEAR INFORMATION
The LGCIUs receive landing gear position information from proximity detectors when:
‐ The landing gears are locked down or up, or
‐ The shock absorbers are compressed or extended, or
‐ The landing gear doors are open, or closed, or
‐ The bogie are aligned or not.
The LGCIUs send the landing gear position data to other aircraft systems.
In case of a LGCIU failure, the landing gear is controlled by the remaining healthy LGCIU.
Ident.: DSC-32-10-20-A-00018606.0001001 / 21 MAR 16
CARGO DOORS INFORMATION
Sensors send to the LGCIUs the position of the following components :
‐ Manuel selector valves
‐ Locking shaft
‐ Locking handle
‐ Safety shaft
‐ Door sills .
The LGCIUs detect electrical failures only in certain proximity switches in the cargo door system :
‐ Locking shaft
‐ Locking handle
‐ Safety shaft.
When an LGCIU makes such a detection, it indicates the NON LOCKED condition for that
component.
Ident.: DSC-32-10-20-A-00018607.0001001 / 21 MAR 16
LANDING FLAPS INFORMATION
The LGCIU s process the signals from four flap disconnect proximity switches, then send them to
the Slat/Flap Control Computers (SFCCs).
The LGCIU s do not monitor failures in the SFCC system.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A
DSC-32-10-20 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - LANDING GEAR SYSTEM/INTERFACE
PROXIMITY DETECTOR OUTPUT SIGNALS
Ident.: DSC-32-10-20-00001278.0001001 / 22 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
DSC-32-10-20 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - LANDING GEAR SYSTEM/INTERFACE
PROXIMITY DETECTOR OUTPUT SIGNALS (CONT'D)
Ident.: DSC-32-10-20-00001279.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-32-10-20 P 3/4
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AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - LANDING GEAR SYSTEM/INTERFACE
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AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN
LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-32-10-30-00001285.0001001 / 10 DEC 09
Applicable to: ALL
The following tables present the operational effects of the proximity detectors on aircraft systems.
How to read the tables :
SYSTEM
SERVICE INTERPHONE
SFCC 1(2)
LGCIU 1
6
5
LGCIU 2
6
(5)
A/C IN FLT
........
........
A/C ON GROUND
........
........
The above lines mean that the service interphone receives the output n° 6 from both LGCIU s, while
SFCC 1 receive the output 5 from LGCIU 1 and SFCC 2 the output 5 from LGCIU 2.
The two additional columns give the system functioning when the aircraft is in flight and on the
ground.
PROXIMITY DETECTORS ON SHOCK ABSORBERS
Ident.: DSC-32-10-30-00018608.0003001 / 06 SEP 16
Applicable to: ALL
SYSTEM
GENERAL
LGCIU 1 LGCIU 2
OUTPUT OUTPUT
A/C IN FLT
STROBE lts
5
LOGO lts
AIRSTAIRS
5
On when
AUTO selected
Off when flaps retracted
1
Control inhibited(1)
3
CARGO
DOOR(5)
WATER
FILLING
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
5
5
A to B →
Normal control
not available
Preselect water
servicing inhibited
A/C ON GRND
Off when AUTO selected
On
Control not inhibited(2)
Normal control available
Preselect water
servicing available
Continued on the following page
DSC-32-10-30 P 1/10
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN
LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW
OPERATING MANUAL
SYSTEM
AVNCS
COOLING
GRND
COOLING
AIR COND
APU AUTO
SHUTDOWN
A/C ON GRND
• Skin temp. < 35 °C • Skin temp. < 5 °C : The
: The system is in
system is in closed conf.(2)
closed conf.(1)
• Skin temp. > 5 °C : The
• Skin temp. > 35 °C
system is in open conf.(2)
: The system is in
intermediate conf. (1)
5
1
3
1
3
Inhibited(1)
Not inhibited(2)
5
Extract fan stopped
when ΔP > 1 PSI
Extract fan on
5
Climb mode active(4)
‐ Prepressurization active
before TO (3)
‐ Depressurization active after
LDG (3)
3
(1)
Pack air inlet
flaps opened
Pack air inlet flap fully
closed at TO and LDG
5
PACK 1(2)
TEMP
CONTROL
APU
A/C IN FLT
5
FWD CARGO
VENT
CAB PRESS
Continued from the previous page
LGCIU 1 LGCIU 2
OUTPUT OUTPUT
In case of oil low press,
automatic shutdown
is delayed by 15.5 s
5
‐ In case of oil low press,
the automatic shutdown is
delayed by :
• 15.5 s if the oil temp <
-4 °C
• 0.05 s if oil temp > -4 °C
Continued on the following page
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FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN
LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW
OPERATING MANUAL
SYSTEM
SERVICE
INTERPHONE
PUBLIC
ADDRESS
ADIRU and
AVIONICS
ground
warning
FLT
INTERPHONE
COCKPIT
CALL LIGHT
ACARS
(ACARS MU
COMMUNICATIONS or ATSU)
CVR
ELEC
A/C IN FLT
A/C ON GRND
6
6
Inhibited(6)
Available(7)
1
3
1
3
P.A. increased level(6)
P.A. low level(7)
1
3
1
3
External horn and
light inhibited(6)
External horn and
light not inhibited(7)
9
Communication
with ground
mechanic inhibited
Communication with
ground mechanic available
9
Inhibited
Not inhibited
7
Available
Available
1
3
7
1
3
5
CVR
DC generation
Continued from the previous page
LGCIU 1 LGCIU 2
OUTPUT OUTPUT
5
GALLEY
supply
5
EIS
EIS
5
FIRE
APU
5
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Runs(6)
Runs: (7)
‐ during the first 5 min
following energization
‐ with one engine running
Stops: (7)
5 min after second engine
shutdown
• ERASE function
inhibited
• No low frequency
signal in the
loudspeakers if test
performed
APU start on batteries
only, is delayed by 45 s
Main galley not supplied
when APU GEN
only is supplying
Display test inhibited
when ANN LT
TEST is selected
No APU fire automatic
extinguishing
←B→
• ERASE function not
inhibited
• Low frequency signal in
the loudspeakers if test
performed
No APU start delay
when on batteries only
Main galley supplied when
APU GEN only is supplying
Display test not inhibited
Automatic extinguishing
not inhibited
Continued on the following page
DSC-32-10-30 P 3/10
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN
LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW
OPERATING MANUAL
SYSTEM
FLT CTL
FLT INST
FUEL
SFCC 1(2)
• DFDR
• QAR
Continued from the previous page
LGCIU 1 LGCIU 2
OUTPUT OUTPUT
5
1
3
7
FQI
5
BLUE and
GREEN
pumps
1
3
BLUE pump
7
BLUE and
YELLOW
pumps
(5)
Runs(6)
FQI uses flight
attitude correction
due to wing bending
Blue or green pump
"FAULT" light not
inhibited when related
pump is stopped(6)
Runs when electrical
power is available
Blue or yellow pump
"FAULT" light not
inhibited when related
pump is stopped(6)
1
3
7
A/C ON GRND
• For SFCC 1(2):
• For SFCC 1(2):
Slats alpha/speed
Slats alpha/speed lock
lock function active
function active if speed >
• For SFCC (2):
60 kt
No flaps movement • For SFCC (2):
Flaps movement inhibition if
inhibition if the cargo
cargo door is opened
door is opened
1
3
HYD
PTU
A/C IN FLT
Runs: (7)
• During the first 5 min
following energization
• With one engine running
Stops: (7)
5 min after second engine shut
down
FQI uses ground
attitude correction
Blue or green pump
"FAULT" light inhibited when
related pump is stopped(7)
Runs when at least
one engine is running
Blue or yellow pump
"FAULT" light inhibited when
related pump is stopped(8)
PTU runs if green/yellow diff.
press > 500 PSI and
• both MASTER LEVERS are
at OFF or
• Both MASTER LEVERS are
PTU runs if green/yellow at ON or
diff. press > 500 PSI • Nose wheel steering is
not in towing position with
parking brake released.
PTU is inhibited during the use
of the cargo door hand pump
and for 40 s after its use.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-32-10-30 P 4/10
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN
LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW
OPERATING MANUAL
SYSTEM
ICE RAIN PROT
LANDING GEAR
NAVIGATION
CAPT , (F/O
), ((STBY ))
probes and
CAPT , (F/O)
windows
heating
4,
(2)
((8))
4,
(2)
((8))
WING
ANTI ICE
3
1
1
3
1
3
RAIN
REPELLENT
DRAIN
MAST(10)
L/G SAFETY
VALVE
L/G control
Continued from the previous page
LGCIU 1 LGCIU 2
OUTPUT OUTPUT
9
6
10
TIRE
PRESS
10
5
STAND
BY ALTI
5
ATC 1(2)
3
ADIRU 1(10)
7
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
(1)
A/C IN FLT
A/C ON GRND
• CAPT , (F/O ),
• With engines stopped: no
((STBY )) pitots
heating(8)
and CAPT , (F/O)
• With at least one engine
windows : high
running:
heating level applied • CAPT , (F/O ), ((STBY ))
• All other probes and
pitots and CAPT , (F/O)
windows are heated(6) windows are heated at low
level(8)
Wing anti ice valves
open when the WING
ANTI ICE pb is at ON(6)
Not inhibited(6)
Wing anti ice valves open
for 30 s when the WING
ANTI ICE pb is at ON(8)
Inhibited if engines
are stopped(7)
High heating
Low heating level is applied
level is applied
Safety valve closes if
Safety valve opened
aircraft speed > 260 kt
Retraction not inhibited(9)
Retraction inhibited(9)
"TYRE LO PRESS"
"TYRE LO PRESS" warning
warning threshold
threshold set to its ground level
set to its flight level
VIBRATION
VIBRATION function inhibited
function active
ATC 1(2) available
ATC 1(2) inhibited
in AUTO mode
in AUTO mode
No external horn
when ADIRU supplied
External horn not inhibited
from batteries only
Continued on the following page
←B→
DSC-32-10-30 P 5/10
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN
LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW
OPERATING MANUAL
SYSTEM
POWER PLANT
LGCIU 1 LGCIU 2
OUTPUT OUTPUT
FADEC 1(2)
Continued from the previous page
A/C IN FLT
A/C ON GRND
On ENG 1(2): (8)
• Reverse available
• Automatic start abort
available
• 5 min after eng-shut down
FADEC 1(2) no more
supplied
• FLEX available
• If installed, BUMP selectable
Modulated idle only available (7)
1
3
8
(1)
(3)
(8)
On ENG 1(2): (6)
• Reverse inhibited
• No automatic start
abort
• FADEC always
supplied
• FLEX not available
• If installed, BUMP not
selectable
1
3
8
(1)
(3)
(8)
Modulated idle
and approach idle
are available(6)
(1)
When either LGCIU indicates flight.
(2)
When both LGCIU indicate ground.
(3)
When either LGCIU indicates ground.
(4)
When both LGCIU indicate flight.
(5)
Valid from MSN 44.
(6)
When either output indicates flight.
(7)
When all outputs indicate ground.
(8)
When both outputs indicate ground.
(9)
One valid output is sufficient.
(10)
Valid from MSN 22.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-32-10-30 P 6/10
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN
LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW
OPERATING MANUAL
PROXIMITY DETECTORS ON UPLOCKS
Ident.: DSC-32-10-30-00018610.0002001 / 21 MAR 16
Applicable to: ALL
LGCIU 1 LGCIU 2
OUTPUT OUTPUT
SYSTEM
L/G control
LANDING GEAR
ECAM
WHEEL page
L/G indicator
panel
19
19
16
17
18
16
17
18
16
17
18
(1)
One valid output is sufficient.
(2)
When all outputs indicate the same position.
L/G UPLOCKED
L/G NOT UPLOCKED
If UP selected :(1)
L/G doors will close
If UP selected :(2)
L/G uplocked indications
If UP selected :(1)
L/G doors will not close
If UP selected :(2)
L/G in transit indications
If UP selected :(2)
no indication
If UP selected :(2)
"UNLK" red indications
PROXIMITY DETECTORS ON DOORS
Ident.: DSC-32-10-30-00018611.0001001 / 21 MAR 16
Applicable to: ALL
LANDING GEAR
(1)
SYSTEM
LGCIU 1
OUTPUT
L/G control
24
ECAM
WHEEL page
20
21
22
23
LGCIU 2
DOORS FULLY OPENED
DOORS CLOSED
OUTPUT
L/G extension or retraction L/G extension or retraction
24
possible (1)
inhibited (1)
20
Doors fully opened
Doors closed indication
21
indication
22
23
One valid output is sufficient.
PROXIMITY DETECTORS ON DOWNLOCKS
Ident.: DSC-32-10-30-00018613.0001001 / 21 MAR 16
Applicable to: ALL
SYSTEM
GEN
COMM
TAXI/T.O
lights
LGCIU 1
OUTPUT
LGCIU 2
OUTPUT
L/G DOWNLOCKED
L/G NOT DOWNLOCKED
15
Lights not inhibited
Lights inhibited
12
"NO SMOKING" and
"EXIT" signs on when
AUTO selected(2)
(1)
SIGNS
12
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to E →
"NO SMOKING" (1)and
EXIT" signs inhibited
when AUTO selected(3)
Continued on the following page
DSC-32-10-30 P 7/10
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN
LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW
OPERATING MANUAL
FLT INST
WBS
FMGS
FAC 1(2)
12
12
L/G control
14
14
ECAM
WHEEL
page
11
13
15
11
13
15
11
13
15
15
15
BSCU test operative(2)
BSCU test inhibited(3)
13
Cooling available
when ON selected
Cooling inhibited
when ON selected
"TOO LOW-FLAPS" or
"TOO LOW TERRAIN"
warning operative
"TOO LOW-GEAR" or
"TOO LOW TERRAIN"
warning operative
SYSTEM
LANDING GEAR
L/G INDIC
panel
BRAKING
STEERING
BRAKE
COOLING
FANS
NAV
GPWS
LGCIU 2
OUTPUT
15
Continued from the previous page
LGCIU 1
OUTPUT
15
13
(1)
For cabin not configured for non smoking flight
(2)
When either output indicates DOWNLOCK.
(3)
When both outputs indicate NOT DOWNLOCK.
(4)
When both outputs indicate DOWNLOCK.
(5)
When either output indicates NOT DOWNLOCK.
(6)
One valid output is sufficient.
(7)
When all outputs indicate the same position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
L/G DOWNLOCKED
L/G NOT DOWNLOCKED
Active
VLE indication
displayed on PFD 1(2)
If DOWN selected : (6)
L/G doors will close
If DOWN selected : (7)
L/G down indications
If DOWN selected : (6)
L/G doors will not close
If DOWN selected : (7)
L/G in transit indications
If DOWN selected :(7)
L/G down indications
If DOWN selected : (7)
L/G in transit indications
(4)
Inhibited (5)
No VLE indication
DSC-32-10-30 P 8/10
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - INTERACTIONS BETWEEN
LANDING GEAR AND AIRCRAFT SYSTEMS
FLIGHT CREW
OPERATING MANUAL
PROXIMITY DETECTORS ON CARGO DOORS
Ident.: DSC-32-10-30-00018614.0001001 / 21 MAR 16
Applicable to: ALL
LOCKING HANDLE OR SHAFT, DOOR SILLS
SYSTEM
CRG DOORS
ECAM
DOOR PAGE
LGCIU 1 LGCIU 2
OUTPUT OUTPUT
30
(31)
UNLOCKED
Forward (aft) door
normal opening inhibition
Forward (aft) door normal
operation possible
Forward (aft) door symbol
appears amber, associated
with "CARGO" amber
Forward (aft) door
normal opening possible
Forward (aft) door normal
operation inhibited
CLOSE
OPEN
Forward (aft) door
normal opening inhibition
Forward (aft) door
normal opening possible
Forward (aft) door
symbol appears green
34
(35)
36
(37)
CARGO
DOOR
OPERATION
LOCKED
MANUAL SELECTOR VALVE
SYSTEM
CRG DOORS
CARGO
DOOR
OPERATION
LGCIU 1 LGCIU 2
OUTPUT OUTPUT
32
(33)
PROXIMITY DETECTORS ON FLAPS ATTACHMENTS
Ident.: DSC-32-10-30-00001291.0001001 / 22 MAR 16
Applicable to: ALL
SYSTEM
FLT CTL
SFCC
LGCIU 1 LGCIU 2
OUTPUT OUTPUT
28
28
(29)
(29)
(1)
When at least one SFCC detects normal operation
(2)
When both SFCCs detect attachment failure
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F to G
FLAP ATTACHMENT
L(R) FLAPS
normal operation (1)
FLAP ATTACHMENT
FAILURE
"FLAPS LOCKED”
warning (2)
DSC-32-10-30 P 9/10
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - INTERACTIONS BETWEEN
LANDING GEAR AND AIRCRAFT SYSTEMS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-32-10-30 P 10/10
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
LANDING GEAR INDICATOR PANEL
Ident.: DSC-32-10-40-00018615.0001001 / 21 MAR 16
Applicable to: ALL
This panel is connected to LGCIU1, which receives signals from proximity detectors.
▿ light: comes on green if the gear is locked down.
UNLK: comes on red if the gear is not locked in the selected position.
light
Note:
This panel is connected to the LGCIU1 only, therefore, the lights on the LDG GEAR
indicator panel come on as long as the LGCIU1 is electrically supplied.
If one UNLK indication remains on, the landing gear position can be confirmed using the
WHEEL SD page (information from LGCIU 1 & 2). Only one green triangle on each landing
gear is sufficient to confirm that the landing gear is downlocked.
LANDING GEAR SELECTOR LEVER
Ident.: DSC-32-10-40-00018616.0001001 / 20 MAY 16
Applicable to: ALL
A two-position selector lever sends electrical signals to the two LGCIUs. These control the green
hydraulic supply to the landing gear system by means of selector valves.
The flight crew must always move the L/G lever in one continuous movement (i.e. with no stop
between both positions).
When the flight crew selects UP or DOWN (and if the airspeed is below 260 kt):
‐ All landing gear doors open
‐ Each landing gear moves to the selected position
‐ All landing gear doors close.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-32-10-40 P 1/6
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - CONTROLS AND INDICATORS
(1)
L/G LEVER
UP
: This position selects landing gear retraction.
While the landing gear doors are opening, the normal brake system brakes the
wheels of the main landing gear automatically.
A brake band in the nose landing gear well brakes the nose landing gear wheels as
the doors close (for aircraft equipped with nose landing gear rubbing strips).
DOWN : This position selects landing gear extension.
An interlock mechanism prevents anyone from accidentally retracting the gear
while the aircraft is on the ground. It does so by locking the lever in DOWN position
when the shock absorber on either main gear is compressed (aircraft on ground) or
the nose wheel steering is not centered.
The landing gear hydraulic system remains pressurized as long as the landing gear
is extended (if green hydraulic pressure is available).
(2)
RED ARROW
This red arrow lights up if the landing gear is not locked down when the aircraft is in the landing
configuration, and a red warning appears on ECAM.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-32-10-40 P 2/6
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
GEARS AND DOORS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
LANDING GEAR GRAVITY EXTENSION
Ident.: DSC-32-10-40-00018617.0001001 / 21 MAR 16
Applicable to: ALL
To put the landing gear down by gravity, the flight crew must pull the gear crank out, then turn it
clockwise for 3 turns.
When the flight crew operates the crank handle, the cutout valve shuts off hydraulic pressure to the
landing gear system and depressurizes it.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-32-10-40 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - CONTROLS AND INDICATORS
WHEEL SD PAGE
Ident.: DSC-32-10-40-00018618.0004001 / 21 MAR 16
Applicable to: ALL
(1)
Landing gear position indication
The landing gear positions are indicated by 2 triangles for each gear:
‐
‐
‐
‐
Green triangle indicates that one LGCIU detects a landing gear downlocked
Red triangle indicates that one LGCIU detects a landing gear in transit
No triangle indicates that one LGCIU detects a landing gear uplocked
Amber crosses on one triangle indicate that LGCIU 1 or LGCIU2 is failed.
Note:
Only one green triangle on each landing gear strut is sufficient to confirm that the
landing gear is downlocked.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
DSC-32-10-40 P 4/6
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - CONTROLS AND INDICATORS
(2)
Landing gear door position indication
(3)
UP LOCK
This legend appears amber along with a caution on the ECAM if the landing gear uplock is
engaged when the landing gear is down locked.
(4)
L/G CTL
This legend appears amber along with an ECAM caution if the landing gear lever and the
landing gear position do not agree. This legend only appears when the landing gear is moving
to the selected position.
MEMO DISPLAY
Ident.: DSC-32-10-40-00018778.0001001 / 22 MAR 16
Applicable to: ALL
FLT L/G DOWN
:
This memo appears in green if the aircraft is operated in ferry flight
conditions with landing gear down.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E
DSC-32-10-40 P 5/6
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GEARS AND DOORS - CONTROLS AND INDICATORS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-32-10-40 P 6/6
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
NOSE WHEEL STEERING - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-32-20-10-00018619.0007001 / 21 MAR 16
Applicable to: ALL
A hydraulic actuating cylinder steers the nose wheel. The yellow hydraulic system supplies pressure
to the cylinder, and electric signals from the Brake and Steering Control Unit (BSCU) control it.
The BSCU receives orders from:
‐ Captain's, and the First Officer’s steering hand wheels (orders added algebraically), or
‐ Rudder pedals, or
‐ Autopilot.
The BSCU transforms these orders into nose wheel steering angle. That angle has the following
limits, which depend on ground speed and the origin of the orders.
The steering system receives actuating hydraulic pressure when:
‐ A/SKID & N/W STRG switch is ON
‐ Towing control lever is in normal position
‐ At least one engine is running
‐ Aircraft is on ground.
The handwheel can turn the nosewheel up to 75 ° in either direction. A lever, on the towing electrical
box (on nose landing gear), enables ground crew to deactivate the steering system for towing. Then
the wheel can be turned 95 ° in either direction.
To prevent rudder pedal orders, or autopilot orders, from going to the BSCU, the pilots can use the
pushbutton on either steering handwheel.
00000An internal cam mechanism returns the nose wheel to the centered position after takeoff.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-32-20-10 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
NOSE WHEEL STEERING - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
ARCHITECTURE
Ident.: DSC-32-20-10-00001298.0002001 / 21 MAR 16
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
DSC-32-20-10 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NOSE WHEEL STEERING - DESCRIPTION
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-32-20-10 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
NOSE WHEEL STEERING - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-32-20-10 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NOSE WHEEL STEERING - CONTROLS AND INDICATORS
SIDE CONSOLES
Ident.: DSC-32-20-20-00018620.0001001 / 21 MAR 16
Applicable to: ALL
(1)
Steering handwheels
The steering handwheels, which are interconnected, can steer the nose wheel up to 75 ° in
either direction.
Note:
(2)
The steering system centers the nose wheel automatically after liftoff.
Rudder PEDALS DISC pb
Pressing this button on either handwheel removes control of nose wheel steering from the
rudder pedals until the button is released.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-32-20-20 P 1/2
05 SEP 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NOSE WHEEL STEERING - CONTROLS AND INDICATORS
WHEEL SD PAGE
Ident.: DSC-32-20-20-00018622.0004001 / 21 MAR 16
Applicable to: ALL
(1)
N/W STEERING indication
It appears in amber, when nosewheel steering is lost, due to failure of the nosewheel steering
system, or of both BSCU channels, or in case of a yellow hydraulic system low pressure, or if
the A/SKID & N/W STRG switch is OFF.
(2)
N/W STEERING hydraulic supply indication:
Only when the N/W STEERING indication is displayed, Y is displayed:
‐ In green when the yellow hydraulic system is not failed, or
‐ In amber when the yellow hydraulic system low pressure.
MEMO DISPLAY
Ident.: DSC-32-20-20-00016853.0001001 / 10 AUG 15
Applicable to: ALL
NW STRG DISC
:
NW STRG DISC
:
This memo appears in green, when the nose wheel steering selector is in
the towing position.
This memo appears in amber, if one engine is running.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B to C
DSC-32-20-20 P 2/2
05 SEP 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
BRAKES AND ANTISKID - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-32-30-10-00018623.0002001 / 21 MAR 16
Applicable to: ALL
The main wheels are equipped with carbon multidisc brakes, which can be actuated by either of two
independent brake systems.
The normal system uses green hydraulic pressure, whereas the alternate system uses the yellow
hydraulic system backed up by the hydraulic accumulator.
An anti-skid and autobrake system is also provided.
Braking commands come from either the brake pedals (pilot action), or the autobrake system
(deceleration rate selected by the crew).
In normal operation, a dual channel Brake and Steering Control Unit (BSCU) controls normal braking
and antiskid.
Depending on the failure, braking may revert to:
‐ Alternate braking with antiskid. This braking mode is controlled by the Alternate Braking Control
Unit (ABCU ), and the antiskid is controlled by the BSCU
‐ Alternate braking without antiskid. This braking mode is fully-controlled by the ABCU
‐ Alternate braking without antiskid on accumulator. This braking mode is fully-controlled by the
ABCU.
All the normal and alternate braking components are fully-monitored. Any detected failure is signaled
to the crew via ECAM warnings.
The BSCU performs the following secondary functions:
‐ Checks the residual pressure in the brakes
‐ Monitors the brake temperature
‐ Provides discrete wheel speed information to other aircraft systems.
A changeover between the two BSCU channels takes place at each DOWN landing gear lever
selection, or in case one channel fails.
The main gear wheels are fitted with fusible plugs which protect against tire burst, in the event of
overheat.
Main gear wheels are also equipped with brake cooling fans , which permit a high speed cooling
of brakes.
ANTI-SKID SYSTEM
Ident.: DSC-32-30-10-00018624.0001001 / 21 MAR 16
Applicable to: ALL
The antiskid system provides maximum braking efficiency by maintaining the wheels at the limit of an
impending skid.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-32-30-10 P 1/6
22 MAR 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
BRAKES AND ANTISKID - DESCRIPTION
At skid onset, brake release orders are sent to the normal and alternate servovalves, as well as to
the ECAM system which displays the released brakes.
Without using autobrake, full braking performance is achieved only with brake pedals at full
deflection.
The antiskid system is deactivated below 20 kt (ground speed).
An ON/OFF switch activates, or deactivates, the antiskid and nosewheel steering systems.
PRINCIPLE
The speed of each main gear wheel (given by a tachometer) is compared to the aircraft speed
(reference speed). When the speed of a wheel decreases below approximately 0.87 times
(depending on conditions) reference speed, brake release orders are given to maintain the wheel
slip at that value (best braking efficiency).
In normal operation, the reference speed is determined by the BSCU from the horizontal
acceleration of ADIRU 1, or ADIRU 2, or ADIRU 3.
In case all ADIRUs fail, reference speed equals the maximum of either main landing gear wheel
speeds.
AUTO BRAKE
Applicable to: ALL
Ident.: DSC-32-30-10-A-00018625.0001001 / 21 MAR 16
GENERAL
The purposes of the autobrake system are the following:
‐ Reduce the braking distance in case of an aborted takeoff
‐ Establish and maintain a selected deceleration rate during landing, thereby improving
passenger comfort and reducing crew workload.
Ident.: DSC-32-30-10-A-00018626.0002001 / 21 MAR 16
SYSTEM ARMING
The crew may arm the system by pressing the LO, MED , or MAX pushbutton provided all the
following arming conditions are met :
‐ Green pressure available
‐ Anti-skid electrically-powered
‐ No failure in the braking system
‐ At least one ADIRU is available.
Note:
1. Auto brake may be armed with the parking brake on.
2. MAX autobrake mode cannot be armed in flight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-32-30-10 P 2/6
22 MAR 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
BRAKES AND ANTISKID - DESCRIPTION
Ident.: DSC-32-30-10-A-00018627.0002001 / 21 MAR 16
SYSTEM ACTIVATION
Automatic braking is activated when:
‐ The command for ground spoilers extension is detected (Refer to DSC-27-10-20 Speed Brakes
and Ground Spoilers - Speed Brake Control), for LO and MED mode, or
‐ The command for ground spoilers extension is detected, and the aircraft speed is above 40 kt,
for MAX mode.
Therefore, if the aircraft makes an acceleration stop and begins to decelerate when its speed is
under 72 kt, the automatic braking will not activate because the ground spoilers will not extend.
For autobrake to activate, at least two SEC’s must be operative.
Ident.: DSC-32-30-10-A-00018628.0001001 / 21 MAR 16
SYSTEM DEACTIVATION
The system deactivates when:
‐ The system disarmed (Refer to DSC-32-30-10 Auto Brake - System Disarming), or
‐ The ground spoilers retract. In this case it remains armed.
Ident.: DSC-32-30-10-A-00018629.0002001 / 21 MAR 16
The system disarms when:
‐ Flight crew presses the pushbutton switch, or
‐ One or more arming conditions is lost, or
‐ After take-off/touch and go, or
‐ Flight crew applies enough deflection to at least one brake pedal when autobrake is active in MAX
, MED or LO mode.
BRAKING MODES
Applicable to: ALL
Ident.: DSC-32-30-10-B-00018630.0001001 / 21 MAR 16
GENERAL
There are four modes of operation:
‐ Normal braking
‐ Alternate braking with antiskid
‐ Alternate braking without antiskid
‐ Parking brake.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
DSC-32-30-10 P 3/6
22 MAR 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
BRAKES AND ANTISKID - DESCRIPTION
Ident.: DSC-32-30-10-B-00018631.0001001 / 21 MAR 16
NORMAL BRAKING
Normal braking is operative when:
‐ Green hydraulic pressure is available
‐ A/SKID & N/W STRG switch is ON.
During normal braking, antiskid is operative and autobrake is available.
Braking is electrically-controlled through the BSCU from:
‐ Pilot’s pedals, or
‐ Automatically activates when:
• On ground by the autobrake system, or
• In flight when the landing gear lever is up.
The antiskid system is controlled by the BSCU via the normal servo valves.
There is no brake pressure indication in the cockpit.
Ident.: DSC-32-30-10-B-00018632.0002001 / 17 MAR 17
ALTERNATE BRAKING WITH ANTI-SKID
Autobrake is inoperative.
Braking uses this mode when green hydraulic pressure is insufficient, and :
‐ Yellow hydraulic pressure is available
‐ A/SKID & N/W STRG switch is ON
‐ Parking brake is not ON.
Braking inputs are made by the brake pedals and sent to the ABCU . Then, taking into account the
brake pedal input, the ABCU:
‐ Energizes the alternate brake selector valve to pressurize the yellow hydraulic circuit
‐ Electrically controls the Alternate Servo Valve to obtain the correct pressure for the related
brakes.
Antiskid is controlled by the BSCU.
A triple indicator on the center instrument panel indicates the pressure delivered to the left and
right brakes, as well as the accumulator pressure.
Note:
Initial pedal force or displacement produces more braking action in alternate mode than
in normal mode.
Ident.: DSC-32-30-10-B-00018633.0002001 / 17 MAR 17
ALTERNATE BRAKING WITHOUT ANTI-SKID
Autobrake and antiskid are inoperative.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-32-30-10 P 4/6
22 MAR 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
BRAKES AND ANTISKID - DESCRIPTION
The antiskid system is either deactivated:
‐ Electrically (A/SKID & N/W STRG sw OFF, or power supply failure, or BSCU failure), or
‐ Hydraulically (Y + G system low pressure, the brakes are supplied by the brake accumulator
only).
Depending on the brake pedals’ demand, the ABCU controls the alternate brake selector and the
alternate servovalves.
Brake pressure and accumulator pressure are indicated on a triple indicator, located on the
center instrument panel. To avoid wheel locking and limit the risk of tire burst, brake pressure is
automatically limited to 1 000 PSI.
The accumulator can supply at least 7 full brake applications.
Note:
Initial pedal force or displacement produces more braking action in alternate mode than
in normal mode.
Ident.: DSC-32-30-10-B-00018634.0002001 / 21 MAR 16
PARKING BRAKE
Brakes are supplied by the yellow hydraulic system, or by accumulator pressure via the parking
brake control valve, which opens allowing full pressure application on the main gear wheel brakes.
The accumulator maintains the parking pressure for at least 12 h.
If the parking brake is activated and no yellow hydraulic or accumulator brake pressure is
available, then the normal braking system can be applied via the brake pedals.
Yellow accumulators can be pressurized by pressing the yellow electrical pump switch.
A triple indicator on the center instrument panel indicates the pressure delivered to the left and
right brakes, as well as the accumulator pressure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
DSC-32-30-10 P 5/6
22 MAR 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
BRAKES AND ANTISKID - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
BRAKING SCHEMATIC
Ident.: DSC-32-30-10-00001316.0003001 / 09 OCT 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
DSC-32-30-10 P 6/6
22 MAR 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
CENTER INSTRUMENT PANEL
Ident.: DSC-32-30-20-00018635.0002001 / 21 MAR 16
Applicable to: ALL
(1)
A/SKID & N/W STRG sw
ON : If green hydraulic pressure is available, then antiskid is available.
If green hydraulic pressure is lost, then:
‐ Yellow hydraulic pressure automatically takes over to supply the brakes
‐ Antiskid and nosewheel steering remain available
‐ Triple indicator shows yellow system brake pressure.
OFF :
The yellow hydraulic system supplies pressure to the brakes.
‐ Antiskid is deactivated. The pilot must refer to the triple indicator to limit brake
pressure and avoid locking a wheel
‐ Nosewheel steering is lost
‐ Differential braking remains available through the pedals
‐ Triple indicator displays yellow system brake pressure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-32-30-20 P 1/8
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(2)
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
BRAKES and ACCU PRESS indicator
Brake pressure is only indicated when the yellow hydraulic system controls the brake pressure,
This is when the:
‐ Alternate braking system is activated, or
‐ Parking brake is applied.
ACCU :
PRESS
BRAKES :
Indicates the pressure in the yellow brake accumulator.
Indicates the yellow pressure delivered to the left and right brakes, as measured
upstream of the alternate servovalves.
AUTO BRK PANEL
Ident.: DSC-32-30-20-00018636.0002001 / 21 MAR 16
Applicable to: ALL
(3)
AUTO/BRK panel
The springloaded MAX , MED , and LO pushbutton switches arm the appropriate deceleration
rate. The usage for each mode are as follow:
‐ MAX mode is normally selected for takeoff.
In the case of an aborted takeoff, maximum pressure goes to the brakes, as soon as the
system generates the ground spoiler deployment order
‐ MED or LO mode is normally selected for landing:
• MED mode sends progressive pressure to the brakes 2 s after the ground spoilers deploy
in order to decelerate the aircraft at 3 m/s² (9.8 ft/s²)
• LO mode sends progressive pressure to the brakes 4 s after the ground spoilers deploy, in
order to decelerate the aircraft at 1.7 m/s² (5.6 ft/s²).
The lighting on the pushbutton switches are as follow:
ON light
: comes on blue to indicate positive arming
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-32-30-20 P 2/8
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
DECEL light
:
comes on green when the actual deceleration is 80 % of the selected
rate
Note:
Off :
On slippery runways, the predetermined deceleration may not
be reached, due to antiskid operation. In this case, the DECEL
light will not come on. This does not mean that autobrake is
not working.
The corresponding autobrake mode is not armed
BRAKE FAN
Ident.: DSC-32-30-20-00018637.0001001 / 21 MAR 16
Applicable to: ALL
(4)
BRK FAN pb-sw
ON light : The brake fans run if the lefthand main landing gear is down and locked
Off
: The brake fans stop
HOT : This amber light comes on when the brakes get too hot (A caution appears on
light
ECAM, also)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C
DSC-32-30-20 P 3/8
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
PEDESTAL
Ident.: DSC-32-30-20-00018638.0001001 / 21 MAR 16
Applicable to: ALL
(1)
PARKING BRK handle
Flight crew pulls this handle, then turns it clockwise, to apply the parking brake.
The ECAM memo page displays “PARK BRK”.
CAUTION
If the pointer is not at ON, the parking brake is not on.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
DSC-32-30-20 P 4/8
24 JAN 17
AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
WHEEL SD PAGE
Ident.: DSC-32-30-20-00018639.0008001 / 21 MAR 16
Applicable to: ALL
(1)
Release indicators
It appears in amber in case of brake released fault.
(2)
ANTI SKID indication
(A) ANTISKID label
It appears in amber, a long with an ECAM caution, in case of a total BSCU failure, or
when the A/SKID & N/W STRG sw is OFF, or if the BSCU detects an ANTI-SKID failure,
or in case of normal braking and yellow hydraulic system low pressure.
It appears in green in case of autobrake, normal braking, or alternate braking failure, and
antiskid is still available.
(B) BSCU channel indication
When ANTISKID label is displayed, the number of the failed system(s) is (are) displayed
in amber, if any.
(3)
AUTO BRK
This legend appears:
‐ In green when auto brake is armed, or
‐ Flashing green for 10 s after autobrake disengagement, or
‐ In amber, along with an ECAM caution, to indicate a system failure.
MED , LO, or MAX appears underneath in green to show which rate has been selected.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
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AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
(4)
Wheel number
This white number identifies individual wheels of the main landing gear.
(5)
Brake temperature
‐ Temperature normally appears in green.
‐ Green arc appears on the hottest wheel when one brake temperature exceeds 100 °C.
‐ Green arc becomes amber, and an ECAM caution appears, when the corresponding brake
temperature exceeds 300 °C.
(6)
NORM BRK indication
(A) NORM BRK label
This indication appears in green when autobrake or alternate braking is failed, and
normal braking is still available.
The legend appears in amber when normal braking is failed due to total BSCU failure, or
to the loss of the green hydraulic pressure, or to the loss of antiskid.
(B) NORM BRK hydraulic supply indication
G is displayed when the NORM BRK label is displayed. It is green when green hydraulic
pressure is available and amber, in case of green hydraulic low pressure.
(7)
(A) ALTN BRK label
This indication appears in green, if the braking system is in alternate mode and not failed,
or in case autobrake or normal braking is failed and alternate braking is still available.
This indication appears in amber when alternate braking is failed.
(B) ALTN BRK hydraulic supply indication
Y is displayed when the ALTN BRK label is displayed. It is green when yellow hydraulic
pressure is available and amber, in case of yellow hydraulic low pressure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
DSC-32-30-20 P 6/8
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AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(C) ACCU indications
(*)
Appears in green, when the ALTN BRK label is displayed, and the yellow hydraulic
pressure is available.
Appears in amber, with no arrow, when the yellow hydraulic system and the
accumulator are in low pressure.
(**) Appears in green when the alternate braking is pressurized by the yellow
accumulator.
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-32-30-20-A-00016854.0001001 / 22 MAR 16
AUTO BRK LO/MED/MAX :
This memo appears in green, depending on the selection of the
AUTO BRK pb.
Ident.: DSC-32-30-20-A-00016855.0001001 / 22 MAR 16
AUTO BRK OFF
:
This memo appears in green if the auto brake is failed.
Ident.: DSC-32-30-20-A-00016856.0001001 / 22 MAR 16
BRK FAN
:
This memo appears in green if the BRK FAN pb is ON.
Ident.: DSC-32-30-20-A-00016857.0001001 / 22 MAR 16
PARK BRK
:
This memo appears in green, if the parking brake is ON, during flight
phases 1, 2, 9 and 10.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F
DSC-32-30-20 P 7/8
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AIRCRAFT SYSTEMS
LANDING GEAR
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
BRAKES AND ANTISKID - CONTROLS AND INDICATORS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-32-30-20 P 8/8
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AIRCRAFT SYSTEMS
LIGHTS
Intentionally left blank
AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-33-10 Cockpit Lighting
DSC-33-10-10 General
General.....................................................................................................................................................................A
DSC-33-10-20 Description
Description............................................................................................................................................................... A
Schematic.................................................................................................................................................................B
DSC-33-10-30 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Maintenance Panel.................................................................................................................................................. B
Lateral Window........................................................................................................................................................ C
Pedestal................................................................................................................................................................... D
Glareshield............................................................................................................................................................... E
Main Inst Panel........................................................................................................................................................ F
DSC-33-20 Exterior Lighting
DSC-33-20-10 General
General.....................................................................................................................................................................A
DSC-33-20-20 Controls and Indicators
Schematic.................................................................................................................................................................A
Overhead Panel....................................................................................................................................................... B
Memo Display.......................................................................................................................................................... C
DSC-33-30 Emergency Lighting
DSC-33-30-10 Description
General.....................................................................................................................................................................A
Proximity Emergency Escape Path Marking System/Exit Signs............................................................................. B
DSC-33-30-20 Controls and Indicators
Controls and Indicators............................................................................................................................................A
DSC-33-40 Signs
DSC-33-40-10 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Memo Display.......................................................................................................................................................... B
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-33-PLP-TOC P 1/2
05 SEP 17
AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-33-PLP-TOC P 2/2
05 SEP 17
AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
COCKPIT LIGHTING - GENERAL
GENERAL
Ident.: DSC-33-10-10-00017615.0001001 / 21 MAR 16
Applicable to: ALL
The instrument panel has both integral instrument lighting and flood lighting.
The brightness of all panel lighting is adjustable.
Spot lights and flood lights provide lighting for all work surfaces and the side consoles.
Two dimmable dome lights provide lighting for the overall cockpit. When the batteries are supplying
electrical power, only the right-hand dome light is on line.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-33-10-10 P 1/2
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
COCKPIT LIGHTING - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-33-10-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
COCKPIT LIGHTING - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-33-10-20-00017616.0001001 / 21 MAR 16
Applicable to: ALL
INTEGRATED LIGHTING FOR INSTRUMENTS AND PANELS
All instruments and panels in the cockpit (other than display units) have integral lighting.
The flight crew can adjust the brightness of all integral lighting.
ANNUNCIATOR LIGHTS
The ANN LT sw on the overhead panel controls the brightness of all the annunciator lights in the
cockpit.
The ANN LT sw sets the brightness of all annunciator lights at the same level.
The flight crew can test the annunciator lights with the following procedure: Set the ANN LT sw to
the TEST position, and check to see that all the annunciator lights come on.
DOME LIGHTS
Two dome lights provide the cockpit with shadow-free lighting.
MAP HOLDER LIGHTING
Each flight crewmember has a map holder that can be lighted.
CONSOLE AND BRIEFCASE LIGHTING
Each flight crewmember has lighting for briefcase stowage, the side console, and the floor.
CENTER INSTRUMENT PANEL
Lights under the glareshield provide lighting for the center instrument panel.
STANDBY COMPASS
The standby compass has integral lighting.
READING LIGHTS
Each flight crewmember has a reading light.
PEDESTAL LIGHTING
A flood light in the middle of the overhead panel provides lighting for the center pedestal.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-33-10-20 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
COCKPIT LIGHTING - DESCRIPTION
SCHEMATIC
Ident.: DSC-33-10-20-00001336.0002001 / 05 FEB 14
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
DSC-33-10-20 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
COCKPIT LIGHTING - CONTROLS AND INDICATORS
OVERHEAD PANEL
Ident.: DSC-33-10-30-00017617.0001001 / 21 MAR 16
Applicable to: ALL
(1)
OVHD INTEG LT knob
This knob turns the overhead panel’s integral lighting on and off, and adjusts its brightness.
(2)
ICE IND & STBY COMPASS sw
This switch turns the standby compass light and the external ice detector light on and off.
(3)
DOME sw
The DOME sw controls both dome lights.
The DOME sw can have one of the two following configurations:
or
BRT :
DIM :
OFF :
(4)
Both dome lights are on and bright.
Both dome lights are on and dim.
Both dome lights are off.
ANN LT sw
The ANN LT sw controls all the flight deck annunciator lights.
The ANN LT sw can have one of the two following configurations:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-33-10-30 P 1/6
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
COCKPIT LIGHTING - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
or
TEST :
DIM :
BRT :
Note:
(5)
All flight deck annunciator lights turn On.
The figure '8' is displayed on all Liquid Crystal Display (LCD) of the FCU.
Reduces the brightness of all flight deck annunciator lights.
All flight deck annunciator lights operate normally.
When the ANN LT sw is set to TEST, do not reconfigure the DU (ECAM /ND transfer)
or the DMC (DMC switching).
READING LT knob
The reading light on each side of the overhead panel has its own control knob that turns it on
and off and adjusts its brightness.
MAINTENANCE PANEL
Ident.: DSC-33-10-30-00001338.0001001 / 22 MAY 12
Applicable to: ALL
(1)
AVIONICS COMPT LT pushbutton switch
AUTO : avionic compartment lighting is automatically controlled by door opening.
ON : avionic compartment lighting is on.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B
DSC-33-10-30 P 2/6
24 JAN 17
AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
COCKPIT LIGHTING - CONTROLS AND INDICATORS
LATERAL WINDOW
Ident.: DSC-33-10-30-00001339.0002001 / 05 FEB 14
Applicable to: ALL
(1)
Map light sw (Captain and F/O)
(2)
Brightness adjustment knob
(3)
Light
PEDESTAL
Ident.: DSC-33-10-30-00017619.0001001 / 21 MAR 16
Applicable to: ALL
(1)
FLOOD LT MAIN PNL knob
Turns on or off, and adjusts the brightness of the main instrument panel.
(2)
INTEG LT MAIN PNL & PED knob
Turns on or off, and adjusts the brightness of the integral lights of:
‐ The main instrument panel
‐ The center pedestal.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D →
DSC-33-10-30 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(3)
COCKPIT LIGHTING - CONTROLS AND INDICATORS
FLOOD LT PED knob
Turns on or off, and adjusts the brightness of the pedestal lights.
GLARESHIELD
Ident.: DSC-33-10-30-00001341.0002001 / 21 JAN 14
Applicable to: ALL
(1)
This knob adjusts the brightness of the integral lighting on the glareshield.
(2)
This knob adjusts the brightness of the FCU displays.
(3)
This lighting illuminates the sliding table and map holder.
(4)
This knob adjusts the brightness of the sliding table and map holder lighting.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E
DSC-33-10-30 P 4/6
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
COCKPIT LIGHTING - CONTROLS AND INDICATORS
MAIN INST PANEL
Ident.: DSC-33-10-30-00017620.0001001 / 21 MAR 16
Applicable to: ALL
(1)
CONSOLE/FLOOR sw
Each switch controls the lights of the side console and of the briefcase on each side of the
cockpit. In addition, each switch controls the lighting of the floor around each flight crew
member's seat. The lights can either be bright, dim, or off.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
DSC-33-10-30 P 5/6
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LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
COCKPIT LIGHTING - CONTROLS AND INDICATORS
Intentionally left blank
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
EXTERIOR LIGHTING - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-33-20-10-00017621.0001001 / 21 MAR 16
Applicable to: ALL
Exterior lighting includes the following lights:
‐ The navigation lights
‐ The landing lights
‐ The runway turn off lights
‐ The TO and TAXI lights
‐ The logo lights
‐ The anticollision lights
‐ The wing and engine scan lights.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A
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LIGHTS
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EXTERIOR LIGHTING - GENERAL
FLIGHT CREW
OPERATING MANUAL
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LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTERIOR LIGHTING - CONTROLS AND INDICATORS
SCHEMATIC
Ident.: DSC-33-20-20-00017622.0001001 / 21 MAR 16
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
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LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTERIOR LIGHTING - CONTROLS AND INDICATORS
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTERIOR LIGHTING - CONTROLS AND INDICATORS
OVERHEAD PANEL
Ident.: DSC-33-20-20-00017623.0004001 / 21 MAR 16
Applicable to: ALL
(1)
BEACON sw
This switch turns on and off the two flashing red lights, one on top and one on the bottom of the
fuselage.
(2)
WING sw
This switch turns on and off two beam lights on each side of the fuselage. These lights provide
lighting on the wing leading edge and on the engine air intake to detect ice accretion.
(3)
NAV & LOGO sw
There are single navigation light, or dual navigation lights on each wing and in the APU tail
cone.
A blue light below each navigation light allows to monitor the navigation light wear (LED
technology). When the NAV & LOGO sw is ON, this light flashes in blue if the
navigation light replacement should be planned.
There are logo lights in the upper surface of each horizontal stabilizer. These light provide
lighting for the company logo on the vertical stabilizer provided the main landing gears are
compressed, or depending on the aircraft configuration, when flaps are extended (at least 15 °
on some aircraft) or slats are extended.
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
EXTERIOR LIGHTING - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
The NAV & LOGO sw can have one of the following configuration:
ON
OFF
: Turns on the NAV and the LOGO lights .
: The NAV and the LOGO lights are off.
2
1
OFF
: Turns on NAV 2 and the LOGO lights .
: Turns on NAV 1 and the LOGO lights .
: The NAV and the LOGO lights are off.
or
(4)
NOSE sw
This switch turns the taxi and takeoff lights on and off.
TO
: Turns on both taxi and takeoff lights.
TAXI
: Turns on only taxi light.
OFF
: Taxi and takeoff lights off.
Note:
These two lights, attached to the nose gear strut, go off automatically when landing
gear is retracted.
(5)
L and R LAND sel
These selectors control the landing lights.
ON
: Extends the (left or right) landing lights which come on automatically when
fully extended.
OFF
: Shuts off the landing lights which remain extended.
RETRACT : Shuts off and retracts the landing lights.
(6)
RWY TURN OFF sw
This switch turns the runway turn-off lights on and off.
Note:
(7)
These lights go off automatically when landing gear is retracted.
STROBE sw
This switch turns on and off the three synchronized strobe lights, one on each wing and one
below the tail cone.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTERIOR LIGHTING - CONTROLS AND INDICATORS
A blue light below each strobe light allows to monitor the strobe light wear (LED
technology). When STROBE sw is OFF or BEACON sw is ON, this light flashes in blue if
the strobe light replacement should be planned.
ON
: The strobe lights flash white.
AUTO
: The strobe lights come on automatically when the main landing gear is not
compressed.
OFF
: The strobe lights are off.
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-33-20-20-M-00016785.0001001 / 21 MAR 16
LDG LT
:
The message is displayed in green, if one landing light is extended.
Ident.: DSC-33-20-20-M-00016784.0001001 / 21 MAR 16
STROBE LT OFF :
The message is displayed in green, if the STROBE sw is OFF in flight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTERIOR LIGHTING - CONTROLS AND INDICATORS
Intentionally left blank
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EMERGENCY LIGHTING - DESCRIPTION
GENERAL
Ident.: DSC-33-30-10-00017632.0024001 / 21 MAR 16
Applicable to: ALL
The emergency lighting system consists of the following:
‐ Proximity emergency escape path marking systems (escape path and exit markers)
‐ Overhead emergency lights
‐ EXIT signs
‐ Lavatory auxiliary lights
‐ Overwing escape route lighting
‐ Escape slide lighting.
When in operation:
‐ The proximity emergency escape path marking system is powered by internal batteries for at least
12 min.
‐ The DC SHED ESS BUS supplies the cabin emergency lighting.
‐ If DC SHED ESS BUS fails, batteries inside the light provides power to cabin emergency lighting.
‐ In nominal case, the DC SHED ESS BUS charges these internal batteries if:
•
•
•
•
The EMER LT sw is not at ON
The EMER pb on the Purser’s panel is not pressed
The DC BUS 1 is supplied
Depending on the CIDS/CAM programming, when:
▪ The NO SMOKING sw , or
▪ The NO PORTABLE ELEC DEVICE sw , or
▪ The EXIT sw is set to OFF or AUTO when the landing gear is retracted.
Lavatory auxiliary lights are always on. They are supplied by 28 V DC ESS BUS.
The escape slides have an integral lighting system. The escape slide lights and overwing escape
route lights come on automatically when the slide is armed and the door or emergency exit is
open. They are supplied by internal batteries.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A
DSC-33-30-10 P 1/2
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EMERGENCY LIGHTING - DESCRIPTION
PROXIMITY EMERGENCY ESCAPE PATH MARKING SYSTEM/EXIT SIGNS
Ident.: DSC-33-30-10-00017646.0013001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EMERGENCY LIGHTING - CONTROLS AND INDICATORS
CONTROLS AND INDICATORS
Ident.: DSC-33-30-20-00017708.0027001 / 21 MAR 16
Applicable to: ALL
(1)
EMER EXIT LT sw
The EMER EXIT LT sw can have one of the following configuration:
or
ON :
OFF :
Overhead emergency lights, EXIT signs and proximity marking system come on.
Above lights are off.
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ARM :
EMERGENCY LIGHTING - CONTROLS AND INDICATORS
‐ Exit markers come on when the normal aircraft electrical power or DC SHED ESS
BUS is lost.
‐ The overhead emergency lights come on if:
• Normal aircraft electrical power system fails or
• DC SHED ESS BUS fails or
• AC BUS 1 fails.
‐ Exit signs come on if:
• Normal aircraft electrical power system fails or
• DC SHED ESS BUS fails or
Note:
The LIGHT EMER pb on the Purser's panel can turn on the emergency
lighting regardless of the position of the EMER EXIT LT sw.
(2)
EMER EXIT LT-OFF lt
OFF : The amber EMER EXIT LT-OFF lt comes on when the EMER EXIT LT sw is set to
OFF.
(3)
LIGHT EMER pb
When pressed, this button performs the same function as the EMER EXIT LT sw when it is set
to ON.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
SIGNS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-33-40-10-00017709.0001001 / 21 MAR 16
Applicable to: ALL
The switches described below are installed on the SIGNS panel on the overhead panel.
The cabin signs consist of the following:
• A SEAT BELTS sw, and
• A NO SMOKING sw , or
• An EXIT sw , or
• A NO PORTABLE ELEC DEVICE sw .
The SEAT BELTS sw activates the FASTEN SEAT BELT and RETURN TO YOUR SEAT signs.
The NO SMOKING sw or EXIT sw activate the EXIT and NO SMOKING signs.
The NO PORTABLE ELEC DEVICE sw activates the EXIT and NO MOBILE signs.
A low tone chime sounds (depending on CIDS/CAM programming) each time a sign goes on or off.
Each switch has 3 positions:
ON : Signs are on in the cabin
AUTO : Signs are on in the cabin when either landing gear is extended or flaps/slats are extended
(position 1, 2, 3, or FULL)
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AIRCRAFT SYSTEMS
LIGHTS
A318/A319/A320/A321
SIGNS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OFF : Signs are off in the cabin
Example of switches layout:
Note:
1. If the cabin altitude goes above 11 300 ft (± 350 ft), the cabin lights (depending on
CIDS/CAM programming) and all the cabin signs, except the NO PORTABLE ELEC
DEVICE signs come on regardless of switches position.
2. For NON SMOKER , the NO SMOKING signs are always on.
MEMO DISPLAY
Ident.: DSC-33-40-10-00016783.0001001 / 21 MAR 16
Applicable to: ALL
When the corresponding signs are on, the ECAM displays in green the SEAT BELTS message, the
NO SMOKING message or the NO PED, depending on aircraft customization.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
NAVIGATION
Intentionally left blank
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-34-NAV-10 ADIRS
DSC-34-NAV-10-10 Description
General.....................................................................................................................................................................A
Probes Location....................................................................................................................................................... B
Probes Schematic....................................................................................................................................................C
ADIRS Schematic.................................................................................................................................................... D
DSC-34-NAV-10-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Pedestal................................................................................................................................................................... B
Memo Display.......................................................................................................................................................... C
Maximum Differences Between Speed/Mach Indications....................................................................................... D
DSC-34-NAV-15 GPS
DSC-34-NAV-15-10 Description
Description............................................................................................................................................................... A
DSC-34-NAV-20 Standby Instruments
Compass.................................................................................................................................................................. A
Description of the ISIS............................................................................................................................................ B
Attitude..................................................................................................................................................................... C
Airspeed................................................................................................................................................................... D
Altimeter................................................................................................................................................................... E
Landing System Function........................................................................................................................................ F
Bugs Function..........................................................................................................................................................G
Flags........................................................................................................................................................................ H
DSC-34-NAV-30 Radio Nav
DSC-34-NAV-30-10 Tuning
General.....................................................................................................................................................................A
Architecture.............................................................................................................................................................. B
DSC-34-NAV-30-20 Navaids
VOR..........................................................................................................................................................................A
ILS/GLS /MLS ....................................................................................................................................... B
ADF ...............................................................................................................................................................C
DME......................................................................................................................................................................... D
Marker Beacon.........................................................................................................................................................E
Continued on the following page
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-34-NAV-30-30 Controls and Indicators
Continued from the previous page
Digital Distance and Radio Magnetic Indicator (DDRMI)............................................................................... A
Radio Management Panel (RMP)........................................................................................................................... B
DSC-34-NAV-40 Radio Altimeter
DSC-34-NAV-40-10 Description
General.....................................................................................................................................................................A
Automatic Callout.....................................................................................................................................................B
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
ADIRS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-34-NAV-10-10-00018524.0001001 / 21 MAR 16
Applicable to: ALL
The Air Data and Inertial Reference System (ADIRS ) supplies temperature, anemometric,
barometric and inertial parameters to the EFIS system (PFD and ND ) and to other user systems
(FMGC , FADEC , ELAC , SEC , FAC , FWC , SFCC , ATC , GPWS , CFDIU , CPC).
The system includes:
‐ Three identical ADIRUs (Air Data and Inertial Reference Units).
Each ADIRU is divided in two parts, either of which can work separately in case of failure in the
other:
• The ADR part (Air Data Reference) which supplies barometric altitude, airspeed, Mach, angle of
attack, temperature and overspeed warnings.
• The IR part (Inertial Reference) which supplies attitude, flight path vector, track, heading,
accelerations, angular rates, ground speed and aircraft position.
‐ One ADIRS control panel on the overhead panel for selection of modes (NAV , ATT, OFF) and
indications of failures.
‐ Four types of sensors:
• Pitot probes (3)
• Static pressure probes (STAT) (6)
• Angle of attack sensors (AOA) (3)
• Total air temperature probes (TAT) (2)
These sensors are electrically heated to prevent from icing up.
‐ Eight ADM s (Air Data Modules) which convert pneumatic data from PITOT and STAT probes into
numerical data for the ADIRUs.
‐ A switching facility for selecting ADR 3 or IR 3 for instrument displays in case of ADIRU1 or 2
failure.
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
ADIRS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
PROBES LOCATION
Ident.: DSC-34-NAV-10-10-00018525.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
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B
DSC-34-NAV-10-10 P 2/4
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
ADIRS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
PROBES SCHEMATIC
Ident.: DSC-34-NAV-10-10-00018526.0001001 / 21 MAR 16
Applicable to: ALL
Note:
ADIRU (1) is supplied by CAPT probes,
ADIRU (2) is supplied by F/O probes,
ADIRU (3) is supplied by STBY probes and CAPT TAT.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
ADIRS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
ADIRS SCHEMATIC
Ident.: DSC-34-NAV-10-10-00018527.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
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DSC-34-NAV-10-10 P 4/4
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
ADIRS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-34-NAV-10-20-00018528.0002001 / 21 MAR 16
Applicable to: ALL
(1)
ADR 1(2)(3) pb sw
OFF light
: Air data output disconnected.
FAULT light : This amber light comes on with an ECAM caution if a fault is detected in the
air data reference part.
(2)
IR 1(2)(3) pb sw
OFF light
: Inertial data output disconnected.
FAULT light : This amber light comes on with an ECAM caution when a fault affects the
respective IR.
Steady : the respective IR is lost.
Flashing : the attitude and heading information may be recovered in
ATT mode.
(3)
IR 1(2)(3) mode rotary sel
OFF : The ADIRU is not energized.
ADR and IR data are not available.
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NAV :
ATT :
(4)
ADIRS - CONTROLS AND INDICATORS
Normal mode of operation.
Supplies full inertial data to aircraft systems.
IR mode supplying only attitude and heading information if the system loses its
ability to navigate.
The heading must be entered through the MCDU and has to be reset frequently
(about every 10 min).
ON BAT light
The ON BAT light comes on in amber when the aircraft battery supplies at least one IRS . The
ON BAT light also comes on for a few seconds at the beginning of a complete IRS alignment.
The light does not come on in the case of a fast alignment.
Note:
When the aircraft is on ground and if at least one ADIRU is supplied by aircraft
batteries:
‐ An external horn sounds
‐ The ADIRU and AVNCS light comes on amber on the EXTERNAL POWER panel.
PEDESTAL
Ident.: DSC-34-NAV-10-20-00018529.0001001 / 21 MAR 16
Applicable to: ALL
(1)
ATT HDG and AIR DATA sel
NORM : ADIRU 1 supplies data to PFD 1, ND 1, DDRMI and VOR /DME.
ADIRU 2 supplies data to PFD 2, and ND2.
CAPT 3 : ADR 3 or IR 3 replaces ADR 1 or IR1.
F/O 3 : ADR 3 or IR 3 replaces ADR 2 or IR2.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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DSC-34-NAV-10-20 P 2/4
22 MAR 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
ADIRS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-34-NAV-10-20-A-00017043.0002001 / 21 MAR 16
IR IN ATT ALIGN
:
This memo appears in green during the IR alignment in Attitude mode.
Ident.: DSC-34-NAV-10-20-A-00017041.0002001 / 21 MAR 16
The memo "IRS IN ALIGN X MN" appears during IRS alignment in flight phase 1 or 2. X MN
indicates the number of remaining minutes (1 < X < 10), until NAV mode is reached.
Before any engine is started:
IRS IN ALIGN X MN
: This memo appears in green when at least one active IRS is being
aligned.
IRS IN ALIGN X MN
: This memo pulses in green, if the alignment of one IRS is faulty.
When one engine is started:
IRS IN ALIGN X MN
: This memo appears in amber during IRS alignment. If the alignment
of one IRS is faulty, this memo is replaced by the “IR NOT ALIGNED”
ECAM caution.
MAXIMUM DIFFERENCES BETWEEN SPEED/MACH INDICATIONS
Ident.: DSC-34-NAV-10-20-00021130.0002001 / 17 MAR 17
Applicable to: ALL
FL
SPEED
GND CHECK
FL 50
FL 100
FL 200
FL 300
FL 390
250 kt
250 kt
300 kt
M 0.78
M 0.78
(1)
SPEED/MACH COMPARISON BETWEEN
ADR 3 and ADR 1,
Standby Airspeed Indicator
ADR 1 and ADR 2 (on PFD)
or ADR 3 and ADR2
and any ADR 1, or 2, or 3
Mach on
kt
Mach
kt
Mach
kt
ISIS (1)
6 kt
M 0.008
6 kt
M 0.008
6 kt
4 kt
M 0.005
4 kt
M 0.007
7 kt
4 kt
M 0.005
5 kt
M 0.008
8 kt
M 0.032
3 kt
M 0.007
5 kt
M 0.011
9 kt
M 0.033
3 kt
M 0.010
5 kt
M 0.014
9 kt
M 0.025
3 kt
M 0.010
4 kt
M 0.014
8 kt
M 0.025
Mach values lower than M 0.50 in climb, and M 0.45 in descent, are not displayed on ISIS .
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AIRCRAFT SYSTEMS
NAVIGATION
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ADIRS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
GPS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-34-NAV-15-10-00018530.0001001 / 21 MAR 16
Applicable to: ALL
The Global Positioning System (GPS) is a satellite-based radio navigation aid.
Worldwide, 24 satellites broadcast accurate navigation data that the aircraft use for precise
determination of its position.
The aircraft has two independent GPS receivers. Depending of the aircraft configuration, each
receiver consists:
‐ Of a GPS Sensor Unit (GPSSU), or
‐ Is integrated in the Multi Mode Receiver (MMR ). The GPS 1 receiver in MMR 1, and the GPS 2
receiver in MMR2.
The GPSSU or the MMR processes the received data, and transfers them to the ADIRU s. Then
each ADIRU performs the GP-IRS hybrid position calculation. FMGCs use this hybrid position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
GPS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
GPS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
OPERATIONS
GPS information are available on the FMS – GPS Monitor Page. Refer to DSC-22_20-50-10
Pages descriptions.
• During normal operations
The GPS receiver 1 supplies the ADIRU 1 and the ADIRU 3, and the GPS receiver 2 supplies
the ADIRU 2.
• In case of failure of one GPS receiver
All ADIRU s use the operative GPS receiver.
• In case of failure of ADIRUs
‐ If the ADIRU 1 fails, ADIRU 3 is supplied by the GPS receiver 1, and ADIRU 2 is supplied by
the GPS receiver 2.
‐ If the ADIRU 2 fails, the ATT HDG selector has to be set to F/O 3 in order to maintain Side 1
and Side 2 segregation. In this case, the ADIRU 3 will be supplied with GPS receiver 2.
‐ If two ADIRU s fail, the remaining ADIRU is supplied by its own side GPS receiver.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
GPS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
STANDBY INSTRUMENTS
FLIGHT CREW
OPERATING MANUAL
COMPASS
Ident.: DSC-34-NAV-20-00001367.0001001 / 19 DEC 12
Applicable to: ALL
There is a compass located on top of the windshield center post.
The deviation card is located above the compass.
Note:
Because of the location of the APU power on contactor in the cockpit, the APU start
sequence may disturb the compass reading.
DESCRIPTION OF THE ISIS
Ident.: DSC-34-NAV-20-00018543.0002001 / 21 MAR 16
Applicable to: ALL
GENERAL
The ISIS system displays the following information:
‐ Attitude
‐ Airspeed and mach
‐ Altitude
‐ Barometric pressure
‐ LS function
‐ Bugs
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-34-NAV-20 P 1/10
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(1)
STANDBY INSTRUMENTS
”+”/ “-” activation pushbuttons
Two pushbuttons labelled “+” and “–” are used to adjust the level of brightness.
The brightness of the screen automatically adjusts after power-up tests.
This is because of the photosensitive cell located on the surface of the ISIS system display.
The “+” and “–” pushbuttons then allow this initial brightness to be manually adjusted and
changed.
Note:
The system must be reset after 350 h of continuous electrical supply using the «
ATT RST » pushbutton.
ARCHITECTURE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-34-NAV-20 P 2/10
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDBY INSTRUMENTS
ATTITUDE
Ident.: DSC-34-NAV-20-00018575.0002001 / 21 MAR 16
Applicable to: ALL
Note:
When leveling the wings after performing a small turn of a small bank angle, the displayed
roll attitude may temporarily be incorrect by a few degrees.
(1)
Fixed aircraft symbol
The fixed aircraft symbol is in black, and outlined in yellow.
Depending of the aircraft configuration, the center of the fixed aircraft symbol is a point (like on
the illustration above) or “V-bars”.
(2)
Roll scale
The roll scale is in white.
The markers are at 0 (small yellow triangle), 10, 20, 30, 45, 60 ° of bank.
(3)
Roll index
The roll index is in black, and outlined in white. It indicates the bank angle.
(4)
Lateral acceleration index
The trapezoidal index moves beneath the roll index. It represents the aircraft’s lateral
acceleration.
(5)
Pitch scale
The pitch scale is in white. The scale shows markers every 2.5 ° between 30 ° nose up and
30 ° nose down. Beyond 30 °, large red arrowheads (V-shaped) indicate that the attitude has
become excessive, and show the direction to follow in order to reduce it. The minimum pitch
scale displayed is -17.5 ° +15 ° at 0 ° pitch.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-34-NAV-20 P 3/10
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(6)
STANDBY INSTRUMENTS
ATT RST
The attitude indication can be reset by pressing this pushbutton for at least 2 s. The aircraft
must be level during this procedure. During the reset time (approximately 10 s), the “ATT 10 s”
message is displayed on the screen. This pushbutton is also used to realign the system, if
excessive aircraft movement is detected during the alignment phase.
AIRSPEED
Ident.: DSC-34-NAV-20-00018576.0002001 / 21 MAR 16
Applicable to: ALL
(1)
Airspeed scale
A white scale moves in front of a yellow triangle indicating the airspeed. The scale ranges from
5 to 250 kt, with a mark every 5 kt, and from 250 to 520 kt, with a mark every 10 kt.
(2)
Mach Number
The Mach number is displayed in green it goes greater than 0.5. And it disappears only when it
goes below 0.45.
(3)
Speed bug
When a speed bug is entered via the BUGS function, the corresponding speed mark is
indicated by a cyan dash.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-34-NAV-20 P 4/10
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDBY INSTRUMENTS
ALTIMETER
Ident.: DSC-34-NAV-20-00018577.0002001 / 21 MAR 16
Applicable to: ALL
(1)
Altitude indication
The altitude indication is given as a white moving scale, and a green digital readout on a gray
background.
The altitude scale ranges from -2 000 to 50 000 ft every 100 ft, with altitude digital indications
every 500 ft.
For negative altitudes, "NEG" appears in the window in white.
The altitude box changes to cyan, when it also corresponds to a bug value.
Depending of the aircraft configuration, the altitude in meters is displayed above the altitude
scale.
(2)
Barometric reference
The barometric reference pressure is displayed in cyan.
The displayed barometric reference is:
‐ The standard barometric reference "STD", or
‐ Depending of the aircraft configuration, the barometric pressure is "hPa" or "hPa/ inHg".
(3)
Barometric selection knob
This knob enables the selection of a barometric pressure, setting a variation of 10 hPa per
knob rotation.
The standard barometric pressure can be selected by pressing the barometric knob. “STD” is
then displayed, in place of the pressure value.
Pressing the knob again will display the selected barometric pressure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
STANDBY INSTRUMENTS
FLIGHT CREW
OPERATING MANUAL
(4)
Altitude bug
When an altitude bug is entered through the bugs function, the corresponding altitude mark is
indicated by a cyan dash, or by a cyan box when the dash covers the digital indication on the
scale.
LANDING SYSTEM FUNCTION
Ident.: DSC-34-NAV-20-00001377.0005001 / 22 JUL 14
Applicable to: ALL
(1)
Localizer / scale and index
(2)
Glideslope / scale and index
When the LS pb is pressed, the deviation scales are displayed.
When deviation scales are displayed and the LS deviations are valid, the indexes appear.
The LS deviations that are displayed correspond to the LS approach:
‐ Selected on the MCDU, or
‐ Tuned on the RMP.
Note:
(3)
The LS approach corresponds to either ILS approach, or MLS approach, or GLS
approach, or non precision approach using FLS .
LS selection pushbutton
Pressing the LS pb will display the LS scales. Pressing the LS pb again will remove the LS
scales.
CAUTION
Do not use the ISIS LS for takeoff using the localizer of the opposite runway,
or for a back-course localizer approach. The LOC deviations are given in the
wrong sense.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F
DSC-34-NAV-20 P 6/10
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
STANDBY INSTRUMENTS
FLIGHT CREW
OPERATING MANUAL
BUGS FUNCTION
Ident.: DSC-34-NAV-20-00018578.0001001 / 21 MAR 16
Applicable to: ALL
(1)
BUGS function selection pushbutton
Pressing the BUGS pushbutton will activate the BUGS function and display the bug values to
be selected.
(2)
SPD BUG and ALT BUG columns
The SPD BUG column gives four speed values (in knots) that can be selected by the crew.
The ALT BUG column gives two altitude values (feet) to be selected by the crew.
(3)
BUGS value selection knob
It allows the bug value to be set by rotating the BARO knob. This value cannot be lower than
30 kt for a speed bug, or a negative value for an altitude bug.
Pressing the BARO setting knob, once a bug value box is activated, will deselect the bug value.
The “OFF” label comes on close to the activated box.
The entered values are memorized by the system, when exiting the screen, by pressing the
BUGS pushbutton (1), or after 15 s without any pilot action.
(4)
“+”/”-” box activation buttons
Access from one box to another is obtained by pressing the “+” or “–” pushbutton.
When a bug value is entered, access to the next box is obtained by pressing the “–”
pushbutton. The box becomes active and flashes.
The “+” pushbutton can be used to return to a previous box.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G→
DSC-34-NAV-20 P 7/10
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
STANDBY INSTRUMENTS
Use of the ISIS bugs function is not recommended because, in the event that both
PFDs are lost in flight, when the ISIS bugs were previously set for takeoff, then for the
approach, the bugs would remain at the takeoff characteristic speed settings.
FLAGS
Ident.: DSC-34-NAV-20-00018580.0002001 / 21 MAR 16
Applicable to: ALL
(1)
ATT flag (red)
When attitude data is lost, the red ATT flag appears.
(2)
SPD flag (red)
When airspeed data is lost, the red SPD flag appears.
(3)
M flag (red)
When mach number is lost, the red M flag appears.
(4)
ALT flag (red)
When altitude data is lost, the red ALT flag appears.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-34-NAV-20 P 8/10
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDBY INSTRUMENTS
(5)
G/S flag (red)
When glideslope information is lost, the red G/S flag appears.
(6)
LOC flag (red)
When localizer data is lost, the red LOC flag appears.
(7)
ATT: RST (yellow)
The “ATT: RST” flag appears:
‐ When excessive aircraft movement is detected during the alignment phase, or
‐ After 350 h of continuous electrical supply, or
‐ When the “WAIT ATT” flag is displayed during more than 10 s.
In both cases, press the ATT RST pb to reset/realign and recover the attitude indication.
(8)
MAINT flag (white)
Maintenance required. This “MAINT flag” does not affect ISIS operation.
Displayed only on ground phase (speed < 60 kt).
(9)
OUT OF ORDER (white)
When an internal failure of the ISIS indicator occurs, the “OUT OF ORDER” message appears,
accompanied by a fault code.
(10) WAIT ATT flag (yellow)
If the ISIS looses attitude data, its entire sphere is cleared to display the: “WAIT ATT” flag.
‐ If the “WAIT ATT” flag is displayed during less than 10 s, a normal operation is recovered.
‐ If attitude data are lost for more than 10 s, the “WAIT ATT ” flag is then replaced by the
“ATT: RST” flag.
(11) ATT 10 s flag (yellow)
This count down flag appears, when the flight crew press the ATT RST pb, in order to indicate
that the attitude reset function is in progress.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
STANDBY INSTRUMENTS
FLIGHT CREW
OPERATING MANUAL
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FCOM
DSC-34-NAV-20 P 10/10
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
RADIO NAV - TUNING
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-34-NAV-30-10-00018581.0001001 / 21 MAR 16
Applicable to: ALL
Three modes of tuning are available.
1. Automatic Tuning
This is the basic means for tuning navaids.
In normal operation, the FMGC tunes navaids automatically, with each FMGC controlling its own
receivers.
If one FMGC fails, the remaining FMGC controls both sides receivers.
2. Manual Tuning
The flight crew can use the MCDU to override the automatic tuning of navaids by FMGC in order
to select a specific navaid for visual display.
This does not affect the automatic function of the FMGC.
Any entry on one MCDU is sent to both FMGC in dual mode, or the remaining FMGC in single
mode.
3. Back Up Tuning
If both FMGC s fail, the flight crew can use the RMPs (Radio Management Panels 1 and 2) on the
pedestal for back up tuning.
The CAPT RMP controls VOR1 and ADF 1 .
The F/O RMP controls VOR2 and ADF 2 .
Either RMP controls ILS /GLS / MLS , provided “STBY NAV” is selected on RMP 1 and
RMP2. RMP3 is not used for navaids tuning.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
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AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
RADIO NAV - TUNING
FLIGHT CREW
OPERATING MANUAL
ARCHITECTURE
Ident.: DSC-34-NAV-30-10-00018582.0001001 / 21 MAR 16
Applicable to: ALL
NORMAL OPERATION
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-34-NAV-30-10 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
RADIO NAV - TUNING
FLIGHT CREW
OPERATING MANUAL
FMGC 1 FAILURE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-34-NAV-30-10 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
RADIO NAV - TUNING
FLIGHT CREW
OPERATING MANUAL
BACK UP TUNING
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
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24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
RADIO NAV - NAVAIDS
FLIGHT CREW
OPERATING MANUAL
VOR
Ident.: DSC-34-NAV-30-20-00018657.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft has two VOR receivers.
‐ The Navigation Displays (ND s) display VOR 1 and VOR 2 information, in accordance with the
position of the ADF /VOR selectors on the EFIS control panel (Refer to DSC-31-45 ROSE
Modes).
‐ The DDRMI also displays VOR 1 and VOR2 bearings, if the heading signal is valid.
ILS/GLS /MLS
Ident.: DSC-34-NAV-30-20-00018658.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft has two ILS /GLS /MLS receivers.
Note:
When the aircraft is equipped with MMR s, ILS and GLS and MLS receivers are in
the MMR s (ILS 1/GLS1 /MLS1 in the MMR 1 and the ILS 2/GLS2 /MLS2
in the MMR2)
‐ PFD 1 and ND 2 display ILS1/GLS1 /MLS1 information.
‐ PFD 2 and ND 1 display ILS2/GLS2 /MLS2 information.
‐ The PFD display the ILS /GLS /MLS information if the flight crew press the LS pb or ILS
pb (depending of the aircraft configuration) on the EFIS control panel (Refer to DSC-31-50 EFIS
Control Panel).
‐ The ND s display the ILS /GLS /MLS information if the flight crew selects the ROSE LS
mode or the ROSE ILS mode (depending of the aircraft configuration) on the EFIS control panel
(Refer to DSC-31-50 EFIS Control Panel).
ADF
Ident.: DSC-34-NAV-30-20-00018659.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft may be fitted with 1 ADF or 2 ADF .
The ND s display ADF information, depending on the position of the ADF /VOR selectors on the
EFIS control panel (Refer to DSC-31-45 ROSE Modes).
The DDRMI also displays ADF 1 and ADF 2 bearings, depending on the position of the
ADF /VOR selector on the DDRMI .
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C
DSC-34-NAV-30-20 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
RADIO NAV - NAVAIDS
FLIGHT CREW
OPERATING MANUAL
DME
Ident.: DSC-34-NAV-30-20-00018660.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft has two DMEs.
The frequency that is automatically set on the DME corresponds to the frequency/channel that is set
on the VOR , or ILS, or GLS , or MLS .
The ND s and the DDRMI can display DME information associated with VOR.
The PFD s can display DME information associated with ILS/GLS /MLS (Refer to
DSC-31-40 Trajectory Deviation - ILS Approach).
MARKER BEACON
Ident.: DSC-34-NAV-30-20-00001389.0001001 / 21 MAR 16
Applicable to: ALL
One marker beacon system is included in VOR receiver 1.
The PFD displays the outer, middle, and inner marker signals (Refer to DSC-31-40 Trajectory
Deviation - ILS Approach).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D to E
DSC-34-NAV-30-20 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RADIO NAV - CONTROLS AND INDICATORS
DIGITAL DISTANCE AND RADIO MAGNETIC INDICATOR (DDRMI)
Ident.: DSC-34-NAV-30-30-00018583.0001001 / 21 MAR 16
Applicable to: ALL
(1)
Compass card
ADIRU1 normally supplies the signal that positions the compass card.
ADIRU 3 supplies this signal when selected by the ATT HDG SWITCHING selector.
(2)
Bearings pointers
Indicate the magnetic bearing to the station received by VOR 1 or ADF 1 (dashed pointer)
and VOR2 or ADF 2 (double pointer).
Note:
(3)
Depending on the quality of the VOR beacon's signal, and mainly at distances greater
than 25 NM from the station, the processing of the signal, on aircraft equipped with
COLLINS or BENDIX VOR may lead to bearing pointer oscillations.
DME1(2) counters
Indicates distance in nautical miles to/from DME station.
The counters indicate distances:
‐ in NM when the station is at more than 20 NM
‐ 1/10th of NM when the station is at less than 20 NM.
When the station is at less than 1 NM, 0 is shown.
The DME 1 and DME2 display are blanked or dashed when a fault is detected or data invalid.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
RADIO NAV - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(4)
VOR/ADF selector
‐ VOR1 or ADF 1 on the dashed pointer.
‐ VOR 2 or ADF 2 on the double pointer (if ADF 2 is not installed, then ADF1 may be
selected).
The DDRMI has also VOR /ADF flags and HDG flags when the associated information is not
available.
The indicators display these flags if:
‐ The VOR or ADF receiver fails (associated to the VOR /ADF flag only)
‐ The DDRMI has an internal failure
‐ The heading signal from ADIRS is not valid
‐ The power supply fails.
As long as the VOR /ADF flag is shown, and depending of the aircraft configuration, the associated
bearing pointer remains:
‐ At the last valid position, or
‐ Into the horizontal line.
RADIO MANAGEMENT PANEL (RMP)
Ident.: DSC-34-NAV-30-30-00018584.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-34-NAV-30-30 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RADIO NAV - CONTROLS AND INDICATORS
(1)
ON/OFF sw
This switch controls the power supply to the panel.
(2)
NAV key (transparent switchguard)
‐ Pressing this key engages the radio navigation backup mode. It takes control of the VOR ,
ILS , GLS , MLS and ADF receivers away from the FMGC and gives it to the
RMP.
‐ The green monitor light comes on.
‐ Pressing the NAV key a second time returns control of the navigation radios to the FMGC.
Note:
‐ The flight crew must select this backup tuning mode on both RMP 1 and RMP 2
if both FMGC s or both MCDU s fail. In the emergency electrical configuration,
only RMP1 receives power
‐ Pressing the NAV key on RMP3 has no effect
‐ In the NAV backup mode, the flight crew can select radio communication
systems as it would in the normal mode.
Setting one RMP to NAV backup mode removes navaids tuning from both
FMGCs.
‐ When the flight crew uses an RMP to tune an ILS /DME or GLS /DME or
MLS /DME , the PFD s do not display the DME distance.
(3)
STBY NAV keys
When the NAV key is on and the flight crew presses one of these STBY NAV keys, the ACTIVE
window displays the frequency/channel to which that receiver is tuned. The green monitor light
on the selected key comes on, and the one on the previously selected STBY NAV or COM key
goes out.
(4)
Frequency/channel selector knob
Two concentric knobs allow the flight crew to preselect frequencies/channels for
communication radios and stand-by navigation systems and select courses for VOR , ILS ,
GLS and MLS .
The desired frequency, channel or course is set in the STBY/CRS window.
The outer and the inner knobs set a frequency/channel: the outer knob controls the most
significant digits, the inner knob controls the least significant digits. A rate multiplier speeds up
the tuning when the knob is rotated quickly.
The inner knob only sets a course.
(5)
Transfer key
The flight crew presses this key to interchange ACTIVE and STBY frequencies/channels. This
action tunes the selected receiver to the new ACTIVE frequency/channel.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-34-NAV-30-30 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(6)
RADIO NAV - CONTROLS AND INDICATORS
STBY /CRS window
The flight crew can make the displayed frequency /channel by rotating the tuning knob.
The frequency/channel displayed in the window becomes the active frequency/channel when
the flight crew presses the Transfer Key.
If this window displays a course, then the ACTIVE window displays the associated
frequency/channel.
Note:
If the STBY /CRS window is displaying a course, then pressing the transfer key
displays the active frequency/channel in both windows.
(7)
ACTIVE window
This window displays the frequency/channel of the selected navaid, which is identified by a
green monitor light on the selection key.
(8)
LOAD FUNCTION
The flight crew can load the VHF frequency from the CPDLC CONTACT/MONITOR messages
to the STBY/CRS window.
(9)
BFO key
If the ADF is selected, rressing this key activates the BFO (Beat Frequency Oscillator).
For most ADF , with BFO activated, the audio identification is heard. However there are some
ADF where the BFO must be deactivated in order to hear the audio identification.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-34-NAV-30-30 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
RADIO ALTIMETER - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-34-NAV-40-10-00018585.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft has two radio altimeters (RA).
CAPT PFD displays the RA 1 height, and the F/Os PFD displays the RA2 height.
If one RA fails, both PFD s display the height from the remaining RA.
For indication on the PFD, Refer to DSC-31-40 Altitude (CONT'D).
AUTOMATIC CALLOUT
Ident.: DSC-34-NAV-40-10-00018656.0001001 / 21 MAR 16
Applicable to: ALL
GENERAL
The FWC generates a synthetic voice for radio height announcement below 2 500 ft. These
announcements come through the cockpit loudspeakers, even if the speakers are turned off.
PREDETERMINED CALL OUT
The altitude call out uses the following predetermined threshold:
Height (feet)
Call out
TWO THOUSAND FIVE HUNDRED
OR TWENTY FIVE HUNDRED
TWO THOUSAND
ONE THOUSAND
FIVE HUNDRED
FOUR HUNDRED
THREE HUNDRED
TWO HUNDRED
STANDBY (1)
ONE HUNDRED
STANDBY (1)
FLARE (1)
FIFTY
FORTY
THIRTY
TWENTY
TEN
FIVE
HUNDRED ABOVE
MINIMUM
2 500
2 000
1 000
500
400
300
200
115
100
90
65
50
40
30
20
10
5
DH (or MDA /MDH) + 100
DH (or MDA /MDH)
(1)
These callouts are triggered only if the Steep Approach and Landing function is active. In this
case, the “ONE HUNDRED” callout is inhibited.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-34-NAV-40-10 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
NAVIGATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
RADIO ALTIMETER - DESCRIPTION
The reference altitude for callouts is the radio height for precision approaches (DH ), and
baro altitude (MDA /MDH) for non precision approaches.
Pin programming enables Operators to select the required callouts. If the aircraft remains at a
height that is in the detection zone for a height callout, the corresponding message is repeated at
regular intervals.
INTERMEDIATE CALL OUT
If time between two consecutive predetermined call outs exceeds a certain threshold, the present
height is repeated at regular intervals.
The threshold is:
‐ 11 s above 50 ft
‐ 4 s below 50 ft
The repeating interval is 4 s.
RETARD ANNOUNCEMENT
The loudspeaker announces RETARD at:
‐ 20 ft, or
‐ at 10 ft if autothrust is active and one autopilot is in LAND mode.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
SURVEILLANCE
Intentionally left blank
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-34-SURV-10 ATC
DSC-34-SURV-10-10 Description
Principle....................................................................................................................................................................A
DSC-34-SURV-10-20 Controls and Indicators
Control Panels......................................................................................................................................................... A
DSC-34-SURV-30 Weather Radar
DSC-34-SURV-30-10 Description
Description............................................................................................................................................................... A
DSC-34-SURV-30-20 Predictive Windshear System
General.....................................................................................................................................................................A
Windshear Alerts During Takeoff Roll, Up to 100 knots......................................................................................... B
Windshear Alerts Above 50 feet............................................................................................................................. C
Windshear Alerts Inhibition......................................................................................................................................D
DSC-34-SURV-30-30 Controls and Indicators
Control Panel........................................................................................................................................................... A
Weather Radar indication on ND............................................................................................................................ B
PWS indication on PFD and ND .................................................................................................................. C
Memo Display.......................................................................................................................................................... D
DSC-34-SURV-40 GPWS
DSC-34-SURV-40-10 Description
Overview.................................................................................................................................................................. A
Principle....................................................................................................................................................................B
DSC-34-SURV-40-20 GPWS Basics Modes
Mode 1 : Excessive Rate of Descent..................................................................................................................... A
Mode 2 : Excessive Terrain Closure Rate.............................................................................................................. B
Mode 3 : Altitude Loss After Takeoff...................................................................................................................... C
Mode 4 : Unsafe Terrain Clearance when Not in Landing Configuration............................................................... D
Mode 5 : Descent Below Glideslope.......................................................................................................................E
DSC-34-SURV-40-35 Predictive GPWS Functions
Terrain Awareness and Display.............................................................................................................................. A
Terrain Caution and Warning Envelope.................................................................................................................. B
Terrain Clearance Floor.......................................................................................................................................... C
Runway Field Clearance Floor................................................................................................................................D
Continued on the following page
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AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-34-SURV-40-40 Controls and Indicators
Continued from the previous page
Overhead Panel....................................................................................................................................................... A
Instrument Panels.................................................................................................................................................... B
Memo Display.......................................................................................................................................................... C
DSC-34-SURV-60 TCAS
DSC-34-SURV-60-10 Description
Overview.................................................................................................................................................................. A
Principle....................................................................................................................................................................B
Main Components....................................................................................................................................................C
Intruder Detection Categories................................................................................................................................. D
TCAS Modes............................................................................................................................................................E
Advisory Inhibition.................................................................................................................................................... F
DSC-34-SURV-60-20 Controls and Indicators
ATC/TCAS Panel..................................................................................................................................................... A
ND Indications..........................................................................................................................................................B
TCAS Messages......................................................................................................................................................C
PFD Indications....................................................................................................................................................... D
Aural Messages....................................................................................................................................................... E
Memo Display.......................................................................................................................................................... F
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-34-SURV-PLP-TOC P 2/2
05 SEP 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
ATC - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
PRINCIPLE
Ident.: DSC-34-SURV-10-10-00020602.0002001 / 17 MAR 17
Applicable to: ALL
The aircraft has two ATC transponders (XPDR) which are controlled by a control panel (ATC /TCAS)
on the center pedestal.
Only the selected XPDR operates.
The XPDR automatically responds to requests:
‐ From the ATC, to ensure effective air traffic surveillance
‐ From other aircraft that have a TCAS, to ensure that traffic alerts are triggered.
The XPDR is capable of elementary surveillance (ELS) and enhanced surveillance (EHS). It
transmits the following data to the ATC center:
‐ The aircraft 24 bit address, the aircraft altitude, the flight number, the RA report
‐ The indicated airspeed, the Mach number, and the barometric vertical speed that are all supplied
by the ADRs
‐ The magnetic heading, the roll angle, the ground speed, the track angle, the track angle rate, and
the inertial vertical speed, that are all supplied by the IRs
‐ The selected altitude and barometric reference settings supplied by the FCUs.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-34-SURV-10-10 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
ATC - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-34-SURV-10-10 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
ATC - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
CONTROL PANELS
Ident.: DSC-34-SURV-10-20-00020607.0012001 / 17 MAR 17
Applicable to: ALL
(1)
XPDR Selector
Selects XPDR 1 or 2.
(2)
IDENT Switch
The flight crew presses this button to send the aircraft identification signal.
(3)
Keypad
The flight crew uses these key to set the code assigned by ATC.
(4)
Code Display
The window displays the selected code.
(5)
ATC FAIL Light
This light comes on if the selected XPDR fails.
(6)
Mode Selector
STBY
:
ALT RPTG :
OFF
Both XPDR and TCAS are electrically-supplied, but are on standby.
No altitude data is transmitted.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-34-SURV-10-20 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(7)
XPNDR
:
XPNDR
:
TA-RA/TA
:
ATC - CONTROLS AND INDICATORS
In flight : Selected XPDR operates in all modes.
Baro altitude data is transmitted.
ATC 1 uses ADR 1 or ADR 3. ATC 2 uses ADR 2 or ADR 3.
The TCAS is on standby.
On ground : Selected XPDR only operates in mode S (Selective aircraft
interrogation mode).
Refer to DSC-34-SURV-60-20 ATC/TCAS Panel.
CLR Key
The flight crew uses this key to clear the code display.
Note:
As long as the four figures of the new code are not entirely written, the previous code
remains.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-34-SURV-10-20 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
WEATHER RADAR - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-34-SURV-30-10-00014867.0002001 / 22 MAR 17
Applicable to: ALL
The aircraft is fitted with one or two Multiscan weather radar systems with a Predictive
WindShear (PWS ) function and a weather hazard prediction function .
The flight crew can display weather data on the CAPT and/or F/O NDs in either ARC or ROSE mode.
The flight crew can adjust the brightness of the weather image on the ND thanks the outer knob of
the ND Brightness Control knob (Refer to DSC-31-50 Other EFIS Controls).
Note:
A low brightness setting of the weather display may reduce the visibility of weather data,
and therefore reduce crew awareness of the weather situation.
The flight crew can use the radar in the following modes:
‐ Multiscan Automatic mode: MULTISCAN sw set to AUTO (recommended), or
‐ Manual mode: MULTISCAN sw set to MAN.
When in Multiscan Automatic mode:
‐ The radar alternatively scans at two antenna tilt settings. The weather radar image that is
displayed is the result of the stored and combined information from each beam.
‐ When the gain selector is set to the Calibrated position (CAL), the radar automatically adjusts the
gain based on various parameters (aircraft altitude, geographical area, season, time of the day) to
obtain the best weather display.
‐ To prevent unnecessary clutter display, the “Quiet and Dark cockpit” philosophy removes the
weather that:
‐ is not on the aircraft flight path
‐ is not a threat to the aircraft (post convective cell).
‐ The Ground Clutter Suppression (GCS ) function removes the ground returns from the ND.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-34-SURV-30-10 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
WEATHER RADAR - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Multiscan Principle
When in Manual mode:
‐ The flight crew can adjust manually the antenna tilt settings, and can adjust gain either
automatically or manually using knobs located on the radar control panel
‐ The GCS function is not available
‐ When the gain selector is set to CAL, there is no automatic gain adjustment based on altitude,
geographical area, season and time of the day.
As a consequence, when the flight crew switches from the Multiscan Automatic mode with CAL gain
to the Manual mode with CAL gain, the weather displayed on the ND may be significantly different.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-34-SURV-30-10 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEATHER RADAR - PREDICTIVE WINDSHEAR SYSTEM
GENERAL
Ident.: DSC-34-SURV-30-20-00020942.0004001 / 17 MAR 17
Applicable to: ALL
The weather radar has a Predictive WindShear system (PWS ) that operates when the PWS switch
is in the AUTO position , and the aircraft radio height is below 2 300 ft, and
‐ Weather radar is ON (Radar sw on position 1 or 2), or
‐ Weather radar is OFF, and
‐ At least one engine is running, and
‐ Aircraft ground speed is greater than 30 kt, or
‐ Aircraft longitudinal acceleration is above a given threshold during at least 0.5 s.
Note:
If two weather radars are installed, when the selected weather radar fails, the flight crew
can recover the PWS function by selecting the operative system on the Radar sw of the
radar control panel.
The system scans the airspace for windshear within a range of 5 NM ahead of the aircraft. When the
system detects windshear, a windshear symbol appears on the ND (Refer to DSC-34-SURV-30-30
PWS (if installed) indication on PFD and ND).
Predictive windshear warnings and cautions are associated to an aural alert and to a red (warning)
or amber (caution) "W/S AHEAD" message on the PFD , whereas windshear advisories are only
displayed on the ND (Refer to DSC-34-SURV-30-30 PWS (if installed) indication on PFD and ND )
without message on the PFD.
Alert Level
Warning (Approach)
Warning (Takeoff)
Caution
Advisory
Aural Warning
«GO AROUND
WINDSHEAR AHEAD»
«WINDSHEAR
AHEAD» (twice)
«MONITOR
RADAR DISPLAY»
Nil
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PFD
ND (Refer to
DSC-34-SURV-30-30
PWS (if installed)
indication on PFD and ND)
W/S AHEAD (red)
Windshear icon
W/S AHEAD (red)
Windshear icon
W/S AHEAD (amber)
Windshear icon
Nil
Windshear icon
DSC-34-SURV-30-20 P 1/4
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEATHER RADAR - PREDICTIVE WINDSHEAR SYSTEM
WINDSHEAR ALERTS DURING TAKEOFF ROLL, UP TO 100 KNOTS
Ident.: DSC-34-SURV-30-20-00020944.0001001 / 17 MAR 17
Applicable to: ALL
Windshear Alerts During Takeoff Roll, Up to 100 knots
During the takeoff roll, up to 100 kt, both warnings and cautions are available within a range of 3 NM.
Note:
This is also applicable during taxi when weather radar is set to ON.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
DSC-34-SURV-30-20 P 2/4
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEATHER RADAR - PREDICTIVE WINDSHEAR SYSTEM
WINDSHEAR ALERTS ABOVE 50 FEET
Ident.: DSC-34-SURV-30-20-00006422.0001001 / 12 APR 16
Applicable to: ALL
Windshear Alerts Above 50 feet
During final approach, the visual and aural warning alerts are downgraded to caution alerts between
370 ft AGL and 50 ft AGL, and range between 1.5 NM and 0.5 NM.
WINDSHEAR ALERTS INHIBITION
Ident.: DSC-34-SURV-30-20-00006426.0002001 / 20 JUL 15
Applicable to: ALL
At takeoff, alerts are inhibited above 100 kt and up to 50 ft.
During landing, alerts are inhibited below 50 ft.
The aural alerts of the Predictive WindShear system (PWS):
‐ Have priority over TCAS , GPWS , and other FWC aural warnings
‐ Are inhibited by reactive windshear detection and aural messages of stall warnings.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D
DSC-34-SURV-30-20 P 3/4
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEATHER RADAR - PREDICTIVE WINDSHEAR SYSTEM
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-34-SURV-30-20 P 4/4
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEATHER RADAR - CONTROLS AND INDICATORS
CONTROL PANEL
Ident.: DSC-34-SURV-30-30-00001402.0002001 / 21 MAR 17
Applicable to: ALL
(1)
(2)
Radar sw
This switch sets one radar to ON or turns both radars to OFF.
Note:
If only one radar is installed on the aircraft, either:
‐ a "INOP" or "DEACT" sticker replaces the "2", or
‐ a "ON/OFF" Radar sw replaces the "1/OFF/2" Radar sw.
Note:
If only one radar is installed on the aircraft, no weather image is displayed on the
Navigation Display (ND) when the "1/OFF/2" SYS sw is set to "2".
GAIN knob
This knob adjusts the sensitivity of the radar.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-34-SURV-30-30 P 1/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEATHER RADAR - CONTROLS AND INDICATORS
CAL is the normal position of the knob :
‐ When in Multiscan Automatic mode and gain set to CAL, the radar automatically adjusts the
gain according to various parameters (aircraft altitude, geographical area, season, time of
the day) to obtain the best weather display
‐ When in Manual mode and gain set to CAL, the radar adjusts the gain to a calibrated setting.
(3)
Display mode selector
WX
: Weather mode :
Colors indicate the intensity of precipitation (black for the lowest intensity,
green, amber and red indicate progressively higher intensity).
WX+T
: Weather and Turbulence mode :
The ND indicates precipitation and turbulence areas. Turbulence areas are
displayed in magenta (within 40 NM).
TURB : Turbulence mode :
The ND only displays turbulence areas in magenta (within 40 NM).
WX+T+HZD : Weather, Turbulence and Hazard mode (recommended position) :
The ND indicates precipitation, turbulence areas in magenta (within 40 NM)
and hazard prediction risk areas (Refer to DSC-34-SURV-30-30 Weather
Hazard Prediction Function Indication on ND).
Hazard prediction function is only available when the MULTISCAN sw is set to
AUTO.
Note:
MAP
:
When MULTISCAN sw is set to MAN, WX+T+HZD mode is
equivalent to WX+T mode.
Map mode :
The radar operates in ground mapping mode: black indicates water, green
indicates the ground, and amber indicates cities and mountains.
(4)
TILT knob
This knob adjusts the antenna tilt when MULTISCAN sw is set to MAN.
Zero indicates the horizon reference provided by the IRS.
(5)
MULTISCAN sw
AUTO : Activates Multiscan mode
Multiscan controls the tilt automatically and combines two scans done at different
tilt angles to optimize weather detection and minimize ground clutter.
MAN : When set to MAN, the crew can manually adjust the tilt by using the TILT knob.
(6)
GCS sw
The Ground Clutter Suppression (GCS) switch is spring-loaded to the AUTO position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-34-SURV-30-30 P 2/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
WEATHER RADAR - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
AUTO :
OFF
(7)
:
‐ If MULTISCAN sw is set to AUTO, the radar is in normal use. Ground clutter is
not displayed on the screen
‐ If MUTLISCAN sw is set to MAN, the GCS sw has no utility. Ground clutter is
displayed on the screen.
Ground clutter is displayed on the screen.
PWS sw
AUTO : Activates the Predictive WindShear function in accordance with activation
conditions (Refer to DSC-34-SURV-30-20 Windshear Alerts Above 50 feet).
OFF : The Predictive WindShear function is off.
WEATHER RADAR INDICATION ON ND
Ident.: DSC-34-SURV-30-30-00001255.0007001 / 21 MAR 16
Applicable to: ALL
(1)
Weather Radar Picture
‐ When the radar is operating, and when the ND is not in PLAN mode, the ND displays the
weather radar picture.
‐ The weather echoes appear in different colors, depending on the precipitation rates (black,
green, yellow, red or magenta for turbulence).
‐ The selected ND range will determine how often the image is refreshed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-34-SURV-30-30 P 3/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(2)
WEATHER RADAR - CONTROLS AND INDICATORS
Tilt Angle
‐ The multiscan function of the weather radar alternatively scans at low and high beam, and
automatically sets the tilt of these beams to optimize the weather radar detection. The
displayed weather radar picture is the result of the storing and merging of the information
from each beam.
‐ The tilt angle is the angle between the horizon and the radar beam axis. The value of the
tilt angle is in degrees, and quarters of a degree. It appears in the lower right corner of the
screen:
• In green, when the MULTISCAN sw is set to AUTO. This value represents the average of
the lower and the upper beam tilts.
• In blue, next to the blue “MAN ” indication, when the flight crew sets the MULTISCAN sw
to MAN.
• When the multiscan function is lost, the tilt value is dashed and the “NO AUTO TILT”
message appears in amber on the ND , until the flight crew sets the MULTISCAN sw to
MAN.
(3)
Gain Mode
‐ ”MAN GAIN” appears in white, when the flight crew selects the manual gain mode.
(4)
Failure Messages
The ND lists the detected failures.
If the message is in “red”, the ND does not display a radar image.
If the message is in “amber”, the image is not affected.
NO WXR (red)
: Radar System failure.
WXR RT (red)
: Radar transceiver failure.
WXR ANT (red)
: Radar antenna failure.
WXR CTL (red)
: Radar control unit failure.
WXR RNG (red)
: Range error.
WXR WEAK (amber)
: Calibration failure.
WXR ATT (amber)
: Attitude control failure.
WXR STAB (amber)
: Antenna stabilization failure.
PRED W/S (amber)
: PWS function failure.
NO AUTO TILT (amber)
: Automatic tilt adjustment failure.
WXR TEST (amber)
: Radar System test.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-34-SURV-30-30 P 4/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(5)
WEATHER RADAR - CONTROLS AND INDICATORS
PAC alert
When the flight crew sets the display mode selector to WX or WX+T, or WX+T+HZD and
sets the gain to CAL, and when the aircraft is within 80 NM of a storm cell, the Path Attenuation
Compensation (PAC) alert is available.
The PAC alert displays a yellow arc on the outermost scale of the ND, when an intervening
rainfall creates an attenuated area behind a storm cell (also called a radar shadow or
attenuation effect).
Note:
The PAC alert is only available when the MULTISCAN sw is in the AUTO position.
PWS INDICATION ON PFD AND ND
Ident.: DSC-34-SURV-30-30-00020941.0002001 / 17 MAR 17
Applicable to: ALL
(1)
W/S AHEAD message on the PFD
This message is displayed, when the Predictive WindShear system detects windshear ahead of
the aircraft.
The message is in amber or red, depending on the level of the alert. Refer to
DSC-34-SURV-30-20 General.
(2)
Predictive WindShear area indication
A red and black symbol and two yellow radial lines indicate the predicted windshear area.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-34-SURV-30-30 P 5/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEATHER RADAR - CONTROLS AND INDICATORS
Windshear indication is available in ARC and ROSE ND modes.
When the radar detects a windshear event and the ND range is set above 10 NM, a W/S SET
RNG 10 NM (Windshear, set range to 10 NM) message appears. This message requests the
flight crew to adjust the range on the corresponding ND.
Depending on the windshear alert level, ND indication may be associated with an aural
message and a PFD message. Refer to DSC-34-SURV-30-20 General.
(3)
PWS SCAN message on the ND
If only the PWS detection is active, the ND displays a PWS SCAN message when the PWS is
active. In this mode, when the radar detects a windshear event, a windshear symbol and the
weather returns appear automatically on the ND.
MEMO DISPLAY
Ident.: DSC-34-SURV-30-30-00017051.0001001 / 21 MAR 16
Applicable to: ALL
The "PRED W/S OFF" message appears when windshear is set to OFF on the weather radar panel.
PRED W/S OFF
: This memo appears in green during flight phases 2 and 6.
PRED W/S OFF
: This memo appears in amber when:
‐ The aircraft is in flight phases 3, 4, 5, 7, 8, and 9.
‐ The T.O. CONFIG pb is pressed during flight phase 2.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
DSC-34-SURV-30-30 P 6/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GPWS - DESCRIPTION
OVERVIEW
Ident.: DSC-34-SURV-40-10-00021292.0001001 / 17 MAR 17
Applicable to: ALL
The purpose of the Ground Proximity Warning System (GPWS) is to warn the flight crew of
potentially hazardous situations, such as a collision with terrain. It detects terrain collision threats and
triggers applicable aural and visual indications.
The GPWS includes:
‐ Five basic modes active up to radio height of 2 500 ft.
•
•
•
•
•
Excessive rate of descent (Mode 1)
Excessive terrain closure rate (Mode 2)
Altitude loss after takeoff or go-around (Mode 3)
Terrain clearance not sufficient, if not in landing configuration (Mode 4)
Excessive descent below the glide slope (Mode 5).
‐ A predictive GPWS function, based on a GPWS database, to display terrain information. It
can be provided:
• By Honeywell through Enhanced GPWS (EGPWS)
• By ACSS as Ground Collision Avoidance System (GCAS ), through T2CAS or T3CAS.
The predictive GPWS is composed of:
• Mandatory functions such as the Forward Looking Terrain Alerting function
• Optional functions such as the obstacle database.
Note:
The terrain data are displayed on the ND and the brightness is controlled via the weather
radar brightness control knob. If the weather radar brightness was set to low (due to bad
weather) and a terrain alert occurs, then the brightness of the terrain display will also be
low.
PRINCIPLE
Ident.: DSC-34-SURV-40-10-00021293.0001001 / 17 MAR 17
Applicable to: ALL
The GPWS computes the geometric altitude of the aircraft by using:
‐ Pressure altitude
‐ Radio altitude
‐ Temperature
‐ Barometric references
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-34-SURV-40-10 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
‐ GPS altitude for predictive GPWS
‐ Data from the GPWS database for predictive GPWS .
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-34-SURV-40-10 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - GPWS BASICS MODES
FLIGHT CREW
OPERATING MANUAL
MODE 1 : EXCESSIVE RATE OF DESCENT
Ident.: DSC-34-SURV-40-20-00015115.0004001 / 13 JAN 14
Applicable to: ALL
Mode 1 triggers aural and visual alerts about excessive rates of descent, based on the radio height,
and the rate of descent of the aircraft.
Mode 1 is active for all phases of the flight.
CAUTION
AURAL ALERT
VISUAL ALERT
WARNING
"SINK RATE, SINK RATE"
The GPWS amber
lights come on
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
"PULL UP"
(repeated as long as MODE 1 is triggered)
The PULL UP red
lights come on
DSC-34-SURV-40-20 P 1/6
05 SEP 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - GPWS BASICS MODES
FLIGHT CREW
OPERATING MANUAL
MODE 2 : EXCESSIVE TERRAIN CLOSURE RATE
Ident.: DSC-34-SURV-40-20-00015116.0004001 / 03 AUG 17
Applicable to: ALL
Mode 2 triggers aural and visual alerts, based on the landing gear/flaps configuration of the aircraft,
the radio height, and the RA rate of change.
There are two types of Mode 2 alerts, Mode 2A (active during climb, cruise, and initial approach), and
Mode 2B (active during approach and 60 s after takeoff).
CONFIGURATION
AURAL ALERT
VISUAL ALERT
Flaps not in Landing Position + Landing Gear Up (Mode 2A)
Flaps in landing position + Landing Gear Up (Mode 2B)
CAUTION
WARNING
"PULL UP"
(repeated as long as
MODE 2 is triggered in
the warning conditions)
"TERRAIN, TERRAIN"
The GPWS amber
lights come on
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
The PULL UP red
lights come on
B→
"TERRAIN"
(repeated as long as MODE
2 is triggered after leaving
the warning conditions)
The PULL UP
red lights stay on
DSC-34-SURV-40-20 P 2/6
05 SEP 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - GPWS BASICS MODES
FLIGHT CREW
OPERATING MANUAL
CONFIGURATION
AURAL ALERT
Flaps in landing position + Landing Gear Down (Mode 2B)
CAUTION
"TERRAIN"
(repeated as long as MODE 2 is triggered)
VISUAL ALERT
The GPWS amber lights come on
MODE 3 : ALTITUDE LOSS AFTER TAKEOFF
Ident.: DSC-34-SURV-40-20-00015117.0004001 / 19 SEP 13
Applicable to: ALL
Mode 3 triggers aural and visual alerts when the altitude significantly decreases after takeoff, and
go-arounds with landing gear or flaps not in landing configuration.
CAUTION
AURAL ALERT
"DON'T SINK, DON'T SINK"
(repeated as long as MODE 3 is triggered)
VISUAL ALERT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
The GPWS amber lights come on
← B to C
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05 SEP 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GPWS - GPWS BASICS MODES
MODE 4 : UNSAFE TERRAIN CLEARANCE WHEN NOT IN LANDING CONFIGURATION
Ident.: DSC-34-SURV-40-20-00015118.0005001 / 13 JAN 14
Applicable to: ALL
There are three types of Mode 4 alerts, Mode 4A and Mode 4B (both active during cruise and
approach), and Mode 4C (active during takeoff*).
Mode 4A and Mode 4B trigger aural and visual alerts when terrain clearance is not sufficient based
on the phase of flight, the configuration of the landing gear and the flaps, and the speed. Mode 4C
triggers aural and visual alerts based on the minimum terrain clearance and the radio height of the
aircraft. *(Only EGPWS not T2CAS)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
DSC-34-SURV-40-20 P 4/6
05 SEP 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - GPWS BASICS MODES
FLIGHT CREW
OPERATING MANUAL
CONFIGURATION
AURAL ALERT
Landing gear
Up (Mode 4A)
"TOO LOW
TERRAIN"
"TOO LOW
GEAR"
VISUAL ALERT
Flaps not in landing
position + Landing
gear down (Mode 4B)
CAUTION
"TOO LOW
TERRAIN"
Flaps not in landing
position OR Landing
Gear Up (Mode 4C)
"TOO LOW
FLAPS"
"TOO LOW TERRAIN"
The GPWS amber lights come on
MODE 5 : DESCENT BELOW GLIDESLOPE
Ident.: DSC-34-SURV-40-20-00015119.0004001 / 19 SEP 13
Applicable to: ALL
Mode 5 triggers aural and visual alerts, when the aircraft descends below the glide slope.
CAUTION
AURAL ALERT
"GLIDESLOPE'"
(repeated as long as MODE 5 is triggered)
VISUAL ALERT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
The GPWS amber lights come on
← D to E
DSC-34-SURV-40-20 P 5/6
05 SEP 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - GPWS BASICS MODES
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-34-SURV-40-20 P 6/6
05 SEP 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - PREDICTIVE GPWS FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
TERRAIN AWARENESS AND DISPLAY
Ident.: DSC-34-SURV-40-35-00001417.0114001 / 29 JUN 16
Applicable to: ALL
The Terrain Awareness and Display (TAD) function computes a caution and a warning envelope
in front of the aircraft, depending on the aircraft altitude, the nearest runway altitude, the distance
to the nearest runway threshold, the ground speed, and the turn rate. When the boundary of these
envelopes conflicts with the terrain, or with an obstacle memorized in the database, the system
generates the relevant alert:
Alert Level
ND (Refer to DSC-31-45
Flags and Messages
Displayed on ND)
Aural Warning
TERRAIN
TERRAIN PULL UP
Warning
‐ Automatic terrain display
See *
‐ Solid red areas
‐ TERRAIN (red)
‐ Automatic terrain display
OBSTACLE
See *
OBSTACLE, PULL UP ‐ Solid red areas
‐ OBST (red)
CAUTION TERRAIN
Caution
Local Warning
‐ Automatic terrain
displaySee *
‐ Solid yellow areas
‐ TERRAIN (amber)
On each pilot’s instrument
panel, The pushbutton
light comes on.
‐ Automatic terrain display
See *
CAUTION OBSTACLE ‐ Solid yellow areas
‐ OBST (amber)
* When the TERR pb-sw ON ND is set to ON, and ARC or ROSE mode is selected, the ND displays
the terrain and the obstacles memorized in the database, depending on the aircraft’s position. The
terrain is displayed in various densities of green, yellow, red, or magenta, depending on the threat
(Refer to DSC-31-45 Flags and Messages Displayed on ND). If an alert is generated (caution or
warning), and TERR pb-sw ON ND is not selected, the terrain and the obstacles are automatically
displayed, and the ON light of the TERR pb-sw ON ND comes on.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-34-SURV-40-35 P 1/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
GPWS - PREDICTIVE GPWS FUNCTIONS
1. When TERR pb-sw ON ND is selected, the weather radar image is not displayed.
2. The Geometric Altitude function can protect against certain BARO setting errors,
provided the components used to compute the Geometric Altitude are valid and accurate
enough.
3. The TAD and Terrain Clearance Floor (TCF) functions operate using the pure lateral
GPS position and, the FMS1 position as backup.
If the crew identifies that navigation accuracy is low, it must set the enhanced modes to off, via the
TERR pb-sw. The 5 GPWS modes remain active.
TERRAIN CAUTION AND WARNING ENVELOPE
Ident.: DSC-34-SURV-40-35-00006161.0002001 / 19 DEC 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-34-SURV-40-35 P 2/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - PREDICTIVE GPWS FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
VERTICAL ENVELOPE
HORIZONTAL ENVELOPE
TERRAIN CLEARANCE FLOOR
Ident.: DSC-34-SURV-40-35-00006162.0002001 / 03 JUN 14
Applicable to: ALL
A terrain clearance floor envelope is stored in the database for each runway for which terrain data
exist. The Terrain Clearance Floor (TCF) function warns of a premature descent below this floor,
regardless of aircraft configuration.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-34-SURV-40-35 P 3/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - PREDICTIVE GPWS FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
If the airplane descends below this floor, a TOO LOW TERRAIN aural warning is announciated, and
the pushbutton light comes on, on the glareshield.
RUNWAY FIELD CLEARANCE FLOOR
Ident.: DSC-34-SURV-40-35-00006163.0002001 / 19 DEC 12
Applicable to: ALL
The Runway Field Clearance Floor (RFCF) provides an additional envelope protection, for runways
that are significantly higher than the surrounding terrain. It is contained in a circle within the 5.5 NM
of the runway threshold and it is based on the geometric altitude and the runway elevation.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
DSC-34-SURV-40-35 P 4/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
GPWS - PREDICTIVE GPWS FUNCTIONS
←D
DSC-34-SURV-40-35 P 5/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - PREDICTIVE GPWS FUNCTIONS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-34-SURV-40-35 P 6/6
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-34-SURV-40-40-00001418.0002001 / 21 MAR 17
Applicable to: ALL
(1)
SYS pushbutton
OFF
: All basic GPWS alerts (Mode 1 to 5) are inhibited.
FAULT light : This amber light comes on, along with an ECAM caution, if the basic GPWS
mode 1 to 5 malfunction.
Note:
If ILS 1 fails, only mode 5 is inhibited. Consequently, the FAULT light does not come
on and the GPWS FAULT warning is not triggered.
(2)
G / S MODE pushbutton
OFF
: Glideslope mode (mode 5) is inhibited.
(3)
FLAP MODE pusbutton
OFF
: Flap mode (“TOO LOW FLAPS” mode 4) is inhibited.
(To avoid nuisance warning in case of landing with flaps setting reduced).
(4)
LDG FLAP 3 pushbutton
ON
: Flap mode is inhibited when FLAPS CONF 3 is selected (to avoid nuisance
warning in case of landing in CONF 3).
In this case, LDG MEMO displays "FLAPS ... 3" instead of “CONF ... FULL”.
(5)
TERR pushbutton
OFF
: Inhibits the Terrain Awareness Display (TAD) and Terrain Clearance Floor
(TCF) modes, and does not affect the basic GPWS mode 1 to 5. If OFF is
selected the ECAM caution NAV GPWS TERR DET FAULT is displayed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-34-SURV-40-40 P 1/4
19 JUN 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
FAULT light :
This amber light comes on, along with an ECAM caution, if the TAD or TCF
mode fails. The terrain is not shown on the ND . The basic GPWS mode 1 to
mode 5 are still operative if the SYS pushbutton OFF or FAULT lights are not
illuminated.
INSTRUMENT PANELS
Ident.: DSC-34-SURV-40-40-00001419.0003001 / 19 DEC 12
Applicable to: ALL
(1)
GPWS – G/S pushbutton
GPWS : This red light comes on when any mode from 1 to 4, or any TAD or TCF alert is
activated. A specific voice alert accompanies it.
G/S
: Comes on amber when Mode 5 is activated. It is accompanied by the aural
“GLIDE SLOPE” warning.
Note:
1. If the flight crew presses this button briefly when a glide slope warning is on, the
G/S light goes out and the “GLIDE SLOPE” aural warning (soft or loud) stops.
2. On ground, the GPWS can be tested by pressing this pushbutton. If the pushbutton
is pressed briefly, some of the aural warnings sound and pushbutton captions,
related to the GPWS, come on. If the pushbutton is pressed continuously, then all
the aural warnings sound.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-34-SURV-40-40 P 2/4
19 JUN 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
GPWS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(2)
TERR ON ND pushbutton
These pushbuttons are located on either side of the ECAM. Each pushbutton controls the
onside terrain display.
ON
: The terrain is displayed on the ND if the:
‐ TERR pb-sw is selected ON, and
‐ TERR FAULT light is not on.
The ON light comes on.
OFF : The terrain data is not displayed on the ND.
Note:
‐ If the Terrain Awareness Display (TAD) mode generates a caution or a warning,
while the TERR ON ND is not switched ON, the terrain is automatically displayed
on the ND s (see EGPWS specific caution and warning due to TAD mode) and the
ON light of the TERR ON ND pushbutton come on.
‐ To differenciate between the terrain and the weather display, the terrain display
sweeps from the center outward to both sides of the ND.
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-34-SURV-40-40-A-00017057.0001001 / 21 MAR 16
GPWS FLAP 3
:
This memo appears in green when GPWS LDG FLAP 3 pb-sw is ON.
Ident.: DSC-34-SURV-40-40-A-00017058.0001001 / 21 MAR 16
GPWS FLAP MODE OFF
:
This memo appears in green when GPWS FLAP MODE pb-sw is
OFF.
Ident.: DSC-34-SURV-40-40-A-00017060.0004001 / 21 MAR 16
The TERR OFF memo appears when the TERR pb-sw is OFF.
TERR OFF
: This memo appears in green when:
‐ The aircraft is in flight phase 2, before the Take Off Configuration test is
launched.
‐ The aircraft is in flight phase 6.
TERR OFF
:
This memo appears in amber when:
‐ The aircraft is in flight phase 2, after the Take Off Configuration test.
‐ The aircraft is in flight phases 3, 4, 5, 7, 8 and 9.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-34-SURV-40-40 P 3/4
19 JUN 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GPWS - CONTROLS AND INDICATORS
Ident.: DSC-34-SURV-40-40-A-00017059.0007001 / 21 MAR 16
TERR STBY
:
Airborne TERR STBY memo appears in green when the aircraft position
accuracy (computed by the EGPWS ) is not sufficient to allow the enhanced
TCF and TAD modes to operate. These modes are not available until the
TERR STBY memo disappears. If selected, the terrain data display on ND is
automatically deselected when the TERR STBY memo is triggered.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
DSC-34-SURV-40-40 P 4/4
19 JUN 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TCAS - DESCRIPTION
OVERVIEW
Ident.: DSC-34-SURV-60-10-00020407.0001001 / 21 MAR 17
Applicable to: ALL
The Traffic alert and Collision Avoidance System (TCAS):
‐ Detects and displays surrounding aircraft that have a transponder
‐ Calculates and display possible collision threats
‐ Triggers vertical speed orders, in order to avoid collisions.
PRINCIPLE
Ident.: DSC-34-SURV-60-10-00020408.0001001 / 21 MAR 17
Applicable to: ALL
The TCAS detection capability is limited to intruders flying within a maximum range of 30 NM on
either sides and approximately 30 NM to 80 NM longitudinally (depending on aircraft configuration
and external conditions), and within a maximum altitude range of 9 900 ft above and below the
aircraft.
TCAS Range
The TCAS obtains data transmitted by the transponders of nearby aircraft, and uses this data to
evaluate possible collision threats.
The TCAS determines:
‐ The bearing of intruders, in relation to the bearing of the aircraft.
‐ The distance between the aircraft and intruders, and the rate of separation or closure.
‐ The relative altitude of intruders, if intruders have a Mode-C or Mode-S transponder.
The TCAS then calculates the intruder trajectory, the Closest Point of Approach (CPA), and the
estimated time (TAU) before reaching the CPA.
The TAU is the ratio between the distance that separates both aircraft, and the sum of their speed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-34-SURV-60-10 P 1/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
TAU Definition
If the TCAS detects that the trajectory of an intruder may be a collision threat, it triggers:
‐ Audio and visual indicators
‐ Vertical speed orders, to ensure a sufficient trajectory separation and a minimal vertical speed
variation considering all intruders.
MAIN COMPONENTS
Ident.: DSC-34-SURV-60-10-00020409.0001001 / 21 MAR 17
Applicable to: ALL
The system includes:
‐ A single channel TCAS computer
‐ Two TCAS antennas
‐ Two mode S ATC transponders, one active the other in standby
These transponders allow:
• Interface between the ATC /TCAS control panel and the TCAS computer
• Communication between the aircraft and intruders equipped with a TCAS system.
‐ An ATC /TCAS control panel.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-34-SURV-60-10 P 2/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
INTRUDER DETECTION CATEGORIES
Ident.: DSC-34-SURV-60-10-00020410.0001001 / 21 MAR 17
Applicable to: ALL
The TCAS divides the space surrounding the aircraft into the following four zones, in order to
evaluate and categorize possible collision threats:
‐ Resolution Advisory (RA)
‐ Traffic Advisory (TA)
‐ Proximate intruders
‐ Other intruders.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
DSC-34-SURV-60-10 P 3/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
TCAS Envelopes
Depending on the level of the collision threat, the TCAS triggers audio and visual indicators::
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-34-SURV-60-10 P 4/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
LEVEL
Other intruders
Proximate
Traffic Advisory (TA)
Resolution Advisory
(RA)
INTRUDER POSITION
DISPLAYED INFORMATION AND MESSAGE
‐ No collision threat
‐ ND: Intruder position
‐ Any non proximate, TA ,
RA within the surveillance
envelope (lateral range:
Closer than 30 NM )
‐ No collision threat
‐ ND: Intruder position
‐ Intruder in the vicinity of
the A/C (closer than 6 NM
laterally and ±1200 ft
vertically)
‐ Potential collision threat
‐ TAU is about 40 s
‐ ND: Intruder position
‐ Aural messages
‐ Real collision threat
‐ TAU is about 25 s
‐ ND: Intruder position
‐ Aural messages
‐ PFD: Vertical orders
• Maintain actual V/S
(Preventive Advisory) or
• Modify V/S (Corrective
Advisory)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-34-SURV-60-10 P 5/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
TA /RA thresholds
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
DSC-34-SURV-60-10 P 6/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
TCAS MODES
Applicable to: ALL
Ident.: DSC-34-SURV-60-10-10-00020411.0001001 / 21 MAR 17
TCAS MODES
The TCAS has three different modes of operations that can be selected on the ATC / TCAS
control panel:
‐ The Traffic Advisory/Resolution Advisory (TA/RA) mode
‐ The Traffic Advisory Only (TA ONLY) mode
‐ The standby (STBY) mode.
Ident.: DSC-34-SURV-60-10-10-00020412.0001001 / 21 MAR 17
TRAFFIC ADVISORY/RESOLUTION ADVISORY (TA/RA) MODE
The TA/RA mode is the normal TCAS operating mode that enables:
‐ The ND to display all intruders
‐ The PFD to display the vertical speed orders that indicate the vertical direction that the aircraft
should take, in order to avoid a collision.
Ident.: DSC-34-SURV-60-10-10-00020413.0001001 / 21 MAR 17
TRAFFIC ADVISORY ONLY (TA ONLY) MODE
The TA ONLY mode can be selected:
‐ Manually in case of aircraft degraded performance (engine failure, landing gear extended), or in
specific airports, and for specific procedures (identified by operators) that may provide RA that
are neither wanted nor appropriate (e.g. closely-spaced parallel or converging runways)
‐ Automatically, if TA/RA mode is previously selected and:
•
•
•
•
The windshear alert is triggered
The stall warning is triggered
GPWS alerts are triggered
Aircraft is below 1 000 ft AGL.
When the TCAS is operating in TA ONLY mode:
‐ All RA s are inhibited and converted into TAs
‐ TA threshold is set to TAU ≤20 s, irrespective of the aircraft altitude
‐ No vertical speed advisories are indicated on the PFDs
‐ “TA ONLY” is displayed on the NDs
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
DSC-34-SURV-60-10 P 7/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-34-SURV-60-10-10-00020414.0001001 / 21 MAR 17
STANDBY MODE
In the standby mode, the advisory generation and surveillance functions are not active. The TCAS
does not trigger any alert. No TCAS information can be displayed on the PFD s and NDs.
ADVISORY INHIBITION
Ident.: DSC-34-SURV-60-10-00020416.0007001 / 17 MAR 17
Applicable to: ALL
Some advisories are inhibited depending on the aircraft altitude:
‐ All intruders flying below 380 ft AGL when the own aircraft altitude is below 1 700 ft AGL
‐ All RA below 1 100 ft in climb and 900 ft in descent. In this case, the RA s are converted into TAs
‐ “Descend” RA below 1 100 ft AGL
‐ “Increase Descent” RA below 1 550 ft AGL
‐ All TA aural messages below 600 ft AGL in climb and below 400 ft AGL in descent
‐ The AP/FD TCAS flight guidance mode is inhibited below 900 ft.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F
DSC-34-SURV-60-10 P 8/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
ATC/TCAS PANEL
Ident.: DSC-34-SURV-60-20-00001429.0064001 / 01 OCT 12
Applicable to: ALL
(1)
(2)
Mode selector
TA/RA
:
TA ONLY
:
STBY
XPNDR
:
:
Normal position.
TA s, RAs, proximate and other intruders are displayed.
This mode should be used, in case of degraded aircraft performance (engine
failure, landing gear extended, or approach on parallel runways).
All RA s are converted into TA s. TAs, proximate and other intruders are
displayed.
The TCAS and ATC are on standby.
‐ The TCAS is on standby
‐ On ground : The selected ATC Transponder only operates in the
selective aircraft interrogation mode of Mode S
‐ In flight : The selected ATC Transponder operates.
TRAFFIC selector
ABV
: The altitude range is set to +7 000 ft above the aircraft, and -2 700 ft below
the aircraft.
N
: The altitude range is set to -2 700 ft below the aircraft, and +2 700 ft above
the aircraft.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-34-SURV-60-20 P 1/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
BLW
(3)
:
The altitude range is set to -7 000 ft below the aircraft, and +2 700 ft above
the aircraft.
AUTO/ON selector or THRT/ALL selector
ON (or ALL) : All intruders are displayed.
AUTO (or
: Proximate and other intruders are only displayed, if a TA or RA is already
THRT)
presented.
Note:
Some TCAS control panels are equipped with a THRT/ALL selector, instead of the
AUTO/ON selector. The associated functions remain unchanged.
ND INDICATIONS
Ident.: DSC-34-SURV-60-20-00020418.0002001 / 17 MAR 17
Applicable to: ALL
The traffic is displayed in all ROSE modes and ARC mode when 10, 20 or 40 NM range is selected.
Only the 8 most threatening intruders are displayed.
(1)
Proximate intruder
Indicated by a white filled diamond.
(2)
TA intruder
Indicated by an amber circle.
Associated with the TRAFFIC-TRAFFIC aural message.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-34-SURV-60-20 P 2/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TCAS - CONTROLS AND INDICATORS
(3)
RA intruder
Indicated by a red square.
Associated with vertical orders displayed on the PFD and aural messages.
(4)
Other intruders
Indicated by a white empty diamond.
Note:
If the range of an intruder is not available, the intruder is not displayed. An intruder
may be partially displayed when its range is out of scale.
(5)
Relative altitude
Indicated in hundred of feet above or below the symbol depending on the intruder position.
(6)
Vertical speed arrow
Displayed only if the intruder V/S > 500 ft/min.
Relative altitude and vertical speed arrow are displayed in the same color as the associated
intruder symbol.
Note:
(7)
If the altitude of an intruder is not available, neither altitude nor vertical speed
indications are displayed.
No bearing intruder
If the bearing of TA or RA intruder is not available the following data is presented in digital form
at the bottom of the ND:
‐ range
‐ relative altitude and vertical speed arrow if available.
Displayed amber or red according to threat level.
(8)
Range ring
A 2.5 NM white range ring is displayed when a 10 NM or 20 NM range is selected.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-34-SURV-60-20 P 3/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
TCAS MESSAGES
Ident.: DSC-34-SURV-60-20-00020419.0001001 / 17 MAR 17
Applicable to: ALL
(1)
Mode and range messages
Following messages can be displayed to draw pilot’s attention:
TCAS : REDUCE RANGE : Displayed when a TA or RA is detected and ND range above
40 NM.
TCAS : CHANGE MODE : Displayed when a TA or RA is detected and ND mode is
PLAN.
Displayed amber or red depending on the advisory level (TA or RA).
(2)
TCAS operation messages
TCAS
: Displayed in case of TCAS internal failure.
TA ONLY : Displayed white when the TA mode is selected automatically, or manually by the
flight crew.
PFD INDICATIONS
Ident.: DSC-34-SURV-60-20-00020420.0005001 / 17 MAR 17
Applicable to: ALL
In case of RA detection, the vertical speed scale becomes rectangular and the PFD presents vertical
orders on the vertical speed scale. The vertical speed scale background is normally grey, but may be
partially replaced by green and/or red areas.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D →
DSC-34-SURV-60-20 P 4/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(1)
Red area
Indicates the vertical speed range, when there is a high risk of conflict.
(2)
Green area
Indicates the recommended vertical speed range. It is wider than the red area.
Note:
(3)
‐ The aircraft can also fly in the grey vertical speed range, without the risk of conflict
(preventive RA).
‐ The color of the digits corresponds to the appropriate area.
‐ In case of RA detection, the vertical speed needle that is normally green, becomes
white.
TCAS message
Appears in amber provided that the TCAS is not in standby, when the TCAS cannot deliver RA
data, or in case of an internal TCAS failure.
AURAL MESSAGES
Ident.: DSC-34-SURV-60-20-00001433.0018001 / 08 FEB 13
Applicable to: ALL
TA /RA detection is associated with the following messages:
"TRAFFIC TRAFFIC"
: Only in case of TA detection.
"CLIMB CLIMB"
: Climb at the vertical speed indicated by the green
area on the PFD.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
DSC-34-SURV-60-20 P 5/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
"CLIMB, CROSSING CLIMB" (twice)
:
"INCREASE CLIMB" (twice)
:
"DESCEND DESCEND"
:
"DESCEND, CROSSING
DESCEND" (twice)
"INCREASE DESCEND" (twice)
:
"LEVEL OFF, LEVEL OFF"
"CLIMB CLIMB NOW" (twice)
:
:
:
"DESCEND DESCEND NOW" (twice) :
"MONITOR VERTICAL SPEED"
:
"MAINTAIN VERTICAL SPEED,
MAINTAIN"
"MAINTAIN VERTICAL SPEED,
CROSSING MAINTAIN"
:
"CLEAR OF CONFLICT"
:
:
Same as above. Indicates that you will cross through
the intruder altitude.
Triggered after the CLIMB message, if vertical speed
is insufficient to achieve safe vertical separation.
Descend at the vertical speed indicated by the green
area on the PFD.
Same as above. Indicates that you will cross through
the intruder altitude.
Triggered after the DESCEND message, if the
vertical speed is insufficient to achieve safe vertical
separation.
Set the Vertical Speed to 0.
Triggered after the DESCEND message, if the
intruder trajectory has changed.
Triggered after the CLIMB message, if the intruder
trajectory has changed.
Ensure that the vertical speed remains outside the
red area.
Triggered only once, in case of preventive RA.
Maintain the vertical speed indicated on the green
area of the PFD.
Maintain the vertical speed indicated on the green
area of the PFD.
Indicates that you will cross through the intruder
altitude.
The range increases and separation is adequate.
Return to assigned clearance.
MEMO DISPLAY
Ident.: DSC-34-SURV-60-20-00020422.0002001 / 17 MAR 17
Applicable to: ALL
TCAS STBY
:
This memo appears in green when:
‐
‐
‐
‐
ATC STBY is selected by the crew, or
TCAS STBY is selected by the crew during flight phases other than 6, or
ALT RPTG sw is OFF, or
both ATC s or both RAs are failed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F →
DSC-34-SURV-60-20 P 6/8
22 MAR 17
AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TCAS STBY
:
TCAS - CONTROLS AND INDICATORS
This memo appears in amber when the flight crew sets the TCAS on STBY in
flight phase 6.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
DSC-34-SURV-60-20 P 7/8
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AIRCRAFT SYSTEMS
SURVEILLANCE
A318/A319/A320/A321
TCAS - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
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22 MAR 17
AIRCRAFT SYSTEMS
OXYGEN
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AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-35-10 General
Description............................................................................................................................................................... A
DSC-35-20 Fixed Oxygen System for Cockpit
DSC-35-20-10 Description
General.....................................................................................................................................................................A
Operation..................................................................................................................................................................B
Schematic................................................................................................................................................................ C
Mask Setting............................................................................................................................................................ D
Mask Stowage......................................................................................................................................................... E
DSC-35-20-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Stowage Box............................................................................................................................................................B
Crew Oxygen Mask................................................................................................................................................. C
Pressure Regulator..................................................................................................................................................D
ECAM DOOR/OXY Page........................................................................................................................................ E
DSC-35-30 Fixed Oxygen System for Cabin
DSC-35-30-10 Description
General.....................................................................................................................................................................A
Operation..................................................................................................................................................................B
Schematic................................................................................................................................................................ C
DSC-35-30-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
Overhead Maintenance Panel................................................................................................................................. B
Memo Display.......................................................................................................................................................... C
DSC-35-40 Portable Oxygen System
DSC-35-40-10 Description
Flight Crews Portable Oxygen System................................................................................................................... A
Using the Hood........................................................................................................................................................B
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-35-PLP-TOC P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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FCOM
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22 MAR 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-35-10-00001448.0001001 / 20 DEC 10
Applicable to: ALL
The oxygen system consists of:
‐ A cockpit-fixed oxygen system, which supplies adequate breathing oxygen to the cockpit
occupants in case of depressurization, or emission of smoke and noxious gases.
‐ A cabin-fixed oxygen system, which supplies oxygen for cabin occupants (passengers and cabin
crew) in case of depressurization.
‐ A portable oxygen system, which is provided in both the cockpit and cabin and is to be used:
• As PROTECTION for the crew during on board emergencies.
• For FIRST AID purposes.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-35-10 P 1/2
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AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
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DSC-35-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - DESCRIPTION
GENERAL
Ident.: DSC-35-20-10-00017801.0001001 / 21 MAR 16
Applicable to: ALL
The cockpit’s fixed oxygen system consists of :
‐ A high-pressure cylinder, located in the left-hand lower fuselage.
‐ A pressure regulator, connected directly to the cylinder that delivers oxygen, at a pressure suitable
for users.
‐ Two overpressure safety systems to vent oxygen overboard, through a safety port, if the pressure
becomes too high.
‐ A supply solenoid valve that allows the crew to shut off the distribution system.
‐ Three (or four ) full-face quick-donning masks, stowed in readily-accessible boxes adjacent to
the crewmembers’ seats (one at each seat).
OPERATION
Ident.: DSC-35-20-10-00001450.0001001 / 21 MAR 16
Applicable to: ALL
The crewmember squeezes the red grips to pull the mask out of its box, and this action causes the
mask harness to inflate.
A mask-mounted regulator supplies a mixture of air and oxygen or pure oxygen, or performs
emergency pressure control. With the regulator set to NORMAL, the user breathes a mixture of cabin
air and oxygen up to the cabin altitude at which the regulator supplies 100 % oxygen. The user can
select 100 %, in which case the regulator supplies pure oxygen at all cabin altitudes.
If the situation calls for it, the user can use the emergency overpressure rotating knob and receive
pure oxygen at positive pressure.
The storage box contains a microphone lead, with a quick-disconnect, for connection to the
appropriate mask microphone cable.
Note:
Each mask may have a removable film that protects the visor against scratches.
This strip is optional and may be removed from the mask at any time.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-35-20-10 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - DESCRIPTION
SCHEMATIC
Ident.: DSC-35-20-10-00017802.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-35-20-10 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - DESCRIPTION
MASK SETTING
Ident.: DSC-35-20-10-00016919.0001001 / 21 MAR 16
Applicable to: ALL
Note:
The captain (first officer) must exercise caution and turn the head to the right (left) in the
direction of the first officer (captain) in order to ensure fast donning of the mask when the
HUD on the captain (first officer) side is deployed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
DSC-35-20-10 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - DESCRIPTION
MASK STOWAGE
Ident.: DSC-35-20-10-00001453.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
DSC-35-20-10 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
OVERHEAD PANEL
Ident.: DSC-35-20-20-00017803.0001001 / 21 MAR 16
Applicable to: ALL
(1)
CREW SUPPLY pb
This pushbutton controls the solenoid valve.
On : The valve is open, and supplies low pressure oxygen to the masks (normal position in
flight).
OFF: The valve is closed, and the white light comes on.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-35-20-20 P 1/8
22 MAR 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
STOWAGE BOX
Ident.: DSC-35-20-20-00001455.0001001 / 22 MAY 12
Applicable to: ALL
(1)
Blinker flowmeter (yellow)
This indicator flashes when oxygen is flowing.
(2)
RESET/TEST control slide
The crewmember presses the slide, and pushes it in the direction of the arrow to test: the
operation of the blinker; the regulator supply; system sealing downstream of the valve; and the
regulator sealing and system operation. Pressing the RESET control slide, after the oxygen
mask has been used, cuts off the oxygen, and the mask microphone.
(3)
OXY ON flag
As soon as the left flap door opens, the mask is supplied with oxygen and, once it closes (mask
still supplied with oxygen), the “OXY ON” flag appears.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
DSC-35-20-20 P 2/8
22 MAR 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
CREW OXYGEN MASK
Ident.: DSC-35-20-20-00001456.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-35-20-20 P 3/8
22 MAR 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
PRESSURE REGULATOR
Ident.: DSC-35-20-20-00001457.0001001 / 24 NOV 15
Applicable to: ALL
(1)
Red grips
Squeezing the right-hand side grip unlocks the two-flap door, and permits the harness to
inflate.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
DSC-35-20-20 P 4/8
22 MAR 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
(2)
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
EMERGENCY pressure selector
Use of this selector creates on overpressure which eliminates condensation or fogging of the
mask, and prevents smoke, smell or ashes from entering the mask.
‐ Pressing this knob generates an overpressure for a few seconds.
‐ Turning the knob, in the direction of the arrow, generates a permanent overpressure.
Note:
(3)
1. Overpressure supply is automatically started, when cabin altitude exceeds
30 000 ft.
2. Overpressure supply is available only when the N/100% selector is set on the on
the 100 % position.
N/100 % selector
This two-position button is locked down (100% position) when the crewmember pulls the mask
out of the stowage.Pushing the button up from underneath releases it, and it pops up to the N
(normal) position. Pressing it again returns it to 100 %.
100 % : The mask delivers 100 % oxygen.
N
: The mask provides the flight crew with a mixture of air and oxygen. This mixture
changes with cabin altitude. The higher the cabin altitude, the more oxygen the
mask provides, until the mask supplies 100 % oxygen.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
DSC-35-20-20 P 5/8
22 MAR 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
ECAM DOOR/OXY PAGE
Ident.: DSC-35-20-20-00001458.0004001 / 21 MAR 17
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
DSC-35-20-20 P 6/8
22 MAR 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
(1)
OXY pressure indication
It is in green, when the pressure is ≥ 800 PSI.
It pulses in green, when the pressure is < 800 PSI (the DOOR/OXY SD page is automatically
displayed).
It is in amber, when the pressure is < 400 PSI.
On ground, an amber half frame appears when oxygen pressure is < 1 500 PSI.
In this case, the flight crew must check that the remaining quantity is not below the minimum
(Refer to LIM-OXY Minimum Flight Crew Oxygen Pressure).
(2)
REGUL LO PR indication
It is in amber, if oxygen pressure on the low-pressure circuit is low (50 PSI).
(3)
CKPT OXY indication
It is normally in white.
It becomes amber, when:
‐ Pressure goes below 400 PSI
‐ Low oxygen pressure is detected
‐ The overhead panel’s OXYGEN CREW SUPPLY pb is OFF.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
DSC-35-20-20 P 7/8
22 MAR 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR COCKPIT - CONTROLS AND INDICATORS
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AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR CABIN - DESCRIPTION
GENERAL
Ident.: DSC-35-30-10-00017804.0001001 / 13 MAY 16
Applicable to: ALL
In the case of depressurization, the fixed oxygen system in the cabin supplies oxygen to the cabin
occupants.
Chemical generators produce the oxygen. Each generator feeds a group of 2, 3, or 4 masks.
Oxygen masks are located in containers above the passenger seats, in the lavatories, in each galley
, and at each cabin crew station.
Note:
Gaseous generators replace chemical generators in the lavatories.
OPERATION
Ident.: DSC-35-30-10-00016920.0001001 / 21 MAR 16
Applicable to: ALL
Each container has an electrical latching mechanism that opens automatically to allow the masks to
drop, if the cabin pressure altitude exceeds 14 000 ft (+250, -750 ft), or 16 000 ft (+250, -750 ft) for
the operation on high altitude airfields .
Members of the flight crew can override the automatic control.
When the masks are released, the passenger address system automatically broadcasts prerecorded
instructions .
The generation of oxygen begins when the passenger pulls the mask towards the passenger seat.
The chemical reaction used for oxygen generation creates heat. Therefore, the smell of burning,
smokes and cabin temperature increase may be associated with the normal operation of the oxygen
generators. The mask receives pure oxygen under positive pressure for about 13 min , 15 min
, or up to 22 min , until the generator is exhausted.
A reset is available for the rearming of the system after the masks are restowed. A manual release
tool allows crew members to open the doors manually in case of electrical failure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-35-30-10 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR CABIN - DESCRIPTION
SCHEMATIC
Ident.: DSC-35-30-10-00001461.0001001 / 16 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-35-30-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR CABIN - CONTROLS AND INDICATORS
OVERHEAD PANEL
Ident.: DSC-35-30-20-00017805.0001001 / 21 MAR 16
Applicable to: ALL
(1)
PASSENGER SYS ON light
This light comes on in white, when the control for the oxygen mask doors is activated,
and it remains on until the TMR RESET pb is pressed (Refer to DSC-35-30-20 Overhead
Maintenance Panel).
(2)
MASK MAN ON pb
The guard keeps this button in the AUTO position.
AUTO
: The mask doors open automatically, when the cabin altitude exceeds 14 000 ft,
or 16 000 ft if the HI ALT LANDING pb-sw is set to ON.
Pressed : The mask doors open.
(3)
HI ALT LANDING pb-sw
This pushbutton-switch changes the altitude threshold for the deployment of the passenger
oxygen masks.
OFF: The masks drop, if the cabin pressure exceeds 14 000 ft (+250, -750 ft).
ON : The masks drop, if the cabin pressure exceeds 16 000 ft (+250, -750 ft).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-35-30-20 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FIXED OXYGEN SYSTEM FOR CABIN - CONTROLS AND INDICATORS
OVERHEAD MAINTENANCE PANEL
Ident.: DSC-35-30-20-00001463.0001001 / 11 FEB 11
Applicable to: ALL
(1)
TMR RESET pushbutton
The maintenance crew uses this pushbutton to reset the control circuit, after the system has
operated.
ON
: The PASSENGER SYS ON light goes off.
FAULT : This light comes on in white, when the door latch solenoids are energized for more
than 30 s.
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-35-30-20-A-00016865.0001001 / 21 MAR 16
HI ALT SET
:
This memo appears in green if the crew sets the HI ALT LANDING pb-sw to
ON. In this case, the passenger mask release altitude is 16 000 ft (+250 ft,
-750 ft).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B to C
DSC-35-30-20 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PORTABLE OXYGEN SYSTEM - DESCRIPTION
FLIGHT CREWS PORTABLE OXYGEN SYSTEM
Ident.: DSC-35-40-10-00001465.0004001 / 17 MAR 11
Applicable to: ALL
The flight crew smoke hood located on the right back side of the cockpit, ensures the eyes and
respiratory system protection of one flight crew member when fighting a fire and in case of smoke or
noxious gas emissions or cabin depressurization.
The smoke hood is equipped with one solid state oxygen supply source and one CO2 absorption
system, contained in a life support pack which furnish an effective time of use of 15 min.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-35-40-10 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
OXYGEN
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PORTABLE OXYGEN SYSTEM - DESCRIPTION
USING THE HOOD
Ident.: DSC-35-40-10-00006226.0004001 / 22 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
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AIRCRAFT SYSTEMS
PNEUMATIC
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-36-10 Description
DSC-36-10-10 General
General.....................................................................................................................................................................A
DSC-36-10-20 Engine Bleed System
General.....................................................................................................................................................................A
Architecture.............................................................................................................................................................. B
Air Bleed Selection.................................................................................................................................................. C
Pressure Regulation and Limitation........................................................................................................................ D
Temperature Regulation and Limitation.................................................................................................................. E
DSC-36-10-30 APU Bleed Air Supply
General.....................................................................................................................................................................A
DSC-36-10-40 Crossbleed
General.....................................................................................................................................................................A
ECAM Indication...................................................................................................................................................... B
DSC-36-10-50 Leak Detection
Leak Detection......................................................................................................................................................... A
DSC-36-10-60 Operation Following Failures
BMC Failure............................................................................................................................................................. A
DSC-36-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
ECAM Bleed Page...................................................................................................................................................B
Memo Display.......................................................................................................................................................... C
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-36-10-10-00020804.0001001 / 17 MAR 17
Applicable to: ALL
The pneumatic system supplies high-pressure air for :
‐ Air conditioning
‐ Engine starting
‐ Wing anti-icing
‐ Water pressurization
‐ Hydraulic reservoir pressurization
‐ FWD cargo heating
‐ AFT cargo heating
‐ Fuel Tank Inerting System (FTIS) .
High-pressure air has three sources :
‐ Engine bleed systems
‐ APU load compressor
‐ HP ground connection
Note:
An external HP source may be used for air conditioning.
A crossbleed duct interconnects the engine bleed systems and receives air from the APU and ground
sources when appropriate.
A valve mounted on the crossbleed duct allows the left side (engine 1) and right side (engine 2) to be
interconnected.
Two Bleed Monitoring Computers (BMC 1 and BMC 2), the overhead control panel, and the ECAM
control and monitor the operation of the pneumatic system.
A leak detection system detects any overheating in the vicinity of hot air ducts.
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DSC-36-10-10 P 1/2
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
DESCRIPTION - GENERAL
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - ENGINE BLEED SYSTEM
GENERAL
Ident.: DSC-36-10-20-00001469.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft has two similar engine bleed air systems.
Each system is designed to :
‐ select the compressor stage to use as a source of air
‐ regulate the bleed air temperature
‐ regulate the bleed air pressure.
A Bleed Monitoring Computer (BMC) controls and monitors each system.
Each BMC receives information about bleed pressure and temperature and valve position.
Each is connected with :
‐ other systems using air or information from the bleed system
‐ the other BMC.
Each supplies indications and warnings to the ECAM and CFDS.
If one BMC fails, the other one takes over most of the monitoring functions.
Each bleed valve is pneumatically operated and controlled electrically by its associated BMC.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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DESCRIPTION - ENGINE BLEED SYSTEM
FLIGHT CREW
OPERATING MANUAL
ARCHITECTURE
Ident.: DSC-36-10-20-00001470.0005001 / 15 MAR 17
Applicable to: ALL
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
DESCRIPTION - ENGINE BLEED SYSTEM
FLIGHT CREW
OPERATING MANUAL
AIR BLEED SELECTION
Ident.: DSC-36-10-20-00001471.0003001 / 09 OCT 12
Applicable to: ALL
Air is normally bled from the intermediate pressure stage (IP ) of engine’s high-pressure (HP)
compressor to minimize fuel penalty.
At low engine speed, when the pressure and temperature of the IP air are too low, the system bleeds
air from the HP stage and maintains it at 36 ± 4 PSI.
An intermediate pressure check valve downstream of the IP port closes to prevent air from the HP
stage from being circulated to the IP stage.
L3
The HP valve closes automatically
‐ • In case of low upstream pressure
• in case of excessive upstream pressure
‐ electrically when the bleed valve is closed electrically.
ECAM INDICATION
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FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - ENGINE BLEED SYSTEM
PRESSURE REGULATION AND LIMITATION
Ident.: DSC-36-10-20-00001472.0004001 / 15 MAR 17
Applicable to: ALL
The bleed valve, which is downstream of the junction of HP and IP ducting, acts as a shut-off and
pressure regulating valve.
It maintains delivery pressure at 45 ± 5 PSI.
Note:
Bleed pressure may fluctuate between 38 and 56 PSI (with a maximum peak to peak
pressure of 16 PSI) particularly at high engine power (takeoff or climb) up to FL 100.
The bleed valve is fully closed:
‐ Pneumatically:
• If upstream pressure goes below 8 PSI
• If there is return flow
‐ Electrically by means of:
• The BLEED pushbutton switch (switched OFF)
• The ENG FIRE pushbutton (pushed)
• The Bleed air Monitoring Computer (BMC) in the following cases:
‐
‐
‐
‐
‐
‐
Overtemperature
Overpressure
Leak
Open starter valve
Engine shutdown
APU bleed being ON.
If pressure regulation fails, the overpressure valve closes when the pressure goes over 85 PSI.
Note:
If APU Bleed is ON and the crossbleed valve is SHUT, the Engine bleed valve 2, remains
open.
TEMPERATURE REGULATION AND LIMITATION
Ident.: DSC-36-10-20-00001473.0001001 / 21 MAR 16
Applicable to: ALL
A precooler downstream of the bleed valve regulates the temperature of the bleed air.
The precooler is an air-to-air heat exchanger that uses cooling air bleed from the engine fan to
regulate the temperature to approximately 200 °C.
The fan air valve controls fan air flow.
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - ENGINE BLEED SYSTEM
A spring keeps the fan air valve closed in the absence of pressure.
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A318/A319/A320/A321
DESCRIPTION - ENGINE BLEED SYSTEM
FLIGHT CREW
OPERATING MANUAL
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - APU BLEED AIR SUPPLY
GENERAL
Ident.: DSC-36-10-30-00001474.0001001 / 15 MAR 17
Applicable to: ALL
Air from the APU load compressor is available on ground and in flight.
The APU bleed valve operates as a shut-off valve to control APU bleed air.
The APU BLEED pb-sw, on the AIR COND panel, controls the APU bleed valve. When the flight
crew selects ON with the pushbutton, APU bleed air supplies the pneumatic system, if the APU
speed is above 95 %. This opens the crossbleed valve and closes the engine bleed automatically.
If the APU bleed valve is opened, it automatically closes in the case of APU leak, left wing leak, or
engine 1 leak (except during engine start). Refer to DSC-36-10-50 Leak Detection.
A check valve near the crossbleed duct protects the APU, when bleed air comes from another
source.
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PNEUMATIC
A318/A319/A320/A321
DESCRIPTION - APU BLEED AIR SUPPLY
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
DESCRIPTION - CROSSBLEED
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-36-10-40-00001476.0001001 / 21 MAR 16
Applicable to: ALL
A crossbleed valve on the crossbleed duct allows the air supply systems of the two engines to be
isolated or interconnected.
On the AIR COND panel, a rotary selector controls the crossbleed valve electrically.
Two electric motors, one for automatic mode and one for manual mode, control the valve.
In automatic mode, the crossbleed valve opens when the system uses APU bleed air. It closes, if the
system detects an air leak (except during engine start).
ECAM INDICATION
Ident.: DSC-36-10-40-00001478.0002001 / 21 MAR 16
Applicable to: ALL
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A318/A319/A320/A321
DESCRIPTION - CROSSBLEED
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
DESCRIPTION - LEAK DETECTION
FLIGHT CREW
OPERATING MANUAL
LEAK DETECTION
Ident.: DSC-36-10-50-00001479.0001001 / 15 MAR 17
Applicable to: ALL
Leak detection loops detect any overheating near the hot air ducts in the fuselage, pylons, and
wings.
For the pylon and APU, the sensing elements are tied to form a single loop and for the wing, a
double loop.
When the two wing loops detect a leak, or when one loop detects the leak and the other one is
inoperative, they activate a wing leak signal.
BMC 1 and BMC2 each contain identical control logic for the system.
‐ A wing leak signal causes :
• the bleed valve on the related side to close automatically
• the associated FAULT light on the AIR COND panel to come on
• the x-bleed valve to close automatically (except during an engine start)
• the APU bleed valve to close automatically if the APU bleed valve is open and if the leak
concerns the left wing (except during engine start).
‐ A pylon leak signal causes :
• the bleed valve on the related side to close automatically
• the FAULT light for the related engine on the AIR COND panel to come on
• the x-bleed valve to close automatically (except during an engine start).
• the APU bleed valve to close automatically if the APU bleed valve is open and if the leak
concerns the pylon 1 (except during engine start).
‐ An APU leak signal causes :
• the APU bleed valve to close automatically (except during engine start).
• the FAULT light the APU BLEED pushbutton switch on the AIR COND panel to come on
• the x-bleed valve to close automatically (except during an engine start).
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FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
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DESCRIPTION - LEAK DETECTION
←A
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - OPERATION FOLLOWING FAILURES
BMC FAILURE
Ident.: DSC-36-10-60-00001480.0001001 / 21 MAR 16
Applicable to: ALL
If one BMC fails, the adjacent BMC takes over the monitoring of the bleed system to issue the
following ECAM warnings if necessary :
‐ overpressure
‐ overtemperature
‐ wing leak.
Nevertheless, the associated FAULT light on the AIR COND panel is lost, and the associated bleed
valve does not close automatically.
ENG BLEED LEAK warning is lost for the associated engine, as is also the APU BLEED LEAK
warning if BMC1 has failed.
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PNEUMATIC
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - OPERATION FOLLOWING FAILURES
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Ident.: DSC-36-20-00001481.0001001 / 20 DEC 16
Applicable to: ALL
(1)
ENG 1 and ENG 2 BLEED pb sw
On
: Bleed valve opens if :
‐ Upstream pressure is above 8 PSI.
‐ APU BLEED pushbutton switch is off or APU bleed valve is closed.
‐ There is no onside wing or pylon leak, and no overpressure or
overtemperature has been detected.
‐ The ENG FIRE pushbutton has not been popped out.
‐ The engine start valve is closed.
FAULT lt : This amber light comes on, and an ECAM caution appears, if :
‐ There is an overpressure downstream of the bleed valve.
‐ There is a bleed air overheat.
‐ There is a wing or engine leak on the related side.
‐ The bleed valve is not closed during engine start.
‐ The bleed valve is not closed with APU bleed ON.
lt goes out when the ENG BLEED pushbutton switch is OFF if the fault has
disappeared.
OFF
: The bleed valve and HP valve close. The white OFF light comes on.
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
(2)
APU BLEED pb sw
ON
: The APU valve opens if N > 95 % and there is no leak in the APU or in the left
side bleed. (If there is a leak on the right side, the x-bleed valve closes.)
The blue ON light comes on.
Off
: The APU valve closes.
FAULT
: This amber light comes on, and an ECAM caution appears, when the system
light
detects an APU leak.
(3)
X-BLEED selector sw
AUTO
: The crossbleed valve is open if the APU bleed valve is open.
The crossbleed valve is closed if the APU bleed valve is closed or, in case of a
wing, pylon, or APU leak (except during engine start).
OPEN
: The crossbleed valve is open.
SHUT
: The crossbleed valve is closed.
ECAM BLEED PAGE
Ident.: DSC-36-20-00001482.0002001 / 09 OCT 12
Applicable to: ALL
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AIRCRAFT SYSTEMS
PNEUMATIC
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(1)
HP VALVES
Crossline - Green
In line - Green
Crossline - Amber
(2)
ENGINE BLEED VALVES
In line - Green
: BLEED valve normally open
Crossline - Green
: BLEED valve normally fully closed
In line - Amber
: BLEED valve not in commanded (open) position
Crossline - Amber : BLEED valve not in commanded (closed) position
(3)
ENGINE BLEED INDICATIONS
:
:
:
HP valve normally fully closed
HP valve not fully closed
HP valve not in commanded (closed) position
(A) Precooler inlet pressure
It is normally in green.
It becomes amber, if under 4 PSI, or if overpressure is detected by the BMC (threshold
between 57 and 60 PSI).
(B) Precooler outlet temperature
It is normally in green.
It becomes amber, if the BMC detects an overheat or low temperature.
Overheat: Temperature exceeds:
‐ 290 °C for more than 5 s, or
‐ 270 °C for more than 15 s, or
‐ 257 °C for more than 55 s
Low temperature is detected, if the temperature is lower than 150 °C.
Note:
When the engines are at idle, and depending on the ambient temperature, the
precooler outlet temperature may be below 150 °C (displayed amber).
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CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
(4)
APU BLEED VALVE
Crossline - Green
:
In line - Green
:
Crossline - Amber :
(5)
CROSSBLEED VALVE
Crossline - Green
:
In line - Green
:
Crossline - Amber :
In line - Amber
:
Transit - Amber
:
(6)
GND HP ground connection indication
: Displayed in white when the aircraft is on ground.
(7)
ANTI ICE indication
It is displayed in white, when the WING pushbutton on the ANTI-ICE panel is ON.
(8)
Arrow
(9)
Engine identification (1-2)
It is normally in white.
It becomes amber, when engine N2 is below idle.
:
The APU valve is not fully open, and the APU master switch is ON.
The APU valve is fully open, and the APU master switch is ON.
The APU valve is fully closed, the APU master switch is ON, and the
APU bleed switch is ON for more than 10 s.
The crossbleed valve is normally closed.
The crossbleed valve is normally open.
The crossbleed valve is not in the commanded (closed) position.
The crossbleed valve is not in the commanded (open) position.
The crossbleed valve is in transit.
‐ It is normally not displayed, when the corresponding valve is closed.
‐ It is normally displayed in green, when the corresponding valve is open.
‐ It becomes amber, when the
• Valve is open and air pressure is low or high, or
• Valve is open on ground for more than 10 s.
MEMO DISPLAY
Ident.: DSC-36-20-00016746.0001001 / 21 MAR 16
Applicable to: ALL
APU BLEED :
This memo appears in green, if the APU is available and the APU BLEED pb-sw
is ON.
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AIRCRAFT SYSTEMS
WATER / WASTE
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AIRCRAFT SYSTEMS
WATER / WASTE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-38-10 Description
General.....................................................................................................................................................................A
Potable Water.......................................................................................................................................................... B
Wastewater System.................................................................................................................................................C
Toilet System........................................................................................................................................................... D
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FLIGHT CREW
OPERATING MANUAL
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A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-38-10-00017274.0001001 / 21 MAR 16
Applicable to: ALL
The water and waste systems :
‐ Distribute potable water to the toilets and the galleys
‐ Dispose waste water
‐ Store toilet wastes.
The systems are insulated to prevent water leaks and ice build up.
Controls of the water and waste systems are located on the Forward Attendant Panel (FAP).
POTABLE WATER
Applicable to: ALL
Ident.: DSC-38-10-A-00017286.0002001 / 21 MAR 16
Potable water is stored in a 200 l water tank located in front of the wing box, behind the FWD cargo
compartment.
On ground, the water system is pressurized by the air from the service panel pressure port. In flight,
the water system is pressurized by the bleed air.
Potable water is piped to the galleys and lavatories. Manual shutoff valves isolate wet galleys,
the FWD lavatory, the MID lavatory and the AFT lavatory from the water system. Manual shutoff
valves are located under the washbasins or toilet bowls. The position of each valve is indicated by
OPEN and SHUT legend.
The system can be filled or drained from the service panel under the fuselage. The indication of the
water quantity in the water tank is displayed on the FAP and the aft service panel.
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WATER / WASTE
A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-38-10-A-00017435.0001001 / 21 MAR 16
WASTEWATER SYSTEM
Ident.: DSC-38-10-00017287.0001001 / 21 MAR 16
Applicable to: ALL
The waste/water (from galleys and lavatories) drains overboard through two heated drain masts.
The forward mast drains the waste/water from the forward cabin. The aft mast drains the waste/water
from the aft cabin.
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AIRCRAFT SYSTEMS
WATER / WASTE
A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
The waste and water are discharged by:
‐ Gravity, on ground
‐ Differential pressure, in flight.
TOILET SYSTEM
Ident.: DSC-38-10-00017288.0002001 / 21 MAR 16
Applicable to: ALL
Differential pressure forces the waste from the toilet bowls into the waste tank. The waste tank
has a usable capacity of 170 l. On ground, and in flight below 16 000 ft , the differential pressure is
generated by the vacuum generator.
Clean water from the potable water system flushes toilets.
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AIRCRAFT SYSTEMS
WATER / WASTE
A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
A flush control unit controls the flush sequence in each toilet.
The Vacuum System Controller (VSC) ensures system control, monitoring and fault reporting.
The VSC transmits information to:
‐ Flight attendant panel to indicate the waste tank levels and report system defects
‐ Centralized Fault Display System (CFDS) to signal the system defects to the maintenance.
Ground personnel services the waste tank via a service panel, located under the fuselage.
A manual shutoff valve isolates an inoperative toilet. In the case of an electrical failure of flush valve,
the manual flush control can be used. The manual flush control is located under each toilet bowl.
ARCHITECTURE
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A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
SCHEMATIC
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A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
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MAINTENANCE SYSTEM
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-45-10 Description
General.....................................................................................................................................................................A
Components............................................................................................................................................................. B
Modes of Operation.................................................................................................................................................C
Architecture.............................................................................................................................................................. D
Failure/Fault Classification.......................................................................................................................................E
Functions of the Centralized Fault Display System (CFDS)................................................................................... F
Cockpit/CFDS Interface...........................................................................................................................................G
DSC-45-20 System Operation
Maintenance Menu.................................................................................................................................................. A
Last (or Current) Leg Report...................................................................................................................................B
Last (or Current) Leg ECAM Report....................................................................................................................... C
Previous Leg Report................................................................................................................................................D
Avionics Status........................................................................................................................................................ E
System Report/Test................................................................................................................................................. F
GMT/Date Initialization............................................................................................................................................ G
Backup Mode...........................................................................................................................................................H
ACARS Print Program.............................................................................................................................................. I
DSC-45-25 Data Loading
General.....................................................................................................................................................................A
Data Loading Selector on the Overhead Panel...................................................................................................... B
DSC-45-30 Printer
General.....................................................................................................................................................................A
System Description.................................................................................................................................................. B
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PRELIMINARY PAGES - TABLE OF CONTENTS
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MAINTENANCE SYSTEM
A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-45-10-00001490.0001001 / 21 MAR 16
Applicable to: ALL
The purpose of the Centralized Fault Display System (CFDS) is to make the maintenance task easier
by displaying fault messages in the cockpit and permitting the flight crew to make some specific
tests.
There are two levels of maintenance :
at the line stop
: removal and replacement of equipment
at the main base : troubleshooting
COMPONENTS
Ident.: DSC-45-10-00001491.0001001 / 21 MAR 16
Applicable to: ALL
The CFDS includes :
‐ the BITE (Built-In Test Equipment) for each electronic system
‐ a central computer, the Centralized Fault Display Interface Unit (CFDIU)
‐ two MCDU s (Multipurpose Control and Display Units), used also for FMGS (Flight Management
and Guidance System), AIDS (Aircraft Integrated Data System), and ACARS (Aircraft
Communication And Reporting System, if installed), which work with the CFDIU to display
information or initiate tests
‐ one printer.
If a main channel of the CFDIU fails, the backup channel takes over.
MODES OF OPERATION
Ident.: DSC-45-10-00001492.0001001 / 22 MAR 16
Applicable to: ALL
The CFDS operates in two main modes :
‐ the NORMAL mode or REPORTING mode (in flight)
‐ the INTERACTIVE mode or MENU mode (on ground).
In NORMAL mode, the CFDS records and displays the failure messages transmitted by each system
BITE.
In INTERACTIVE mode, the CFDS allows any BITE to be connected with the MCDU in order to
display the maintenance data stored and formatted by the BITE or to initiate a test.
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MAINTENANCE SYSTEM
A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
ARCHITECTURE
Ident.: DSC-45-10-00001493.0002001 / 19 DEC 12
Applicable to: ALL
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MAINTENANCE SYSTEM
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DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
FAILURE/FAULT CLASSIFICATION
Ident.: DSC-45-10-00017082.0001001 / 21 MAR 16
Applicable to: ALL
The Centralized Fault Display System (CFDS) identifies the faulty system and puts any failures or
faults into one of three classes :
Class 1 : Failures indicated to the flight crew by means of the ECAM , or other flight deck effect.
They must be repaired or entered in the MEL (Minimum Equipment List) before the
aircraft can depart.
Class 2 : Faults indicated to maintenance personnel by the CFDS and which trigger a MAINT
status entry on the maintenance part of the ECAM status page. The aircraft can
operate with these faults, but they must be rectified within the timescale defined in the
Trouble Shooting Manual (TSM).
Class 3 : Faults indicated to maintenance personnel by the CFDS , but which do not trigger a
MAINT status. The operator may have these faults corrected at his convenience.
Failure/fault classes
Operational
consequences
Indication to the
flight crew
Dispatch
consequences
Indication to the
maintenance team
YES
Class 1
NO
YES
Automatically displayed
‐ Warning or caution messages on
Engine
Warning Display
‐ Flag or indication in the flight
deck.
Class 2
YES
Automatically print out at the end of each flight :
Fault messages on the CFDS Post Flight Report.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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E
Class 3
YES
NO
Available on ECAM status
page.
Refer to MMEL/MI-00-08
ECAM and
MAINTENANCE STATUS
Refer to MEL may be :
"GO"
"GO IF"
"NO GO"
NO
MEL not applicable
YES
Available on request
through system report/Test
DSC-45-10 P 3/6
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
FUNCTIONS OF THE CENTRALIZED FAULT DISPLAY SYSTEM (CFDS)
Ident.: DSC-45-10-00001495.0002001 / 21 MAR 16
Applicable to: ALL
The main functions of the CFDS are :
‐ obtaining and storing messages transmitted by the connected system BITEs, or by the Flight
Warning Computer (Warning and Caution titles)
‐ Detailing the maintenance phases.
‐ Presenting maintenance reports :
• Last leg report
• Last leg ECAM report
• Previous leg report
• Avionics status
• System report test
• Post-flight report.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
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24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
COCKPIT/CFDS INTERFACE
Ident.: DSC-45-10-00001496.0001001 / 22 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
DSC-45-10 P 5/6
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
MAINTENANCE MENU
Ident.: DSC-45-20-00001497.0002001 / 14 MAY 12
Applicable to: ALL
The CFDS uses menus displayed on the MCDU. The operator selects functions or reports from these
menus.
Pressing the MCDU MENU key and then selecting CFDS brings up the MAINTENANCE MENU page
(different pages for the aircraft in flight and the aircraft on the ground).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-45-20 P 1/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
LAST (OR CURRENT) LEG REPORT
Ident.: DSC-45-20-00001498.0001001 / 21 MAR 16
Applicable to: ALL
The LAST LEG REPORT (on the ground) or the CURRENT LEG REPORT (in flight), list all class 1
failures and class 2 faults and all system failure and system fault messages received by the CFDS
during the last flight leg or the current flight leg. Pressing the IDENT key displays a list of the systems
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FCOM
← A to B →
DSC-45-20 P 2/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEM OPERATION
(called identifiers) affected by the failure or fault, which helps the pilot or maintenance person to
identify the failure or fault.
LAST (OR CURRENT) LEG ECAM REPORT
Applicable to: ALL
Ident.: DSC-45-20-A-00001499.0001001 / 21 MAR 16
GENERAL
In flight
:
On the ground :
The CURRENT LEG ECAM REPORT displays the primary and independent
warning (class I) messages and MAINTENANCE STATUS (class II) messages
of the current flight leg.
The LAST LEG ECAM REPORT displays the primary and independent
warning (class I) messages plus MAINTENANCE STATUS (class II)
messages of the last flight leg.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
DSC-45-20 P 3/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
Note:
This screen displays PRINT only if the printer is installed.
Ident.: DSC-45-20-A-00001500.0001001 / 14 MAY 12
POST FLIGHT REPORT PRINT
At the end of a flight, LAST LEG and LAST LEG ECAM REPORTS are printed out automatically
after the last engine shutdown. The flight or ground crew can also print them out by selecting
POST FLIGHT REP PRINT.
The report first lists the ECAM warnings, then the FAULT messages.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
DSC-45-20 P 4/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEM OPERATION
PREVIOUS LEG REPORT
Ident.: DSC-45-20-00001501.0001001 / 21 MAR 16
Applicable to: ALL
This report gives access to the POST FLIGHT REPORTS of the previous 63 flight legs.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
DSC-45-20 P 5/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEM OPERATION
On ground, the Operator can print copies of the screen. If ACARS is installed, the Operator can send
the flight report (Refer to DSC-45-20 Last (or Current) Leg ECAM Report - Post Flight Report Print).
AVIONICS STATUS
Ident.: DSC-45-20-00001502.0001001 / 21 MAR 16
Applicable to: ALL
This screen displays the list of systems affected by a failure or fault. If a system is affected by at least
a Class 3 fault, CLASS 3 appears beside it. The display is continuously updated.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
DSC-45-20 P 6/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEM OPERATION
SYSTEM REPORT/TEST
Ident.: DSC-45-20-00001503.0001001 / 21 MAR 16
Applicable to: ALL
This screen gives the operator access to all electronic systems. The CFDIU enters into interactive
dialogue with the selected system.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F →
DSC-45-20 P 7/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
In the above example, the operator has called up menus of the selected systems :
‐ LAST or PREVIOUS LEG REPORT presents the list of Line-Replaceable Units (LRUs) affected by
a failure.
‐ LRU IDENTIFICATION contains the part numbers of all LRUs in the system.
‐ GND SCANNING runs the flight monitoring on the ground and indicates the faulty LRU.
‐ CLASS 3 FAULTS lists class 3 faults detected by the system during the last flight leg.
‐ SYSTEM CONFIGURATION presents the system configuration in a digital form.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
DSC-45-20 P 8/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
Note:
These screens (except LAST or PREVIOUS LEG REPORT) are not shown above.
GMT/DATE INITIALIZATION
Ident.: DSC-45-20-00001504.0001001 / 21 MAR 16
Applicable to: ALL
A CFDIU clock is synchronized with the cockpit clock in order to keep GMT (UTC ) displayed on the
ECAM lower display (except in flight Phases 1 and 2, if the weight and balance system is installed). If
the cockpit clock fails, the CFDIU clock continues to display GMT (UTC ) on the ECAM lower display.
If electrical power is interrupted for more than 200 ms, the crew initializes GMT (UTC ) and the DATE
via the MCDU :
‐ Write GMT (UTC) in the scratchpad, then press the “INIT GMT” key.
‐ Do the same for the month and day.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G →
DSC-45-20 P 9/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
DSC-45-20 P 10/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
BACKUP MODE
Ident.: DSC-45-20-00017066.0001001 / 21 MAR 16
Applicable to: ALL
If the main channel of the CFDIU fails, the backup channel allows the CFDS to operate in backup
mode :
‐ On the ground only
‐ Through MCDU1 or MCDU3
‐ In one mode of operation only : SYSTEM REPORT/TEST
‐ Without the PRINTER or ACARS.
The system changes over from main channel to backup channel :
‐ Automatically in case of an important failure (power supply, for example). In this case, when the
operator selects CFDS on the MCDU MENU, it displays the BACKUP MODE page.
‐ Manually if the operator selects BACKUP MODE on the CFDS menu after a minor failure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H→
DSC-45-20 P 11/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEM OPERATION
ACARS PRINT PROGRAM
Ident.: DSC-45-20-00005361.0001001 / 14 FEB 11
Applicable to: ALL
This function gives access to reprogramming page.
The programming is provided by the ACARS or manually (on the ground or in flight) :
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← H to I →
DSC-45-20 P 12/14
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
Note:
The CFDIU memorizes all manual programming so that at initialisation the last configuration
will be retained.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I
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24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
SYSTEM OPERATION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
DATA LOADING
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-45-25-00001506.0001001 / 10 JAN 11
Applicable to: ALL
With the data loading system, it is possible to upload databases and operational software, or to
download system reports from various onboard computers.
The data transfer is performed via 3.5 in disks and a portable data loader, or the aircraft fixed
Multipurpose Disk Drive Unit (MDDU).
DATA LOADING SELECTOR ON THE OVERHEAD PANEL
Ident.: DSC-45-25-00001507.0001001 / 19 DEC 12
Applicable to: ALL
When the data loading selector is ON, the 3 keys (NEXT, PREV, SEL CTRL) enable the display and
selection of various applicable aircraft systems (FMGC , TCAS etc...).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
DSC-45-25 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
DATA LOADING
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
PRINTER
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-45-30-00001508.0001001 / 21 MAR 16
Applicable to: ALL
The printer prints reports from the following systems (if installed) : ACARS , AIDS , FMGC , CFDIU
and EVMU. It prints these on paper, and does so either on the ground or in flight.
The printer is installed at the rear of the pedestal on the right side.
SYSTEM DESCRIPTION
Ident.: DSC-45-30-00001509.0001001 / 21 MAR 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
DSC-45-30 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
MAINTENANCE SYSTEM
A318/A319/A320/A321
PRINTER
FLIGHT CREW
OPERATING MANUAL
(1)
SLEW sw :
The SLEW switch is used to feed paper after having loaded a new roll.
(2)
PRINTER DOOR LATCH :
The printer door latch locks the door used for loading paper.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-45-30 P 2/2
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
Intentionally left blank
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-46-10 Datalink
DSC-46-10-10 General System Description
Overview.................................................................................................................................................................. A
Architecture.............................................................................................................................................................. B
Cockpit Interface......................................................................................................................................................C
DSC-46-10-20 AOC Applications
DSC-46-10-20-10 General
General.....................................................................................................................................................................A
DSC-46-10-40 Controls and Indicators
DSC-46-10-40-30 MCDU Datalink Pages
ATSU DATALINK.....................................................................................................................................................A
COMM MENU.......................................................................................................................................................... B
VHF3 SCAN SELECT............................................................................................................................................. C
DSC-46-10-40-40 MCDU Scratchpad Messages
MCDU Scratchpad Messages................................................................................................................................. A
DSC-46-10-40-60 ECAM
Memo Display.......................................................................................................................................................... A
DSC-46-10-50 How To
Introduction...............................................................................................................................................................A
How to Initialize....................................................................................................................................................... B
How to Modify FLT Plan......................................................................................................................................... C
DSC-46-20 Electronic Flight Bag (EFB)
DSC-46-20-20 Applications
Introduction...............................................................................................................................................................A
General.....................................................................................................................................................................B
Landing Application................................................................................................................................................. C
Takeoff Application.................................................................................................................................................. D
Loadsheet Application..............................................................................................................................................E
OPS Library Application...........................................................................................................................................F
Manager Application................................................................................................................................................G
DSC-46-30 Electronic QRH (eQRH)
General.....................................................................................................................................................................A
Continued on the following page
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-46-40 Pax Entertainment & Connectivity Systems (If Installed)
DSC-46-40-10 General
Continued from the previous page
General.....................................................................................................................................................................A
DSC-46-40-20 In Seat Power Supply System
IN SEAT POWER SUPPLY SYSTEM ........................................................................................................... A
DSC-46-40-30 Controls and Indicators
MOBILE COM PB-SW .................................................................................................................................. A
DISC IN PROG Light ..................................................................................................................................... B
CINS RESET PB ........................................................................................................................................... C
PAX COM PB-SW ..........................................................................................................................................D
PAX SYS PB-SW ...........................................................................................................................................E
PAX PERSONAL ELEC SPLY PB-SW .......................................................................................................... F
MEMO DISPLAY..................................................................................................................................................... G
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05 SEP 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATALINK - GENERAL SYSTEM DESCRIPTION
OVERVIEW
Ident.: DSC-46-10-10-00020333.0001001 / 17 MAR 17
Applicable to: ALL
The datalink has:
‐ AOC applications
L2
The flight crew uses the AOC applications to communicate with Airline Operational Center (AOC).
L1 ‐ ATC applications
L2
The flight crew uses the ATC applications to communicate with Air Traffic Control (ATC) centers.
L1
The ATC datalink provides communication, navigation, and surveillance for Air Traffic Management
(ATM) services.
The ATC datalink applications enable air traffic controllers to follow the aircraft navigation, and
enhance the air traffic flow.
The datalink communication (messages exchange) between the aircraft and the ground is achieved:
‐ Automatically (without a flight crew action)
‐ Manually (with a flight crew action via the DCDU /MCDU and/or RMP).
The datalink messages are:
‐ Uplink (from a ground facilities to the flight crew), or
‐ Downlink (from the flight crew to an ground facilities).
COMMUNICATION AND NAVIGATION FOR AIR TRAFFIC MANAGEMENT
L2
L1
L2
At the beginning of the flight, the flight crew sends a notification message to the ATC center, via
the MCDU, notification application .
Refer to DSC-46-10-30-10 Notification for more information.
Then, an air traffic controller will establish a connection between the aircraft and the ATC center.
As a result, the flight crew can exchange messages with the ATC center, via the DCDU (CPDLC
application ). The messages that the flight crew sends to the ATC center can be built with
present frames and modified via the MCDU.
Depending on the type of datalink exchange, the datalink uses one of the following communication
networks:
‐ ACARS (Refer to DSC-23-30-30-10 Introduction) for FANS A / FANS A+ applications
‐ ACARS Air Traffic Services (ATS 623) for optional applications
‐ Aeronautical Telecommunication Network (ATN) for FANS B / FANS B+ applications
The ATN supports increasing volume of ATC and AOC communication.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-46-10-10 P 1/6
22 MAR 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L1
DATALINK - GENERAL SYSTEM DESCRIPTION
FUTURE AIR NAVIGATION SYSTEM (FANS)
The ATC datalink provides:
‐ FANS A applications, for operations in remote and in oceanic areas:
▪ Notification
▪ Controller-Pilot Data Link Communication (CPDLC)
▪ Automatic Dependent Surveillance Contract (ADS-C).
‐ FANS B applications, for operations in high-density continental areas:
▪ Notification
▪ Controller-Pilot Data Link Communication (CPDLC).
‐ Optional applications (compatible only with FANS A+ or FANS B+):
▪ Departure Clearance
▪ Oceanic Clearance
▪ Digital - Automatic Terminal Information Service (D-ATIS).
NAVIGATION AND SURVEILLANCE FOR AIR TRAFFIC MANAGEMENT
The Automatic Dependent Surveillance (ADS ) system sends aircraft position and aircraft
navigation data to ATC centers and other aircraft.
L2
L1
L2
L1
L2
There are two different ADS applications:
‐ ADS-Contract (ADS-C)
The ADS-C automatically sends aircraft surveillance data to connected ATC centers via ATC
Datalink in remote or oceanic areas.
Refer to DSC-46-10-30-30 ADS-C for more information, about ADS-C application.
‐ ADS-Broadcast (ADS-B)
The ADS-B automatically broadcasts the aircraft position and navigation data to other users
(ATC centers or other aircraft) equipped with a Mode S transponder. The ATC Datalink
does not host the ADS-B .
Refer to DSC-34-SURV-10-10 ADS-B OUT for more information, about the ADS-B.
SERVICE PROVIDERS
The role of a communication service provider is to deliver a message from the A/C to a ground end
system and vice versa.
A datalink service provider ensures routing of datalink messages between the aircraft and ATC
center.
For VHF communication, the two main providers are ARINC and SITA that operate worldwide
networks.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
DSC-46-10-10 P 2/6
22 MAR 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L1
DATALINK - GENERAL SYSTEM DESCRIPTION
REVERSION TO VOICE COMMUNICATION
Voice communication is a primary means of communication on board.
The flight crew must revert from datalink communication to voice communication, if:
‐ There is an emergency situation (exchange of a critical or urgent message)
‐ There is a doubt about a datalink message, the voice should be used for clarification
‐ An operational timer of datalink message exchange times out
‐ A response to an ATC message was not correctly transmitted via datalink.
CLOCK ACCURACY
The required time precision for ATC datalink communications is +/-1 s UTC. If this constraint is
not respected, a rejection of datalink message or acceptance of obsolete datalink message may
occur.
Not respecting this constraint may lead to the rejection of messages or to the acceptance of
obsolete messages.
For FANS operations, the flight crew should not manually set the clock during cockpit preparation.
ARCHITECTURE
Applicable to: ALL
Ident.: DSC-46-10-10-10-00020329.0001001 / 17 MAR 17
AIR TRAFFIC SERVICE UNIT (ATSU)
The ATSU controls all datalink communication and automatically selects the best available
communication media:
‐ VHF
‐ HF
‐ SATCOM .
The ATSU hosts:
‐ AOC applications
‐ ATC applications
‐ Router services
The ATSU routers automatically select VHF frequency, depending on the aircraft position, in
accordance with an entered scan mask (airline policy).
The scan mask means that a list of VHF datalink service providers, selected via the VHF3
SCAN SELECT page, is scanned, in accordance with their priority level. The VHF scan mask is
compulsory for correct router operation. If there is no scan mask, the ECAM displays DATALINK
ATSU FAULT – ATSU INIT FAULT.
Refer to DSC-46-10-40-30 VHF3 SCAN SELECT for more information about the VHF3 SCAN
SELECT page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
DSC-46-10-10 P 3/6
22 MAR 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATALINK - GENERAL SYSTEM DESCRIPTION
Ident.: DSC-46-10-10-10-00020319.0001001 / 17 MAR 17
SATELLITE COMMUNICATIONS (SATCOM)
The SATCOM system provides voice and data services. The voice/data are transmitted via
satellite, from the aircraft to the ground earth stations, and then switched through international
telecommunications networks (ARINC, SITA, etc.) to anywhere in the world (airline operational
centers, ATC centers, etc).
The ATSU (router) manages switching to/from SATCOM (ACARS environments only).
Ident.: DSC-46-10-10-10-00020321.0002001 / 17 MAR 17
VERY HIGH FREQUENCY (VHF)
The communication between the aircraft and VHF ground stations is established on a VHF
frequency. The datalink system primarily uses the VHF 3 radio communication system. The ATSU
router automatically selects a VHF frequency, depending on entered configuration, the scan mask
for VHF DataLink (VDL), and the aircraft position.
VHF data link service providers are available in each geographical area. Refer to
DSC-23-30-30-40 World Map ACARS Frequencies for a world map of VHF ACARS frequencies.
The VHF3 radio communication system has:
‐ Data mode
‐ Voice mode.
DATALINK/VOICE SWITCHING
The VHF 3 can be used in the voice mode, in case of:
‐ VHF 1 failure
‐ VHF 2 failure
‐ Specific AOC functions (operator's customization).
The flight crew can switch datalink/voice via the RMP , or via VHF3 VOICE DIRECTORY page
of the MCDU.
The voice frequency can be tuned by:
‐ ATSU automatically
‐ Fight crew, via the RMP.
Green HF VOICE memo indicates that VHF 3 datalink communication is interrupted, when the
VHF 3 transceiver operates in the voice mode.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-46-10-10 P 4/6
22 MAR 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATALINK - GENERAL SYSTEM DESCRIPTION
COCKPIT INTERFACE
Ident.: DSC-46-10-10-00020373.0001001 / 17 MAR 17
Applicable to: ALL
The cockpit interface of the datalink system has:
‐ Datalink Control and Display Unit (DCDU) on the CAPT and F/O side
The DCDU displays the uplink and downlink messages and enable the flight crew to control the
datalink message exchange.
‐ ATC MSG pb-sw on the CAPT and F/O side of the glareshield
The ATC MSG pb-sw alerts when an uplink message is received and enables the flight crew to
cancel the alert.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
DSC-46-10-10 P 5/6
22 MAR 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATALINK - GENERAL SYSTEM DESCRIPTION
‐ Multipurpose Control and Display Unit (MCDU)
The MCDU enables to manage AOC and ATC functions and data transfer to the DCDU
‐ Printer
Datalink messages can be printed, when displayed on the DCDU.
‐ RMP
The RMP enables frequency tuning.
‐ ECAM
The ECAM informs about the abnormal operation.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
DSC-46-10-10 P 6/6
22 MAR 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATALINK - AOC APPLICATIONS
General
GENERAL
Ident.: DSC-46-10-20-10-00020385.0001001 / 17 MAR 17
Applicable to: ALL
The AOC applications are datalink applications. The AOC applications enable an exchange of
specific messages between the flight crew and the Airline Operational Control (AOC).
The AOC applications are customized by each operator and depend on operator's choices and the
datalink service provider.
Note:
Details about AOC applications cannot be provided due to the wide range of customization
by the operator.
Airbus does not supervise customization of AOC applications. It is recommended to insert
AOC application description into this chapter in accordance with AOC applications installed
on the aircraft.
The AOC applications can offer the following functions:
EXAMPLE
‐ Preflight Functions:
‐ Flight log
‐ Departure Delay Message
‐ Takeoff Delay Message
‐ Weather Request
‐ NOTAM Request
‐ Loadsheet Request
‐ Others
‐ En-Route Functions:
‐ Flight log
‐ Diversion Message
‐ En-route Delay
‐ Estimated Time of Arrival (ETA) Message
‐ Weather Request
‐ NOTAM Request
‐ Others
‐ Postflight Functions:
‐ Flight log
‐ Flight summary
‐ Gate delay
‐ Others
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATALINK - AOC APPLICATIONS
The flight crew uses the datalink cockpit interface for the AOC applications.
EXAMPLE
Flight Plan Modification
This flight plan modification example is based on following assumptions:
‐ The AOC sends a flight plan modification message to the flight crew.
‐ The flight crew loads the fight plan modification in the FMGS , into the secondary
F-PLN.
‐ The crew obtains ATC clearance before activating the modified flight plan.
‐ Refer to DSC-46-10-50 How to Modify FLT Plan for the flight plan modification
based on an AOC request.
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DSC-46-10-20-10 P 2/2
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
DATALINK - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
MCDU Datalink Pages
ATSU DATALINK
Ident.: DSC-46-10-40-30-00021081.0003001 / 17 MAR 17
Applicable to: ALL
[1R] AOC MENU
[6R] COMM
When selected, the MCDU displays the AOC MENU page.
When selected, the MCDU displays the COMM MENU page.
COMM MENU
Ident.: DSC-46-10-40-30-00021090.0003001 / 17 MAR 17
Applicable to: ALL
EXAMPLE
This is an example of the COMM MENU page. Information, that are displayed on the
COMM MENU page and subsequent pages, accessible via the COMM MENU page,
depend on datalink customization, selected by each operator for AOC applications.
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AIRCRAFT SYSTEMS
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DATALINK - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
EXAMPLE
[1L] COMM INIT
When selected, the DCDU displays the COMM INIT
page.
[2L] VHF3 DATA MODE
When selected, the DCDU displays the VHF3 DATA
MODE page.
[3L] VHF3 VOICE
When selected, the DCDU displays the VHF3 VOICE
DIRECTORY
DIRECTORY page.
[6L] RETURN TO ATSU DLKWhen selected, the MCDU displays the ATSU
DATALINK page.
[1R] COMM STATUS
When selected, the DCDU displays the COMM
STATUS page.
When selected, the DCDU displays the COMM
[2R] COMPANY CALL
CONFIG page.
[4R] MAINTENANCE
When selected, the MCDU displays the
MAINTENANCE page.
[6R] AUTO PRINT
Sets the auto-print on or off.
VHF3 SCAN SELECT
Ident.: DSC-46-10-40-30-00021254.0001001 / 17 MAR 17
Applicable to: ALL
EXAMPLE
This is an example of VHF3 SCAN SELECT pages. Information, that are displayed
on the VHF3 SCAN SELECT pages, depend on datalink customization, selected by
each operator.
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DSC-46-10-40-30 P 2/6
22 MAR 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATALINK - CONTROLS AND INDICATORS
THE VHF 3 SCAN SELECT PAGE 1/4
EXAMPLE
[1L] SITA EUR/AF
[5L]:
NEW SCAN SELECT :
ACTIVE SEL DISPLAY :
Selects the SITA Europe/Africa (datalink service
provider).
Selects the scan mask.
Displays the scan mask used by ATSU.
[6L] RETURN
When selected, the MCDU displays the COMM
CONFIG page.
Selects the ARINC Europe (datalink service
[1R] ARINC EUROPE
provider).
[2R] ARINC MIDDLE EAST Selects the ARINC Eiddle East (datalink service
provider).
[3R] ARINC INDIA
Selects the ARINC India (datalink service provider).
[5R] EMPTY SCAN
Activates an emprty scan mask to inhibit VHF
ACTIVATE
datalink communication.
[6R] SCAN SEL PRINT
When selected, the printer prints information.
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
DATALINK - CONTROLS AND INDICATORS
THE VHF 3 SCAN SELECT PAGE 2/4
EXAMPLE
[1L] SITA PACIFIC
[4L] AVICOM JAPAN
[5L]:
NEW SCAN SELECT :
ACTIVE SEL DISPLAY :
[6L] RETURN
[1R] ARINC RUSSIA
[2R] ARINC ASIA
[3R] ARINC AUSTRAL
[4R] ARINC KOREA
[5R] EMPTY SCAN
ACTIVATE
[6R] SCAN SEL PRINT
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Selects the SITA Pacific (datalink service provider).
Selects the AVCOM Japan (datalink service
provider).
Selects the scan mask.
Displays the scan mask used by ATSU.
When selected, the MCDU displays the COMM
CONFIG page.
Selects the ARINC Russia (datalink service
provider).
Selects the ARINC Asia (datalink service provider).
Selects the ARINC Australia (datalink service
provider).
Selects the ARINC Korea (datalink service provider).
Activates an emprty scan mask, in order to inhibit
VHF datalink communication.
When selected, the printer prints information.
←C→
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DATALINK - CONTROLS AND INDICATORS
THE VHF 3 SCAN SELECT PAGE 3/4
EXAMPLE
[1L] SITA NORTH AM
[2L] SITA SOUTH AM
[3L] DEPV BRASIL
[5L]:
NEW SCAN SELECT :
ACTIVE SEL DISPLAY :
[6L] RETURN
[1R] ARINC AMERICA
[5R] EMPTY SCAN
ACTIVATE
[6R] SCAN SEL PRINT
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Selects the SITA North America (datalink service
provider).
Selects the SITA South America (datalink service
provider).
Selects the DEPV Brasil (datalink service provider).
Selects the scan mask.
Displays the scan mask used by ATSU.
When selected, the MCDU displays the COMM
CONFIG page.
Selects the ARINC America (datalink service
provider).
Activates an emprty scan mask, in order to inhibit
VHF datalink communication.
When selected, the printer prints information.
←C→
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
DATALINK - CONTROLS AND INDICATORS
THE VHF 3 SCAN SELECT PAGE 4/4
EXAMPLE
[5L]:
NEW SCAN SELECT :
ACTIVE SEL DISPLAY :
Selects the scan mask.
Displays the scan mask used by ATSU.
[6L] RETURN
When selected, the MCDU displays the COMM
CONFIG page.
[1R] OLD ARINC EUROPE Selects the OLD ARINC Europe (datalink service
provider).
Selects the ARINC Africa (datalink service provider).
[2R] ARINC AFRICA
[3R] JACARS AUSTRAL Selects the JACARS Australia (datalink service
provider).
[5R] EMPTY SCAN
Activates an emprty scan mask, in order to inhibit
ACTIVATE
VHF datalink communication.
When selected, the printer prints information.
[6R] SCAN SEL PRINT
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AIRCRAFT SYSTEMS
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A318/A319/A320/A321
DATALINK - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
MCDU Scratchpad Messages
MCDU SCRATCHPAD MESSAGES
Applicable to: ALL
Ident.: DSC-46-10-40-40-10-00021338.0001001 / 17 MAR 17
SCRATCHPAD MESSAGES ON THE COMM MENU PAGE
MESSAGE
COMMAND NOT AVAIL
DEFAULT VHF SP LIST
ENTER A/C REGISTR
ENTER A/L ID
ENTER VHF 3 SCAN MASK
FAILED COMMAND
FORMAT ERROR
NOT ALLOWED
PRINT FAILED
PRT MSG PRINT FAIL
VHF 3 CAN BE SET IN VOICE
VHF 3 SWITCH IMPOSSIBLE
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CONDITIONS
The command is not available.
The new SCAN MASK is not available.
The system displays the default SCAN MASK instead.
The aircraft registration number is not valid.
To enter this parameter, Refer to DSC-46-10-50 How to
Initialize.
The airline identification number is not valid.
To enter this parameter, Refer to DSC-46-10-50 How to
Initialize.
No service provider has been selected.
The command, selected by the flight crew, cannot currently
be performed.
The message was entered in an inappropriate format.
It is not permitted to press this key.
A print command is not successful.
Automatic print of an AOC uplink message was not
successful.
VHF 3 datalink communications are lost.
However, VHF 3 can be used in voice mode.
It is not possible to switch from VHF 3 voice mode to VHF 3
data mode.
A
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AIRCRAFT SYSTEMS
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DATALINK - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
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DATALINK - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
ECAM
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-46-10-40-60-A-00016906.0001001 / 21 MAR 16
COMPANY ALERT :
This memo appears in green when the aircraft receives an uplink alert
message, or when an AOC special condition requires a pilot action on the
MCDU (depends on AOC programming). This memo pulses green for 180 s,
then remains steady. It is associated with a buzzer for 1 s.
Ident.: DSC-46-10-40-60-A-00016904.0001001 / 21 MAR 16
COMPANY CALL :
This memo appears in green when the aircraft receives a message from the
ground requesting voice communication on VHF.
Ident.: DSC-46-10-40-60-A-00016903.0001001 / 21 MAR 16
COMPANY DATALINK STBY :
This memo appears in green when AOC datalink air-ground
communication is temporarily unavailable, but not lost.
Ident.: DSC-46-10-40-60-A-00016905.0001001 / 21 MAR 16
COMPANY MSG
:
This memo appears in green when the aircraft receives a message from the
ground.
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
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DATALINK - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
DATALINK - HOW TO
FLIGHT CREW
OPERATING MANUAL
INTRODUCTION
Ident.: DSC-46-10-50-00021191.0002001 / 17 MAR 17
Applicable to: ALL
How To chapter contains examples of:
‐ How to initialize the datalink
‐ How to modify the flight plan.
Illustrations in How To are generic and do not reflect differences depending on the datalink standard
installed in the aircraft.
HOW TO INITIALIZE
Ident.: DSC-46-10-50-00021142.0002001 / 17 MAR 17
Applicable to: ALL
Datalink may be initialized:
‐ Automatically
Datalink initializes automatically, provided that a list of service providers is scanned, and all
required parameters are received, and validated by the ATSU.
‐ Manually
Datalink may be initialized manually, when the system is not correctly initialized automatically.
The VHF3 SCAN SELECT page of the MCDU displays the list of service providers.
The COMM CONFIG / COMM INIT page, on the MCDU displays required parameters.
MANUAL INITIALIZATION
If one of required parameters is not valid, one or more manual entries may be required:
If ARN is not valid:
The MCDU scratchpad displays ENTER A/C REGISTER:
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DSC-46-10-50 P 1/8
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AIRCRAFT SYSTEMS
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DATALINK - HOW TO
FLIGHT CREW
OPERATING MANUAL
The flight crew clears the scratchpad, and inserts the A/C registration via the MCDU scratchpad.
A/C REGISTR..................................................................................................................... INSERT
The flight crew inserts A/C ICAO registration via the MCDU scratchpad to A/C REGISTR.
CONFIG ACTIVATE........................................................................................................... SELECT
The flight crew selects 1R/CONFIG ACTIVATE to activate manual entry of the A/C registration.
If the A/L ID is not valid:
The MCDU scratchpad displays ENTER A/L IDENT:
The flight crew clears the scratchpad, and inserts the two-letter A/L ID code via the MCDU
scratchpad.
A/L ID.................................................................................................................................. INSERT
The flight crew inserts A/L ID code via the MCDU scratchpad to A/L ID.
CONFIG ACTIVATE........................................................................................................... SELECT
The flight crew selects 1R/CONFIG ACTIVATE to activate manual entry of the A/C registration.
If VHF service provider is not selected
and
if the VHF3 SCAN/MASK SELECT menu can be accessed:
The MCDU scratchpad displays ENTER VHF3 SCAN SELECT:
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
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DATALINK - HOW TO
FLIGHT CREW
OPERATING MANUAL
On the VHF3 SCAN SELECT page, select service providers, in the airline priority order, and
activate the VHF SCAN SELECT function.
EXAMPLE OF SELECTION OF DATALINK SERVICE PROVIDERS:
Selection of SITA 725 and ARINC service providers :
1. Press 5L key: The asterisk next to SELECT indication disappears, then reappears.
2. Press 1L key to select SITA 725: SELECT indication goes off, and the priority number of
selection 1 appears.
3. Press 1R key to select ARINC: SELECT indication goes off, and the priority number of
selection 2 appears.
4. Press 5R key to activate the VHF SCAN SELECT function: The star next to SCAN SELECT
ACTIVATE indication disappears, then reappears.
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
DATALINK - HOW TO
FLIGHT CREW
OPERATING MANUAL
Note:
Modification of the SCAN SELECT setting may result in the loss of air-ground VHF
datalink communication, and the increase of datalink service provider charges.
Therefore, the SCAN SELECT setting should not be modified by the flight crew, unless
the flight crew is instructed to do so.
HOW TO MODIFY FLT PLAN
Ident.: DSC-46-10-50-00021153.0001001 / 21 MAR 17
Applicable to: ALL
When the scratchpad (1) displays the AOC SEC F-PLN UPLINK message:
On the MCDU:
SEC INDEX Page:
L2
L1
AOC F-PLN INSERT...................................................................................... SELECT See (2)
The flight plan is inserted in the secondary F-PLN See (3).
The flight can review and modify the flight plan.
SEC F-PLN REQ DISPLAY............................................................................SELECT See (4)
The DCDU automatically displays a datalink message See (5).
The flight crew sends the message to the ATC from the DCDU.
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AIRCRAFT SYSTEMS
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DATALINK - HOW TO
FLIGHT CREW
OPERATING MANUAL
When ATC clearance is received:
On the glareshield:
ATC MSG pb................................................................................................................. PRESS
The aural and visual alerts stop.
L2
L1
L2
L1
L2
On the DCDU:
STBY.............................................................................................................. SELECT See (1)
The message status changes to STBY on a blue background See (2).
SEND..............................................................................................................SELECT See (3)
The background color of the STBY message status changes to green.
LOAD.............................................................................................................. SELECT See (4)
LOAD must be selected. Other selection may prevent loading of the clearance.
The LOAD SEC OK displays in the information field of the DCDU, if loading is successful.
The flight crew can review the clearance on the MCDU , in SEC F-PLN pages.
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AIRCRAFT SYSTEMS
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DATALINK - HOW TO
FLIGHT CREW
OPERATING MANUAL
L1
If the flight crew accepts the clearance:
WILCO......................................................................................................SELECT See (5)
The flight crew can activate the secondary F-PLN.
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AIRCRAFT SYSTEMS
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DATALINK - HOW TO
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OPERATING MANUAL
If the flight crew decides to modify the clearance:
• The flight crew loads the clearance into the SEC F-PLN , on the MCDU and modifies
it.
• The flight crew rejects the clearance by selecting UNABLE on the DCDU.
• The flight crew sends a new request (with the modified F-PLN ) to the ATC.
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DATALINK - HOW TO
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
ELECTRONIC FLIGHT BAG (EFB) - APPLICATIONS
INTRODUCTION
Ident.: DSC-46-20-20-00021223.0001001 / 25 JUL 17
Applicable to: ALL
The FlySmart with Airbus application suite is composed of:
‐ TAKEOFF application
‐ LANDING application
‐ LOADSHEET application
‐ IN–FLIGHT application (available on the latest FlySmart with Airbus applications for Windows
version)
‐ Operational Documentation applications (OLB)
‐ Manager application (available for iPad version).
The FlySmart with Airbus application suite is designed to:
‐ Improve access to flight crew’s operational information
‐ Reduce the quantity of paper documents in the cockpit by replacing them with electronic
documents
‐ Enable reduced revision and distribution cycles to ensure better technical data accuracy
‐ Ease and improve the operational data updating process
‐ Provide an accurate and optimized computation of performance.
The FlySmart with Airbus application suite can be used by the flight crew on a Portable Electronic
Device (PED ). The flight crew can use the power outlets (110 VAC / 60 Hz) installed on each
lateral console to plug their PED.
Note:
The power outlets (115 VAC / 400 Hz) located on the rear of the cockpit are for
maintenance use only.
GENERAL
Ident.: DSC-46-20-20-00021224.0001001 / 20 MAR 17
Applicable to: ALL
The My Flight page enables:
‐ To check that FlySmart with Airbus applications are up to date. The My Flight page provides the
version of the installed applications and data (EFB version)
‐ To start the Manager application, that enables to update the operational data (performance,
manuals)
‐ To initialize the applications with the applicable aircraft tail number, flight number and citypair. This
avoids multiple entries of the same data in the different applications.
There is one My Flight page per application. All the inputs that the user has entered on one My Flight
page are retrieved by the other applications.
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AIRCRAFT SYSTEMS
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ELECTRONIC FLIGHT BAG (EFB) - APPLICATIONS
FLIGHT CREW
OPERATING MANUAL
Note:
On the My Flight page of OLB application, the user can only enter the a/c type and a/c
registration.
LANDING APPLICATION
Ident.: DSC-46-20-20-00021225.0001001 / 20 MAR 17
Applicable to: ALL
The Landing application aims at computing the landing performance data (maximum landing weight,
approach speed) according to the aircraft configuration and external conditions (runway, surrounding
obstacles, weather).
The Landing application allows straightforward computations and provides the optimized landing
performance for the given conditions.
TAKEOFF APPLICATION
Ident.: DSC-46-20-20-00021226.0001001 / 20 MAR 17
Applicable to: ALL
The Takeoff application aims at computing the takeoff performance data (maximum takeoff weight,
takeoff speeds, flexible temperature) according to the aircraft configuration and external conditions
(runway, surrounding obstacles, weather).
The Takeoff application allows straightforward computations and provides the optimized takeoff
performance for the given conditions.
LOADSHEET APPLICATION
Ident.: DSC-46-20-20-00021227.0001001 / 20 MAR 17
Applicable to: ALL
The Loadsheet application allows the flight crew users to prepare the aircraft loading and to
check that all weights and CG remain within the loading operational envelope. This eases the
computation of the ZFWCG , ZFW , TOW and TOCG, and enables last–minute changes to the
passenger/cargo/fuel distribution.
Depending on airline’s authority requirements, the Loadsheet application can also generate a load
and trim sheet.
OPS LIBRARY APPLICATION
Ident.: DSC-46-20-20-00021228.0001001 / 20 MAR 17
Applicable to: ALL
The OLB application enables the onboard consultation of any flight operations document published
in the relevant format (e.g. airline's manuals), including the ones delivered by Airbus (FCOM , MEL ,
AFM , CDL , FCTM).
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AIRCRAFT SYSTEMS
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ELECTRONIC FLIGHT BAG (EFB) - APPLICATIONS
FLIGHT CREW
OPERATING MANUAL
MEL and CDL items (including missing items) selected on OLB application are automatically
transferred to Takeoff and Landing applications.
MANAGER APPLICATION
Ident.: DSC-46-20-20-00021229.0001001 / 20 MAR 17
Applicable to: ALL
The Manager application aims at updating on the iPad the operational data used by FlySmart with
Airbus applications for iPad: performance data and operational manuals.
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
ELECTRONIC FLIGHT BAG (EFB) - APPLICATIONS
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ELECTRONIC QRH (EQRH)
GENERAL
Ident.: DSC-46-30-00021515.0001001 / 17 MAR 17
Applicable to: ALL
The electronic QRH (eQRH ) is an EFB application that enables the flight crew to:
‐ Manage the Normal Checklists and some Abnormal Procedures
‐ Access to some important operational data (OEBs, system architectures, performance…)
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AIRCRAFT SYSTEMS
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OPERATING MANUAL
ELECTRONIC QRH (EQRH)
The eQRH has several main interfaces:
‐ My Aircraft page:
The My Aircraft page enables:
‐ To check that the eQRH application is up to date. The My Aircraft page provides the version of
the installed application and data (EFB version)
‐ To initialize the eQRH application with the applicable aircraft tail number. The My Aircraft page
retrieves automatically the aircraft tail number when defined in other FlySmart with Airbus
applications
‐ EFB version:
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AIRCRAFT SYSTEMS
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OPERATING MANUAL
ELECTRONIC QRH (EQRH)
If required, each flight crew member compares the EFB version with the valid version information
that is given as reference by the airline. This ensures that the eQRH application and the data
installed on their devices correspond to the latest updated version, provided by their airline's flight
operations.
‐ eQRH application:
The eQRH application enables the pilot to manage the normal checklists and non-sensed
Abnormal Procedures. It also gives access to some important operational data that may be
required during the flight.
(1)
(2)
(3)
Access to My Aircraft page
Aircraft tail number and type
Working list
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AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
(4)
(5)
(6)
(7)
ELECTRONIC QRH (EQRH)
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GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-46-30 P 4/4
22 MAR 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
PAX ENTERTAINMENT & CONNECTIVITY
SYSTEMS (IF INSTALLED) - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-46-40-10-00017604.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft is equipped with cabin connectivity systems which enable passengers to use:
‐ Mobile phones for voice and data services, and/or
‐ Internet wireless connection for access to the World Wide Web
The use of mobile phones is prohibited in cockpit and lavatories.
The following table provides the list of controls dedicated to Pax Entertainment & Connectivity
Systems:
P/B
GALLEY
COMMERCIAL
NO PED
PAX SYS
EQUIPMENTS (FUNCTIONS)
Mobile, Wifi, IFE
Mobile, Wifi, IFE
Signs
Mobile, Wifi, IFE, Seat actuators, PED
DESCRIPTIONS
Refer to DSC-24-20 Overhead Panel
Refer to DSC-24-20 Overhead Panel
Refer to DSC-33-40-10 Overhead Panel
Refer to DSC-46-40-30 PAX SYS PB-SW
Refer to DSC-46-40-30 PAX PERSONAL ELEC
PAX PERSONAL ELEC SPLY Mobile, Wifi, IFE, Seat actuators, PED
SPLY PB-SW
MOBILE COM
Mobile, Wifi
Refer to DSC-46-40-30 MOBILE COM PB-SW
CINS reset
Mobile, Wifi
Refer to DSC-46-40-30 CINS RESET PB
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-46-40-10 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
PAX ENTERTAINMENT & CONNECTIVITY
SYSTEMS (IF INSTALLED) - GENERAL
FLIGHT CREW
OPERATING MANUAL
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GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-46-40-10 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
PAX ENTERTAINMENT & CONNECTIVITY SYSTEMS
(IF INSTALLED) - IN SEAT POWER SUPPLY SYSTEM
FLIGHT CREW
OPERATING MANUAL
IN SEAT POWER SUPPLY SYSTEM
Ident.: DSC-46-40-20-00017606.0001001 / 10 NOV 15
Applicable to: ALL
The In-Seat Power Supply System (ISPSS ) provides electrical power to the In-Seat Power Supply
Unit (ISPSU) outlets, and enables passengers to use Portable Electronic Devices (PED) and the
In-Flight Entertainment (IFE) system.
It is possible for the flight crew to simultaneously disconnect power from all ISPSUs, In-Flight
Entertainment (IFE) and Cabin Connectivity systems, via the PAX SYS pb-sw or the PAX
PERSONAL ELEC SPLY pb-sw.
In the case of rapid cabin decompression, both the ISPSS and IFE system are automatically
disconnected.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-46-40-20 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PAX ENTERTAINMENT & CONNECTIVITY SYSTEMS
(IF INSTALLED) - IN SEAT POWER SUPPLY SYSTEM
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-46-40-20 P 2/2
24 JAN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
PAX ENTERTAINMENT & CONNECTIVITY SYSTEMS
(IF INSTALLED) - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
MOBILE COM PB-SW
Ident.: DSC-46-40-30-00017631.0001001 / 19 APR 16
Applicable to: ALL
The pushbutton-switch described here below is installed on the 45 VU panel on the overhead panel.
ON
OFF
Note:
:
:
The mobile phone system is activated.
The mobile phone system is deactivated.
When the pushbutton is released, the OFF light comes on in white however the system
takes approximately 4 min to disconnect. During this disconnection process, the
passengers can use their mobile phones.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-46-40-30 P 1/8
19 JUN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
PAX ENTERTAINMENT & CONNECTIVITY SYSTEMS
(IF INSTALLED) - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
DISC IN PROG LIGHT
Ident.: DSC-46-40-30-00019278.0001001 / 21 MAR 17
Applicable to: ALL
The pushbutton-switch described here below is installed on the 45 VU panel on the overhead panel.
Note:
After the release of Mobile Com pushbutton, the DISC IN PROG light comes in blue and
remains on until the total disconnection of the system.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
DSC-46-40-30 P 2/8
19 JUN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PAX ENTERTAINMENT & CONNECTIVITY SYSTEMS
(IF INSTALLED) - CONTROLS AND INDICATORS
CINS RESET PB
Ident.: DSC-46-40-30-00017630.0001001 / 10 NOV 15
Applicable to: ALL
The pushbutton-switch described here below is installed on the 45 VU panel on the overhead panel.
When pressed, it resets all Cabin Connectivity systems.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
DSC-46-40-30 P 3/8
19 JUN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PAX ENTERTAINMENT & CONNECTIVITY SYSTEMS
(IF INSTALLED) - CONTROLS AND INDICATORS
PAX COM PB-SW
Ident.: DSC-46-40-30-00021654.0001001 / 02 MAY 17
Applicable to: ALL
The pushbutton-switch described here below is installed on the 45 VU panel on the overhead panel.
OFF
:
The Cabin Connectivity system is cut-off. When the pushbutton-switch is
released, the OFF light comes on in white.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
DSC-46-40-30 P 4/8
19 JUN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PAX ENTERTAINMENT & CONNECTIVITY SYSTEMS
(IF INSTALLED) - CONTROLS AND INDICATORS
PAX SYS PB-SW
Ident.: DSC-46-40-30-00017735.0001001 / 10 NOV 15
Applicable to: ALL
The pushbutton-switch described here below is installed on the 56VU panel on the overhead panel.
AUTO
:
OFF
:
All ISPSUs, In-Flight Entertainment (IFE) and Cabin Connectivity systems are
powered.
Simultaneously turns off all ISPSUs, In-Flight Entertainment (IFE) and Cabin
Connectivity systems.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
DSC-46-40-30 P 5/8
19 JUN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
PAX ENTERTAINMENT & CONNECTIVITY SYSTEMS
(IF INSTALLED) - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
PAX PERSONAL ELEC SPLY PB-SW
Ident.: DSC-46-40-30-00017629.0001001 / 21 MAR 17
Applicable to: ALL
The pushbutton-switch described here below is installed on the 56VU panel on the overhead panel.
AUTO
:
OFF
:
INOP
:
All ISPSUs, In-Flight Entertainment (IFE) and Cabin Connectivity systems are
powered, if the pushbutton-switch located in the forward cabin is also in the on
position
Simultaneously turns off all ISPSUs, In-Flight Entertainment (IFE) system and
Cabin Connectivity systems.
This label indicates that the ISPSS has been deactivated and is inoperative.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
DSC-46-40-30 P 6/8
19 JUN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
PAX ENTERTAINMENT & CONNECTIVITY SYSTEMS
(IF INSTALLED) - CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
MEMO DISPLAY
Ident.: DSC-46-40-30-00017628.0001001 / 10 NOV 15
Applicable to: ALL
“GSM DISC < 4 MN”
:
This memo appears in green, if the cockpit switch “Mobile Com” is
pushed. It initiates a shutdown of the Cabin Connectivity systems within
4 minutes. The message disappears when the shutdown is completed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
DSC-46-40-30 P 7/8
19 JUN 17
AIRCRAFT SYSTEMS
INFORMATION SYSTEMS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PAX ENTERTAINMENT & CONNECTIVITY SYSTEMS
(IF INSTALLED) - CONTROLS AND INDICATORS
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GLG A318/A319/A320/A321 For A/C: HC-CRU
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19 JUN 17
AIRCRAFT SYSTEMS
APU
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AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-49-10 Description
DSC-49-10-10 General
General.....................................................................................................................................................................A
DSC-49-10-20 Main Components
APU Engine............................................................................................................................................................. A
Electronic Control Box............................................................................................................................................. B
Air Intake System.................................................................................................................................................... C
Starter...................................................................................................................................................................... D
Fuel System............................................................................................................................................................. E
Oil System................................................................................................................................................................F
Inlet Guide Vanes (IGV)..........................................................................................................................................G
Air Bleed System.....................................................................................................................................................H
Controls..................................................................................................................................................................... I
Ground Operation Safety Devices........................................................................................................................... J
DSC-49-20 Controls and Indicators
Overhead Panel....................................................................................................................................................... A
External Controls..................................................................................................................................................... B
ECAM APU Page.................................................................................................................................................... C
Memo Display.......................................................................................................................................................... D
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-49-PLP-TOC P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-49-PLP-TOC P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - GENERAL
GENERAL
Applicable to: ALL
Ident.: DSC-49-10-10-A-00017436.0001001 / 21 MAR 17
The Auxiliary Power Unit (APU) is a self-contained unit that supplies the aircraft with pneumatic and
electrical power.
On the ground
‐ It supplies bleed air for starting the engines and for the air conditioning system
‐ It supplies electrical power to the electrical system.
During takeoff
‐ It supplies bleed air for air conditioning (for example, when optimum aircraft performance is
required).
In flight
‐ It backs up the electrical system
‐ It backs up the air conditioning
‐ It can be used to start the engines.
The APU may obtain power for starting from the aircraft's batteries or normal electrical system, or
from ground service.
APU starting is permitted throughout the normal flight envelope (Refer to LIM-APU Operational
Envelope).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-49-10-10 P 1/2
22 MAR 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - GENERAL
Ident.: DSC-49-10-10-A-00017437.0002001 / 21 MAR 16
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-49-10-10 P 2/2
22 MAR 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
DESCRIPTION - MAIN COMPONENTS
FLIGHT CREW
OPERATING MANUAL
APU ENGINE
Ident.: DSC-49-10-20-00001528.0001001 / 21 MAR 16
Applicable to: ALL
The basic element of the APU is a single-shaft gas turbine that delivers mechanical shaft power for
driving the accessory gearbox (electrical generator, starter, etc.) and produces bleed air (engine
starting and pneumatic supply).
ELECTRONIC CONTROL BOX
Ident.: DSC-49-10-20-00001529.0001001 / 21 MAR 16
Applicable to: ALL
The Electronic Control Box (ECB ) is a full-authority digital electronic controller that performs the bulk
of the APU system logic for all modes of engine operation, such as :
‐ Sequences the start and monitors it.
‐ Monitors speed and temperature.
‐ Monitors bleed air.
‐ Sequences the shutdown.
‐ Controls the automatic shutdown.
AIR INTAKE SYSTEM
Ident.: DSC-49-10-20-00001530.0001001 / 21 MAR 16
Applicable to: ALL
The air intake and an electrically operated flap allow external air to reach the compressor inlet.
STARTER
Ident.: DSC-49-10-20-00001531.0001001 / 21 MAR 16
Applicable to: ALL
The ECB controls the electric starter. The starter engages if the air intake is fully open and the
MASTER SW and the START pushbutton are ON.
FUEL SYSTEM
Ident.: DSC-49-10-20-00001532.0001001 / 21 MAR 16
Applicable to: ALL
The left fuel feed line supplies the APU.
The required pressure is normally available from tank pumps.
If pressure is not available (batteries only or pumps off) the APU FUEL PUMP starts automatically.
The ECB controls the fuel flow.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to E
DSC-49-10-20 P 1/4
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
DESCRIPTION - MAIN COMPONENTS
FLIGHT CREW
OPERATING MANUAL
OIL SYSTEM
Ident.: DSC-49-10-20-00001533.0001001 / 21 MAR 16
Applicable to: ALL
The APU has an integral independent lubrication system (for lubrication and cooling).
INLET GUIDE VANES (IGV)
Ident.: DSC-49-10-20-00001534.0001001 / 21 MAR 16
Applicable to: ALL
The IGVs control bleed air flow, and a fuel-pressure-powered actuator positions the IGVs.
The ECB controls the actuator in response to aircraft demand.
AIR BLEED SYSTEM
Ident.: DSC-49-10-20-00001535.0002001 / 03 FEB 11
Applicable to: ALL
The air bleed system is fully automatic.
The APU speed is always 100 % whatever the air bleed system demand and the ground/flight
configuration are.
CONTROLS
Ident.: DSC-49-10-20-00001536.0001001 / 21 MAR 16
Applicable to: ALL
The flight crew uses the controls on the APU panel for routine shutdown. For emergency shutdown :
‐ the flight crew can push the APU FIRE handle, or
‐ the ground crew can push the APU SHUT OFF pushbutton on the interphone panel under the
nose fuselage.
GROUND OPERATION SAFETY DEVICES
Ident.: DSC-49-10-20-00001537.0001001 / 21 MAR 16
Applicable to: ALL
The APU may run without cockpit crew supervision when the aircraft is on the ground. In case of fire
in the APU compartment :
‐ APU fire warnings operate in the cockpit.
‐ A horn in the nose gear bay sounds.
‐ The AVAIL light goes out.
‐ The FAULT light in the MASTER SW lights up.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F to J →
DSC-49-10-20 P 2/4
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - MAIN COMPONENTS
‐ The APU shuts down.
‐ The APU fire extinguisher discharges.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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DSC-49-10-20 P 3/4
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
DESCRIPTION - MAIN COMPONENTS
FLIGHT CREW
OPERATING MANUAL
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GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-49-10-20 P 4/4
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
OVERHEAD PANEL
Applicable to: ALL
Ident.: DSC-49-20-A-00017438.0001001 / 21 MAR 16
Ident.: DSC-49-20-A-00017685.0003001 / 21 MAR 16
(1) MASTER SW pb-sw
This switch controls the electric power supply for the operation of the APU and its protective features.
It also controls the starting and shutdown sequences.
ON
: The blue ON light comes on.
Electric power goes to the APU system; the ECB performs a power-up test.
The APU air intake flap opens.
The APU fuel isolation valve opens.
If no fuel tank pump is running, the APU fuel pump operates.
If the aircraft has ground power or main generator power, the APU page appears on
the ECAM display.
OFF
: Manual shutdown sequence.
‐ The ON light on the MASTER SW pb-sw, and the AVAIL light on the START pb go
out.
‐ If the aircraft was using APU bleed air, the APU keeps running for a cooling period
of 60 to 120 s.
‐ At 7 % the air inlet flap closes.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
DSC-49-20 P 1/8
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FAULT lt :
CONTROLS AND INDICATORS
Depending on version of the ECB , this amber light comes on, and a caution appears
on ECAM, when an automatic APU shutdown occurs, which can happen in case of:
Fire (on ground only)
Air inlet flap closed
Overspeed
No acceleration
Slow start
EGT overtemperature
No flame
Reverse flow
Low oil pressure
High oil temperature
DC power lost (BAT OFF when aircraft on batteries only)
Overcurrent
Sensor failure
IGV failure
ECB failure
No speed
Underspeed
Loss of overspeed protection
Oil system shutdown
Inlet overheat
Clogged oil filter
Loss of EGT thermocouples
Note:
In the case of an automatic, non-emergency shutdown, the air inlet flap closes 15 min after
the APU speed is lower than 7%. If an automatic, non-emergency shutdown happens on
ground, the 15 min countdown starts after liftoff.
Ident.: DSC-49-20-A-00017439.0002001 / 21 MAR 16
(2) START pb-sw
ON
: Blue ON light comes on.
‐ When the flap is completely open, the APU starter is energized.
‐ 1.5 s after the starter is energized, the ignition is turned ON.
‐ When N = 55 %. The APU starter is de-energized. The ignition is turned off.
‐ 2 s after N reached 95 %, or when N is above 99.5 %:
The ON light on the START pb goes out.
The APU may now supply bleed air and electrical power to the aircraft systems.
‐ 10 s later, the APU page disappears from the ECAM display.
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FCOM
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DSC-49-20 P 2/8
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AVAIL lt :
CONTROLS AND INDICATORS
This green light comes on when N is above 99.5 % or 2 s after N reaches 95 %.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DSC-49-20 P 3/8
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
EXTERNAL CONTROLS
Ident.: DSC-49-20-00001539.0001001 / 21 MAR 16
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
DSC-49-20 P 4/8
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-49-20 P 5/8
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
ECAM APU PAGE
Applicable to: ALL
Ident.: DSC-49-20-B-00017440.0001001 / 21 MAR 16
Ident.: DSC-49-20-B-00017441.0002001 / 21 MAR 16
(1) AVAIL
Displayed in green when APU N is above 99.5 % or 2 s after N is above 95 %.
Ident.: DSC-49-20-B-00017442.0001001 / 21 MAR 16
(2) APU bleed air valve position
Inline-Green
: The APU bleed air valve is not closed.
Crossline-Green
: The APU bleed air valve is closed.
Crossline-Amber
: The APU bleed air valve is closed and the APU bleed is ON.
XX-Amber
: The APU bleed air valve status information is not available, or the APU
BLEED pb status is not available.
Ident.: DSC-49-20-B-00017443.0001001 / 21 MAR 16
(3) APU bleed air pressure
This box displays the relative bleed air pressure in green.
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DSC-49-20 P 6/8
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS
It shows an amber XX when the ADIRS 1 or the ADIRS 2 is not available or selected OFF or the data
from the ECB are invalid or not transmitted.
Ident.: DSC-49-20-B-00017444.0001001 / 21 MAR 16
(4) APU GEN line contactor indication
Displayed in green when the APU GEN line contactor is closed.
Ident.: DSC-49-20-B-00017445.0001001 / 21 MAR 16
(5) APU GEN parameters
Identical to the APU GEN parameters on the ELEC page.
Ident.: DSC-49-20-B-00017446.0001001 / 21 MAR 16
(6) FUEL LO PR
Displayed in amber if APU fuel pressure gets low.
Ident.: DSC-49-20-B-00017447.0003001 / 21 MAR 16
(7) FLAP OPEN
‐ Displayed in green when APU air intake flap is fully open.
‐ Advisory if the flap is not fully closed 3 min after the MASTER sw has been turned OFF.
Ident.: DSC-49-20-B-00017448.0001001 / 21 MAR 16
(8) APU N
‐ Displays APU speed in green.
‐ Becomes amber when N ≥ 102 %.
‐ Becomes red when N ≥ 107 %.
Ident.: DSC-49-20-B-00017449.0002001 / 06 SEP 16
(9) APU EGT
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FCOM
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DSC-49-20 P 7/8
24 JAN 17
AIRCRAFT SYSTEMS
APU
A318/A319/A320/A321
CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
‐ Displays APU EGT in green.
‐ Becomes amber when EGT ≥ EGT MAX -33 °C.
‐ Becomes red when EGT ≥ EGT MAX (automatic shutdown begins).
Note:
ECB calculates EGT MAX and transmits it to the ECAM . It is a function of N during start,
and a function of ambient temperature when the APU is running.
Maximum EGT during start: 982 °C.
Maximum EGT with APU running:
‐ 682 °C during at least 5 s.
‐ or, 700 °C to 742 °C depending on the ambient temperature.
Ident.: DSC-49-20-B-00017450.0001001 / 21 MAR 16
(10) LOW OIL LEVEL
Advisory: Displayed if the ECB detects a low APU oil level when the aircraft is on the ground, and the
APU is not running.
MEMO DISPLAY
Ident.: DSC-49-20-00016689.0001001 / 21 MAR 16
Applicable to: ALL
APU AVAIL
:
This memo appears in green, when APU N is above 99.5 % or 2 s after N is
above 95 % (depending on the aircraft configuration).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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24 JAN 17
AIRCRAFT SYSTEMS
DOORS
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AIRCRAFT SYSTEMS
DOORS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-52-10 Description
DSC-52-10-10 General
Description............................................................................................................................................................... A
DSC-52-10-20 Passenger Doors
General.....................................................................................................................................................................A
Outside..................................................................................................................................................................... B
Inside........................................................................................................................................................................C
DSC-52-10-30 Emergency Exits
Cockpit..................................................................................................................................................................... A
Cabin........................................................................................................................................................................ B
DSC-52-10-40 Cargo Doors
General.....................................................................................................................................................................A
Fwd and Aft Cargo Doors....................................................................................................................................... B
Bulk Cargo Door ............................................................................................................................................ C
Location of Service Panels..................................................................................................................................... D
DSC-52-10-50 Avionics Compartment Access Door
Avionics Compartment Access Door.......................................................................................................................A
DSC-52-10-60 Cockpit Door
Cockpit Door............................................................................................................................................................ A
DSC-52-10-80 Escape Slides/Rafts
Door Slides.............................................................................................................................................................. A
Wing Slides.............................................................................................................................................................. B
Escape Slide Arrangement......................................................................................................................................C
DSC-52-20 Controls and Indicators
DOOR/OXY SD Page..............................................................................................................................................A
DSC-52-40 Cockpit Door Security System
DSC-52-40-10 Description
Cockpit Door Description.........................................................................................................................................A
DSC-52-40-20 Cockpit Door Locking System (CDLS)
COCKPIT DOOR LOCKING SYSTEM (CDLS).......................................................................................................A
Controls.................................................................................................................................................................... B
Continued on the following page
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AIRCRAFT SYSTEMS
DOORS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-52-40-30 Cockpit Door Surveillance System (CDSS)
Continued from the previous page
General.....................................................................................................................................................................A
Controls.................................................................................................................................................................... B
DSC-52-50 How to
How to Operate the Cockpit Door ......................................................................................................................... A
How to Operate the Fwd and Aft Cargo Door........................................................................................................ B
How to Operate the Fwd and Aft Cargo Doors (Auxiliary Operation).....................................................................C
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DESCRIPTION - GENERAL
FLIGHT CREW
OPERATING MANUAL
DESCRIPTION
Ident.: DSC-52-10-10-00001544.0002001 / 22 MAY 12
Applicable to: ALL
The A320's fuselage has:
‐ Four passenger doors
‐ Four emergency exits in the cabin
‐ Cockpit emergency exits (two sliding windows)
‐ Three cargo compartment doors
‐ Four avionic compartment access doors.
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DESCRIPTION - GENERAL
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OPERATING MANUAL
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DESCRIPTION - PASSENGER DOORS
GENERAL
Ident.: DSC-52-10-20-00017564.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft has four plug-type doors that open outward and forward. There are two doors on each
side of the fuselage (one door in the FWD section and one door in the AFT section).
The doors are operated from inside or outside of the aircraft. Normal operation is manual, with
hydraulic damping.
Each door has emergency features:
‐ An escape slide stowed in a container attached to the inboard lower side of the door
‐ A damper actuator in normal mode, the damper actuator limits the door travel; in emergency
mode, the damper actuator drives the automatic door opening
‐ A slide arming lever.
When the slide arming lever is in the ARMED position, the slide is connected to the floor brackets
on both sides of the door. When the door is open, the slide inflates and deploys automatically. If
the inflation bottle fails to discharge automatically, a crew member can open its valve to make it
discharge. Opening the door from outside disarms the door and the escape slide.
Each passenger door has :
‐ A mechanical locking indicator that confirms the locked or unlocked position of the door
‐ One warning light to show the ARMED or DISARMED indication of the escape slides
‐ One CABIN PRESSURE warning light that illuminates in the case of a residual pressure in the
cabin.
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DESCRIPTION - PASSENGER DOORS
OUTSIDE
Ident.: DSC-52-10-20-00017565.0001001 / 21 MAR 16
Applicable to: ALL
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FLIGHT CREW
OPERATING MANUAL
DESCRIPTION - PASSENGER DOORS
INSIDE
Ident.: DSC-52-10-20-00001547.0002001 / 22 MAY 12
Applicable to: ALL
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DESCRIPTION - PASSENGER DOORS
FLIGHT CREW
OPERATING MANUAL
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DESCRIPTION - EMERGENCY EXITS
COCKPIT
Ident.: DSC-52-10-30-00017567.0001001 / 21 MAR 16
Applicable to: ALL
The two sliding windows in the cockpit are flight crew emergency exits.
A small compartment, located above each window, contains an escape rope that is long enough
to reach the ground when lowered through either sliding window. The cockpit windows can only be
opened from inside.
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DESCRIPTION - EMERGENCY EXITS
Emergency cockpit evacuation is also possible through the cockpit door escape panel . This
panel is designed to be pushed open in the direction of the cabin after removal of the quick-release
pins.
CABIN
Ident.: DSC-52-10-30-00017568.0001001 / 06 DEC 16
Applicable to: ALL
Two emergency exits are located on each side of the cabin, in addition to the passenger doors. The
emergency exits are also equipped with escape slides. In the case of an emergency, the exits open
inwards.
The slides of the overwing emergency exits are always in armed configuration.
To open :
‐ Remove HANDLE COVER : The HANDLE LIGHT and SLIDE ARMED indicator illuminate
‐ Pull CONTROL HANDLE : The EXIT moves inwards
‐ Lift EXIT from frame by holding the HANDLE RECESS
‐ Throw EXIT out.
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DESCRIPTION - EMERGENCY EXITS
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DESCRIPTION - EMERGENCY EXITS
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OPERATING MANUAL
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DESCRIPTION - CARGO DOORS
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-52-10-40-00017569.0001001 / 21 MAR 16
Applicable to: ALL
The aircraft has two cargo doors (FWD and AFT cargo doors) on the right side of the fuselage below
the cabin floor.
FWD AND AFT CARGO DOORS
Ident.: DSC-52-10-40-00017570.0001001 / 21 MAR 16
Applicable to: ALL
The FWD and AFT cargo doors hydraulically open outward and upward. The doors are hydraulically
operated by the yellow hydraulic system. The door locking system (locked open/locked closed) is
mechanical.
If the electric pump of the yellow hydraulic system fails, the system can be powered by using a hand
pump, located on the hydraulic maintenance panel.
The FWD and AFT cargo doors open only from outside.
Note:
When the electric pump operates the FWD or AFT cargo door, the remaining yellow system
devices that operate are the brakes and the engine 2 thrust reverser.
BULK CARGO DOOR
Ident.: DSC-52-10-40-00017571.0001001 / 21 MAR 16
Applicable to: ALL
The bulk cargo door opens inward and upward. The bulk cargo door is a plug-type door. The door is
mechanically locked and manually operated.
The bulk cargo door opens from the outside or from the inside.
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DESCRIPTION - CARGO DOORS
FLIGHT CREW
OPERATING MANUAL
LOCATION OF SERVICE PANELS
Ident.: DSC-52-10-40-00020676.0002001 / 17 MAR 17
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DESCRIPTION - CARGO DOORS
Applicable to: ALL
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DESCRIPTION - CARGO DOORS
FLIGHT CREW
OPERATING MANUAL
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DESCRIPTION - AVIONICS COMPARTMENT ACCESS DOOR
AVIONICS COMPARTMENT ACCESS DOOR
Ident.: DSC-52-10-50-00017579.0001001 / 21 MAR 16
Applicable to: ALL
Four avionics compartment access doors enable an external access to the avionics compartment.
The doors are manually operated, hinged doors. The doors open inwards.
These doors are in the lower fuselage, around the nose landing gear bay.
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DESCRIPTION - AVIONICS COMPARTMENT ACCESS DOOR
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DESCRIPTION - COCKPIT DOOR
FLIGHT CREW
OPERATING MANUAL
COCKPIT DOOR
Ident.: DSC-52-10-60-00017573.0002001 / 21 MAR 17
Applicable to: ALL
Refer to DSC-52-40-10 Cockpit Door Description for information about the secured cockpit door.
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DESCRIPTION - ESCAPE SLIDES/RAFTS
FLIGHT CREW
OPERATING MANUAL
DOOR SLIDES
Ident.: DSC-52-10-80-00001555.0001001 / 09 OCT 12
Applicable to: ALL
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DESCRIPTION - ESCAPE SLIDES/RAFTS
FLIGHT CREW
OPERATING MANUAL
WING SLIDES
Ident.: DSC-52-10-80-00001556.0001001 / 09 OCT 12
Applicable to: ALL
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DESCRIPTION - ESCAPE SLIDES/RAFTS
FLIGHT CREW
OPERATING MANUAL
ESCAPE SLIDE ARRANGEMENT
Ident.: DSC-52-10-80-00017577.0001001 / 21 MAR 16
Applicable to: ALL
There are two types of emergency slides: a single-lane escape slide/slideraft or a dual-lane escape
slide/slideraft.
Each passenger door either has a single-lane escape slide, or a single-lane slideraft, and each
emergency exit has a dual-lane escape slide.
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DESCRIPTION - ESCAPE SLIDES/RAFTS
FLIGHT CREW
OPERATING MANUAL
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CONTROLS AND INDICATORS
FLIGHT CREW
OPERATING MANUAL
DOOR/OXY SD PAGE
Ident.: DSC-52-20-00017645.0001001 / 21 MAR 16
Applicable to: ALL
(1)
Door symbol
Green □
:
Amber ■
:
(2)
Door indication
This appears in amber, when the door is not locked.
(3)
SLIDE indication
This appears in white, when the slide is armed.
(4)
Stair symbol
This appears in amber, when the stair door is not closed.
Note:
The door is closed and locked.
The door is not locked.
For aircraft without FWD EMER EXIT doors, the FWD EMER EXIT door symbols are
always displayed in green.
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COCKPIT DOOR SECURITY SYSTEM - DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
COCKPIT DOOR DESCRIPTION
Ident.: DSC-52-40-10-00017010.0001001 / 17 MAR 17
Applicable to: ALL
A forward-opening hinge door separates the cockpit from the passenger compartment. It has three
electric locking strikes, controlled by the flight crew. In normal conditions, when the door is closed,
they remain locked. When there is a request to enter the cockpit, the flight crew can authorize entry
by unlocking the door, that remains closed until it is pushed open.
When the flight crew does not respond to requests for entry, the door can also be unlocked by
the cabin crew, by entering a two to seven-digit code (programmed by the airline) on the keypad,
installed on the lateral side of the Forward Attendant Panel (FAP).
The door is bulletproof and fully compliant with rapid decompression requirements.
A mechanical override enables the flight crew to open the door from the cockpit side.
A deadbolt is installed at the level of the center latch area of the cockpit door. This deadbolt
bolts the door from the cockpit side, in the event that more than one locking latch strike fails, or in the
case of a total CLS failure.
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Note:
COCKPIT DOOR SECURITY SYSTEM - DESCRIPTION
1. The escape panel enables the flight crew to evacuate the cockpit, in case of an
emergency, when the door is jammed. This panel can only be removed from the cockpit
side by pulling the quick release pins towards the center of the flap and kicking the panel
open.
2. In case of an electrical supply failure, the door is automatically unlocked, but remains
closed.
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COCKPIT DOOR SECURITY SYSTEM COCKPIT DOOR LOCKING SYSTEM (CDLS)
COCKPIT DOOR LOCKING SYSTEM (CDLS)
Ident.: DSC-52-40-20-00001007.0001001 / 21 MAR 17
Applicable to: ALL
The Cockpit Door Locking System (CDLS) provides a means of electrically locking and unlocking the
cockpit door. This system is mainly composed of :
‐ A keypad, located in the forward cabin, near the cockpit door,
‐ A toggle switch, located in the center pedestal’s Cockpit Door panel,
‐ A control unit and its CKPT DOOR CONT normal panel, located on the overhead panel,
‐ A buzzer.
The keypad enables the cabin crew to request access to the cockpit. There are two different access
request types : “Routine” and “Emergency” access request.
The toggle switch enables the flight crew to lock or unlock the cockpit door, following an access
request, thereby allowing or denying the entry to the cockpit.
The cockpit door control unit is the system controller, in charge of :
‐ Locking or unlocking the door latches, upon flight crew action.
‐ Unlocking the door, in case of cockpit decompression (the door then opens towards the cockpit
under differential pressure).
‐ Indicating system failures of electrical latches and pressure sensors.
‐ Activating the access request buzzer and turning on the keypad LEDs.
The buzzer sounds in the cockpit for 1 to 9 s to indicate that a routine access request has been
made, or sounds continuously if an emergency access procedure has been initiated.
CONTROLS
Applicable to: ALL
Ident.: DSC-52-40-20-A-00001008.0001001 / 21 MAR 17
KEYPAD
The keypad is used by the cabin crew to request pilots to open the door.
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COCKPIT DOOR SECURITY SYSTEM COCKPIT DOOR LOCKING SYSTEM (CDLS)
(1)
Locked/Unlocked Door Indicator
GREEN light ON
: The door has been unlocked either by a flight crew action, or
automatically (during 5 s) when no flight crew action is performed
during the delay following an emergency access request. The
door can be pushed open.
GREEN light flashes : An emergency request to enter the cockpit has been made; the
buzzer will sound continuously in the cockpit, but no action has
yet been taken by the flight crew.
RED light ON
: The flight crew has denied access, and the door remains locked.
WHITE light ON : The light comes on each time the cabin crew presses a key on
the keypad.
(2)
Digital Keypad
The keypad is used to sound the buzzer in the cockpit for 1 to 9 s (3 s by default), by
entering a zero to seven-digit code, as programmed by the airline, followed by the '#' key.
It is also used to enter the two to seven-digit emergency code, followed by the '#' key, when
the flight crew does not respond.
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Note:
COCKPIT DOOR SECURITY SYSTEM COCKPIT DOOR LOCKING SYSTEM (CDLS)
During the test performed by the cockpit door control unit, the CDLS keypad
remains operational, and the CDLS operates as follows:
The control unit will store access codes that are entered, and the
LOCKED/UNLOCKED DOOR INDICATOR (RED/GREEN LEDs) of the keypad will
remain on, as long as the test is running.
‐ If the correct access code is entered on the keypad, the buzzer will not sound,
until the test is completed.
‐ If the emergency access code is entered, the door will unlock. The cockpit
buzzer and the LOCKED/UNLOCKED DOOR INDICATOR will be inoperative.
Ident.: DSC-52-40-20-A-00018437.0001001 / 17 MAR 17
CENTRAL PEDESTAL COCKPIT DOOR PANEL
The secured cockpit door opening is controlled by a toggle switch, located on the central pedestal.
(1)
COCKPIT DOOR toggle switch
UNLOCK
: This position is used to enable the cabin crewmember to open the door.
position
The switch must be pulled and maintained in the unlock position until
the door is pushed open.
NORM position : All latches are locked, and EMERGENCY access is possible for the
cabin crew.
LOCK position : Once the button has been moved to this position, the door is locked ;
emergency access, the buzzer, and the keypad are inhibited for a
preselected time (5 to 20 min).
Note:
1. If the LOCK position has not been used by the pilot, for at least 5 to 20 min, the
cabin crew is able to request emergency access to open the cockpit door.
2. The UNLOCK position overrides and resets any previous selection.
3. In case of an electrical supply failure, the cockpit door is automatically unlocked,
but remains closed.
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(2)
COCKPIT DOOR SECURITY SYSTEM COCKPIT DOOR LOCKING SYSTEM (CDLS)
COCKPIT DOOR Fault Open indicator
OPEN light ON : The door is not closed.
OPEN light
: The cabin crew has started an emergency access procedure. If there
flashes
is no reaction from the flight crew, the door will unlock at the end of the
adjustable time delay (15 to 120 s).
FAULT
: This light comes on when a system failure has been identified
(Example : Latch, pressure sensors, control unit).
The inoperative item can be identified by checking the strike and
pressure sensor status lights on the CKPT DOOR CONT panel.
Ident.: DSC-52-40-20-A-00001010.0001001 / 09 OCT 12
OVERHEAD CONTROL PANEL
The Cockpit Door Locking System's control panel is located on the overhead panel.
(1)
Strikes' status lights
Off : The corresponding (upper, mid, or lower) locking latch is operative.
On : The corresponding (upper, mid, or lower) locking latch is faulty.
(2)
Pressure sensor
Two redundant differential pressure sensors enable rapid pressure variation in the cockpit
to be detected, in order to command simultaneous opening of all latches when a defined
pressure drop is detected.
(3)
Pressure sensor status lights
Off : The corresponding (1 or 2) pressure sensor is operative.
On : The corresponding (1 or 2) pressure sensor is faulty.
Note:
These indicators enable the crew to identify the faulty item, when the Central
Pedestal Fault indicator light is ON.
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COCKPIT DOOR SECURITY SYSTEM - COCKPIT
DOOR SURVEILLANCE SYSTEM (CDSS)
GENERAL
Ident.: DSC-52-40-30-00018415.0001001 / 17 MAR 17
Applicable to: ALL
The Cockpit Door Surveillance System (CDSS ) consists of three video cameras, that enable the
flight crew to identify persons prior to authorizing their entry into the cockpit. The lower ECAM display
displays the various camera views. A control panel, located on the central pedestal allows the flight
crew members to select the CDSS display on the SD and to swap between the different camera
views.
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COCKPIT DOOR SECURITY SYSTEM - COCKPIT
DOOR SURVEILLANCE SYSTEM (CDSS)
CONTROLS
Applicable to: ALL
Ident.: DSC-52-40-30-A-00018416.0003001 / 17 MAR 17
(1)
Lower ECAM rotary selector
CKPT
: The lower ECAM displays the camera 1 image.
ENTRY
The camera images are not displayed on the Lower ECAM display in the
case of:
‐ A subsequent automatic system page call following a warning, a caution,
or an advisory, or
‐ A subsequent manual selection of a system page on the ECAM Control
Panel (ECP), or
‐ A SD failure, or
‐ An EWD failure.
OFF
(2)
:
The lower ECAM display operates normally.
Lower ECAM CAM SEL
Selects various camera image displays, when the lower ECAM rotary selector is set to the
CKPT ENTRY position.
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COCKPIT DOOR SECURITY SYSTEM - COCKPIT
DOOR SURVEILLANCE SYSTEM (CDSS)
The image from camera 1 appears:
‐ Automatically, when the lower ECAM rotary selector is set to the CKPT ENTRY position.
‐ When images from cameras 2 and 3 are displayed, and after the flight crew presses the
lower ECAM CAM SEL pb
‐ Automatically, when images from cameras 2 and 3 are displayed, and after a crew member
uses the cabin keypad to make an entry request at least 30 s after a previous entry request.
Images from cameras 2 and 3 are displayed simultaneously on a split screen, when the image
from camera 1 is displayed, and after the flight crew presses the lower ECAM CAM SEL pb.
Note:
1. The message “PLEASE WAIT” is displayed during the transition between two video
images when the flight crew requests an image change.
2. The message “VIDEO NOT AVAIL” is displayed when the flight crew requests a
video image and no image can be displayed.
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COCKPIT DOOR SECURITY SYSTEM - COCKPIT
DOOR SURVEILLANCE SYSTEM (CDSS)
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HOW TO
FLIGHT CREW
OPERATING MANUAL
HOW TO OPERATE THE COCKPIT DOOR
Ident.: DSC-52-50-00020495.0001001 / 17 MAR 17
Applicable to: ALL
The secured cockpit door operation is controlled by a toggle sw that is located on the COCKPIT
DOOR panel (central pedestal).
DOOR OPENING FROM THE COCKPIT
To enable access to the cockpit, set and maintain the COCKPIT DOOR sw to the UNLOCK
position until the door is fully opened. When the door is fully opened, the COCKPIT DOOR sw can
be released to the NORM position.
DOOR CLOSING FROM THE COCKPIT
Close the door and check that the OPEN indicator goes off. If the COCKPIT DOOR sw is in the
NORM position, the door is locked and emergency access is possible from the cabin. When
the door is fully closed, if the cockpit door FAULT light is ON, Refer to PRO-ABN-DOOR [QRH]
COCKPIT DOOR FAULT.
Note:
If the OPEN indicator is ON when the door is closed, the door may be unlocked. Repeat
the above-mentioned opening/closing procedure.
When the COCKPIT DOOR sw is in the LOCK position the door is locked. In this position, the
emergency access, the buzzer, and the keypad are inhibited for a preselected time (5 to 20 min).
ROUTINE ACCESS TO THE COCKPIT FROM THE CABIN (I.E. NORMAL ACCESS)
L2
L1
To request access to the cockpit from the cabin, use the keypad to enter the code and validate
with the “#” key.
The Operator defines this code (between 0 and 7 digits).
The buzzer sounds in the cockpit for 1 to 9 s (3 s by default).
After identification of the person (using the Cockpit Door Surveillance System ) that requests
access, set the COCKPIT DOOR sw to UNLOCK position to unlock the door. A steady green light
on the keypad comes on, that indicates that the door is unlocked.
If the flight crew refuses access to the cockpit by setting the COCKPIT DOOR sw to LOCK
position, a steady red light on the keypad comes on, that indicates that the door is locked. The
keypad and the buzzer are inhibited for a defined period of time.
If the flight crew does not respond, the door remains locked. If the flight crew does not take
any action after a routine cabin request, the cabin crew will be able to open the door with the
emergency access procedure.
EMERGENCY ACCESS FROM CABIN TO THE COCKPIT
To request emergency access to the cockpit, use the keypad to enter the emergency code and
validate with the “#” key.
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HOW TO
The Operator defines this emergency code (between 2 and 7 digits).
The buzzer continuously sounds in the cockpit and the OPEN light flashes on the COCKPIT
DOOR panel (central pedestal). In the cabin, the green light on the keypad flashes until the flight
crew uses the COCKPIT DOOR sw to either lock or unlock the cockpit door.
After identification of the person (via the Cockpit Door Surveillance system ) that requests
access, use the COCKPIT DOOR sw to unlock the door.
If the flight crew refuses access by setting the COCKPIT DOOR sw to LOCK position, the keypad
and the buzzer are inhibited for a defined period of time.
If the flight crew does not respond, after a preselected time between 15 and 120 s, the door
automatically unlocks for 5 s and a steady green light on the keypad comes. The buzzer stops and
indicates that the door is unlocked.
EVACUATION THROUGH THE DECOMPRESSION AND EVACUATION PANEL
Pull the quick-release pins of the escape panel towards the center of the flap.
Kick the escape panel toward the cabin and evacuate the cockpit.
HOW TO OPERATE THE FWD AND AFT CARGO DOOR
Ident.: DSC-52-50-00020574.0003001 / 17 MAR 17
Applicable to: ALL
NORMAL OPERATION
OPENING
On the cargo door, push the door handle flap inward to release the door handle from the recess
of the door structure. Then, pull the door handle away and upward from the LOCKED to the
UNLOCKED position.
Open the access door of the service panel to get access to the selector valve lever. Set the
selector valve lever to the OPEN position and maintain the lever in this position until the green
indicator light comes on. The green indicator light indicates that the door is fully opened and
locked.
Note:
The yellow hydraulic system is pressurized (the YELLOW ELEC PUMP is energized).
The operation of the flight controls and PTU is inhibited.
When the door is fully open, release the selector valve lever. When released, the selector valve
lever returns to the neutral position and shuts down the electrical pump.
CLOSING
In order to close the cargo door, set the selector valve lever to the CLOSE position and maintain
the lever in this position until the green indicator light goes off. When this light goes off, it means
that the door is fully closed and locked.
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Note:
At first the selector valve lever locks in an intermediate position maintaining a preset
pressurization to prevent the door from dropping open.
When the door is fully closed, the selector valve lever returns to the neutral position and shuts
down the electrical pump.
On the cargo door, push the door handle flap downwards to the LOCKED position. When the
door is locked, the cargo door symbol appears in green on the DOOR/OXY SD page. The
CARGO door indication on the ECAM goes off, and the handle flap mechanism locks the
operating handle.
Close the access door of the service panel.
HOW TO OPERATE THE FWD AND AFT CARGO DOORS (AUXILIARY OPERATION)
Ident.: DSC-52-50-00020577.0002001 / 17 MAR 17
Applicable to: ALL
AUXILIARY OPERATION
If there is an electrical failure or if the yellow hydraulic electric pump fails, the operator can open
or close the cargo door with the use of the hand pump that is accessible via the ground service
panel.
Note:
Two persons are necessary for this operation.
MANUAL OPENING
To open the cargo door with the use of the hand pump, unlock the cargo door by using the
operating handle as for normal operation.
Open the ground service panel of the yellow hydraulic system that is in the belly fairing area.
Open the access door of the door service panel. Set the selector valve lever to the OPEN
position and maintain the lever in this position during the operation of the hand pump.
Operate the hand pump until the cargo door is in the fully open position. The green light comes
on and indicates that the door is fully opened and locked.
When the cargo door is fully opened, release the selector valve lever of the door service panel.
MANUAL CLOSING
To close the cargo door, set the selector valve lever (on the door service panel) to the CLOSE
position and maintain the lever in this position during the operation of the hand pump.
Operate the hand pump until the cargo door is in the fully closed position.
When the cargo door is fully closed, release the selector valve lever of the door service panel.
Lock the cargo door with the use of the operating handle as for normal operation.
Close the access door of the door service panel and of the ground service panel.
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PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-56-10 General
General.....................................................................................................................................................................A
DSC-56-20 Fixed Windows
Fixed Windows.........................................................................................................................................................A
DSC-56-30 Sliding Windows
Sliding Windows.......................................................................................................................................................A
DSC-56-40 Description
Description............................................................................................................................................................... A
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GENERAL
FLIGHT CREW
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GENERAL
Ident.: DSC-56-10-00000998.0001001 / 17 MAR 17
Applicable to: ALL
The cockpit has fixed and sliding windows.
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FIXED WINDOWS
FLIGHT CREW
OPERATING MANUAL
FIXED WINDOWS
Ident.: DSC-56-20-00000999.0001001 / 17 MAR 17
Applicable to: ALL
There are four fixed windows :
‐ two windshields
‐ two fixed side windows
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SLIDING WINDOWS
FLIGHT CREW
OPERATING MANUAL
SLIDING WINDOWS
Ident.: DSC-56-30-00018432.0001001 / 17 MAR 17
Applicable to: ALL
The flight crew can use the sliding windows as emergency exits. Therefore they are not permitted to
stow any object so that it protrudes into the window area from the side console. Members of the flight
crew can use the control handle to slide each of the windows rearward, and can use a locking pin to
lock each window open.
(1)
Unlocking button
Flight crew presses this button to unlock the control handle.
(2)
Control handle
‐ To open the window, the crew member pulls inward and rearward.
‐ To close the window, the crew member pushes forward.
(3)
Locking pin
This pin locks the window open.
It is near the window’s lower guide track and is visible when the window is open.
‐ Forward
Between the closed position and the one-third open position, the window is free to move
forward and aft.
When the window is more than one-third open, this pin prevents it from moving forward.
‐ Aft
Flight crew must move the locking pin aft in order to close the window. Left sliding window.
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DESCRIPTION
Ident.: DSC-56-40-00013772.0001001 / 17 MAR 17
Applicable to: ALL
COCKPIT WINDSHIELD AND WINDOWS DESCRIPTION
All cockpit windows are fail-safe design.
The windows are made of:
‐ A non structural ply, the Outer ply (1), which is only a protective layer
‐ Two structural plies, the Middle ply (2) and the Inner ply (3)
Each structural ply is able to sustain individually the pressurization loads
‐ A heating film (4) to defog and/or de-ice the windshield/window
‐ Two interlayers (5).
Typical Structure Of A Cockpit Window (Cut View)
For information on cockpit window damage procedure, description and evaluation method, Refer
to FCTM/PR-AEP-MISC Cockpit Windshield/Window Cracked.
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PRELIMINARY PAGES - TABLE OF CONTENTS
DSC-70-05 Overview
Overview.................................................................................................................................................................. A
DSC-70-10 System Description
Engine...................................................................................................................................................................... A
Engine...................................................................................................................................................................... B
LP Compressor Turbine Assembly......................................................................................................................... C
HP Compressor Turbine Assembly.........................................................................................................................D
Combustion Chamber.............................................................................................................................................. E
Accessory Gearbox..................................................................................................................................................F
DSC-70-20 FADEC
General.....................................................................................................................................................................A
Architecture.............................................................................................................................................................. B
Functions ................................................................................................................................................................ C
Idle Control.............................................................................................................................................................. D
DSC-70-30 Thrust Control System (CFM+PW)
DSC-70-30-10 General
General.....................................................................................................................................................................A
DSC-70-30-20 Thrust Levers
Thrust Levers........................................................................................................................................................... A
DSC-70-30-30 Thrust Rating Limit
Thrust Rating Limit.................................................................................................................................................. A
DSC-70-30-40 Thrust Control
Manual Mode........................................................................................................................................................... A
Automatic Mode....................................................................................................................................................... B
DSC-70-40 Fuel System (CFM56)
General.....................................................................................................................................................................A
Fuel pump Unit........................................................................................................................................................ B
Shut-Off Valves........................................................................................................................................................C
Hydromechanical Unit..............................................................................................................................................D
IDG Cooling System ...............................................................................................................................................E
DSC-70-50 Oil System
General.....................................................................................................................................................................A
Continued on the following page
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DSC-70-60 Airbleed System (CFM56)
Continued from the previous page
General.....................................................................................................................................................................A
Cooling..................................................................................................................................................................... B
DSC-70-70 Thrust Reverser System
General.....................................................................................................................................................................A
Actuation Logic........................................................................................................................................................ B
Protection................................................................................................................................................................. C
Schematic................................................................................................................................................................ D
DSC-70-80 Ignition and Starting
DSC-70-80-10 General
General.....................................................................................................................................................................A
DSC-70-80-20 Architecture
Architecture.............................................................................................................................................................. A
DSC-70-80-30 Ignition System
General.....................................................................................................................................................................A
Ignition for Starting.................................................................................................................................................. B
Continuous Ignition.................................................................................................................................................. C
DSC-70-80-40 Engine Starting System
General.....................................................................................................................................................................A
Automatic Starting....................................................................................................................................................B
Automatic Starting Sequence..................................................................................................................................C
Manual Starting........................................................................................................................................................D
Engine Ventilation (Dry Cranking)........................................................................................................................... E
DSC-70-90 Controls and Indicators
DSC-70-90-10 Overhead Panel
ENG MAN START Panel........................................................................................................................................ A
DSC-70-90-20 Pedestal
ENG MODE Selector and ENG MASTER Levers.................................................................................................. A
Thrust Levers........................................................................................................................................................... B
DSC-70-90-30 Maintenance Panel
ENG FADEC GND PWR Panel.............................................................................................................................. A
Continued on the following page
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DSC-70-90-40 Engine Display
Continued from the previous page
Engine/Warning Display...........................................................................................................................................A
ENG SD Page......................................................................................................................................................... B
DSC-70-90-50 Memo Display
Memo Display.......................................................................................................................................................... A
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OVERVIEW
FLIGHT CREW
OPERATING MANUAL
OVERVIEW
Applicable to: ALL
Ident.: DSC-70-05-10-00018242.0002001 / 21 MAR 16
The aircraft has two CFM International CFM56-5B engines that supply power to the aircraft.
Ident.: DSC-70-05-10-00018265.0001001 / 21 MAR 16
The engines are turbofan engines that have:
‐ A high bypass ratio,
‐ A Full Authority Digital Engine Control (FADEC),
‐ A fuel system,
‐ An oil system,
‐ An air system,
‐ A thrust reverser system,
‐ An ignition system and a start system.
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Overview
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SYSTEM DESCRIPTION
FLIGHT CREW
OPERATING MANUAL
ENGINE
Ident.: DSC-70-10-00018361.0001001 / 21 MAR 16
Applicable to: ALL
The engine has:
‐ Two compressor turbine assemblies:
• The Low Pressure (LP) compressor turbine assembly,
• The High Pressure (HP) compressor turbine assembly.
L2
Each turbine operates its associated compressor via a shaft.
L1 ‐ One accessory gearbox,
‐ One combustion chamber.
The engine operates as follows:
1. The LP compressor, compresses the air.
2. Then, the air is divided into two flows:
‐ Most of the air flows out of the core engine, and provides most of the engine thrust.
‐ The remaining air enters the core engine.
3. The HP compressor compresses the air that enters the core engine.
4. The fuel is added to and mixed with the compressed air of the core engine. The mixture is ignited
in the combustion chamber.
5. The gas that results from combustion drives the HP and the LP turbines.
The rotation speed of the fan provides the N1 engine parameter.
The rotation speed of the HP rotor provides the N2 engine parameter.
The N1 and N2 engine parameters appear on the Engine/Warning Display (E/WD).
L2 The N1 and N2 engine parameters are current rotation speeds displayed in percentage.
L1
The FADEC uses:
‐ The N1 engine parameter to compute the applicable engine thrust,
‐ The N1 and N2 engine parameters for engine control and monitoring.
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ENGINE
Ident.: DSC-70-10-00018362.0002001 / 21 MAR 16
Applicable to: ALL
LP COMPRESSOR TURBINE ASSEMBLY
Ident.: DSC-70-10-00018289.0002001 / 21 MAR 16
Applicable to: ALL
LP COMPRESSOR TURBINE ASSEMBLY
L2
L1
L2
The LP compressor turbine assembly has:
‐ One LP compressor,
‐ One LP shaft,
‐ One LP turbine.
The LP shaft connects the LP compressor to the LP turbine.
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L3
The LP compressor has a fan and 4 stages, and the LP turbine has 4 stages.
HP COMPRESSOR TURBINE ASSEMBLY
Ident.: DSC-70-10-00018290.0001001 / 21 MAR 16
Applicable to: ALL
HP COMPRESSOR TURBINE ASSEMBLY
L2
L1
L2
L3
The HP compressor turbine assembly has:
‐ One HP compressor,
‐ One HP shaft,
‐ One HP turbine.
The HP shaft connects the HP compressor to the HP turbine.
The HP compressor has 9 stages, and the HP turbine has a single stage.
COMBUSTION CHAMBER
Ident.: DSC-70-10-00018292.0001001 / 21 MAR 16
Applicable to: ALL
COMBUSTION CHAMBER
L3
The combustion chamber burns a mixture of fuel and HP air. The FADEC controls the fuel/air
mixture in accordance with the position of the thrust lever and the aircraft operating conditions.
The combustion chamber is an annular assembly with fuel nozzles and two igniters.
The combustion chamber is between the HP compressor and the HP turbine.
ACCESSORY GEARBOX
Ident.: DSC-70-10-00018364.0001001 / 21 MAR 16
Applicable to: ALL
ACCESSORY GEARBOX
The accessory gearbox drives various accessories with mechanical power via the HP shaft for the
operation of the engine and the aircraft systems.
L2
The accessory gearbox of each engine operates:
‐ The oil feed pump that provides the oil system with oil.
‐ The main engine fuel pump that provides the combustion chamber with fuel.
‐ The engine-driven hydraulic pumps that pressurize the GREEN and the YELLOW hydraulic
systems.
‐ The engine-driven generators that are the primary source of electrical power.
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‐ The FADEC alternator that provides the FADEC with electrical power.
‐ The pneumatic starter that enables the engine start.
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FADEC
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GENERAL
Ident.: DSC-70-20-00020869.0001001 / 17 MAR 17
Applicable to: ALL
Each powerplant has a FADEC (Full Authority Digital Engine Control) system.
FADEC is a digital control system that performs complete engine management.
FADEC has two-channel redundancy, with one channel active and one in standby.
If one channel fails, the other automatically takes control.
The system has a magnetic alternator for an internal power source.
FADEC is mounted on the fan case.
The Engine Interface Unit (EIU ) transmits to FADEC the data it uses for engine management.
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ARCHITECTURE
Ident.: DSC-70-20-00001566.0005001 / 21 MAR 16
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Applicable to: ALL
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FADEC
FLIGHT CREW
OPERATING MANUAL
FUNCTIONS
Ident.: DSC-70-20-00001567.0001001 / 21 MAR 16
Applicable to: ALL
The FADEC system performs the following functions :
Control of gas generator
• control of fuel flow
• acceleration and deceleration schedules
• variable bleed valve and variable stator vane schedules
• control of turbine clearance
• idle setting
Protection against engine exceeding limits
• protection against N1 and N2 overspeed
• monitoring of EGT during engine start
Power management
• automatic control of engine thrust rating
• computation of thrust parameter limits
• manual management of power as a function of thrust lever position
• automatic management of power (A/THR demand).
Automatic engine starting sequence
• control of :
‐ the start valve (ON/OFF)
‐ the HP fuel valve
‐ the fuel flow
‐ the ignition (ON/OFF)
• monitoring of N1, N2, FF and EGT
• initiation of abort and recycle (on the ground only)
Manual engine starting sequence
• passive monitoring of engine
• control of :
‐ the start valve
‐ the HP fuel valve
‐ the ignition
Thrust reverser control
• Actuation of the blocker doors
• Engine setting during reverser operation
Fuel recirculation control
• Recirculation of fuel to the fuel tanks, depending on the engine oil temperature, the fuel system
configuration, and the flight phase.
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Transmission of engine parameters and engine monitoring information to cockpit
indicators
• Primary engine parameters
• Starting system status
• Thrust reverser system status
• FADEC system status
Detection, isolation, and recording of failures
FADEC cooling
IDLE CONTROL
Ident.: DSC-70-20-00015374.0001001 / 17 NOV 14
Applicable to: ALL
The FADEC has the following three idle modes :
Modulated idle
‐ Is regulated according to :
• bleed system demand
• ambient conditions
‐ Is selected :
• In flight, when the flaps are retracted (FLAPS lever at zero position)
• On ground, provided reverse is not selected.
Approach idle
‐ Is regulated according to aircraft altitude, regardless of bleed system demand.
‐ Is selected in flight, when the flaps are extended (FLAPS lever not at zero position)
‐ Allows the engine to accelerate rapidly from idle to go-around thrust.
Reverse idle
‐ Is selected on ground, when the thrust lever is in REV IDLE position.
‐ Is slightly higher than forward idle thrust.
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THRUST CONTROL SYSTEM (CFM+PW) - GENERAL
GENERAL
Ident.: DSC-70-30-10-00020872.0002001 / 17 MAR 17
Applicable to: ALL
A FADEC dedicated to each engine controls the thrust.
The pilot uses the thrust levers to set the thrust in manual mode, and the FMGS sets the thrust in
automatic mode (A/THR function).
The FADEC prevents the thrust from exceeding the limit for the thrust lever position in both manual
and automatic modes.
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FLIGHT CREW
OPERATING MANUAL
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FLIGHT CREW
OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST LEVERS
THRUST LEVERS
Ident.: DSC-70-30-20-00020873.0002001 / 17 MAR 17
Applicable to: ALL
The thrust levers can only be moved manually.
They move over a sector that is divided into four operating segments.
The sector has five positions defined by detents or stops.
Thrust lever position is transmitted to the FADEC , which computes and displays the thrust rating
limit and the N1 for that Thrust Lever Angle (TLA).
Note:
There is no reverse idle detent. When the pilot moves the lever out of the idle stop by
pulling up the reverse lever on the front of the thrust lever, he/she selects reverse idle.
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OPERATING MANUAL
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST RATING LIMIT
THRUST RATING LIMIT
Ident.: DSC-70-30-30-00001571.0001001 / 21 MAR 16
Applicable to: ALL
The FADEC computes the thrust rating limit for each thrust lever position, as shown below.
If the thrust lever is set in a detent, the FADEC selects the rating limit corresponding to this detent.
If the thrust lever is set between two detents, the FADEC selects the rating limit corresponding to the
higher detent.
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FLIGHT CREW
OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST RATING LIMIT
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST CONTROL
MANUAL MODE
Ident.: DSC-70-30-40-00001572.0001001 / 17 NOV 14
Applicable to: ALL
The engines are in the manual mode provided the A/THR function is:
‐ not armed or
‐ armed and not active (thrust lever not in the A/THR operating range and no alpha floor).
In these conditions, each engine is controlled by the position of its thrust lever.
The pilot controls thrust by moving the thrust lever between the IDLE and TOGA positions. Each
position of the thrust lever within these limits corresponds to an N1.
When the thrust lever is in a detent, the corresponding N1 is equal to the N1 rating limit computed by
the FADEC for that engine.
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AIRCRAFT SYSTEMS
ENGINES
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FLIGHT CREW
OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST CONTROL
When the thrust lever is in the FLX/MCT detent:
‐ On the ground
The engine runs at the flex takeoff thrust rating if the crew has selected a flex takeoff temperature
on the MCDU that is higher than the current Total Air Temperature (TAT).
Otherwise the engine produces Maximum Continuous Thrust (MCT).
‐ After takeoff
The pilot can change from FLX to MCT by moving the thrust lever to TOGA or CL, then back to
MCT. After that, he cannot use the FLX rating.
Note:
Setting the thrust lever out of FLX/MCT detent without reaching TOGA or CL detent has
no effect.
The pilot can always get MAX TO thrust by setting the thrust levers to TOGA.
AUTOMATIC MODE
Ident.: DSC-70-30-40-00020874.0003001 / 17 MAR 17
Applicable to: ALL
In the autothrust mode (A/THR function active), the FMGC computes the thrust which is limited to the
value corresponding to the thrust lever position (unless the alpha-floor mode is activated).
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22 MAR 17
AIRCRAFT SYSTEMS
ENGINES
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FLIGHT CREW
OPERATING MANUAL
THRUST CONTROL SYSTEM (CFM+PW) - THRUST CONTROL
INDICATIONS ON FMA
The FADEC s monitor the positions of the thrust levers, and trigger appropriate indications on the
FMA.Refer to DSC-22_30-100 Autothrust Annunciations (FMA Column 1) - Third Line.
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FUEL SYSTEM (CFM56)
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-70-40-00020868.0001001 / 17 MAR 17
Applicable to: ALL
The fuel system supplies fuel to the combustion chamber at the required flow rate, pressure, and
temperature.
The fuel flows from the tank, via the fuel pump unit and the fuel/oil heat exchanger, to the
Hydromechanical Unit (HMU) and to the fuel nozzles.
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OPERATING MANUAL
FUEL SYSTEM (CFM56)
FUEL PUMP UNIT
Ident.: DSC-70-40-00001586.0001001 / 21 MAR 16
Applicable to: ALL
The HP compressor shaft drives the HP fuel pump assembly. Fuel flows through the LP pump, then
through the fuel/oil heat exchanger and the HP pump (gear pump).
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AIRCRAFT SYSTEMS
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FUEL SYSTEM (CFM56)
FLIGHT CREW
OPERATING MANUAL
The fuel then divides into a filtered flow for the servo fuel heater and the servo valves of the HMU ,
and an unfiltered flow for the metering valve of the HMU.
SHUT-OFF VALVES
Ident.: DSC-70-40-00001587.0001001 / 12 MAY 16
Applicable to: ALL
Moving the ENG 1 (ENG 2) MASTER switch to OFF directly commands the closing of the LP and HP
fuel shut off valves for that engine's fuel system.
It also closes the fuel return valve and opens the bypass valve.
HYDROMECHANICAL UNIT
Applicable to: ALL
Ident.: DSC-70-40-A-00001588.0001001 / 17 MAR 17
GENERAL
The FADEC controls the HMU, which :
‐ controls fuel flow to the engine combustion chamber
‐ controls fuel hydraulic signals to actuators
‐ protects against overspeeding.
Ident.: DSC-70-40-A-00020880.0001001 / 17 MAR 17
FUEL FLOW
L3
The Fuel Metering Valve (FMV) transforms FADEC orders through a torque motor and servo valve
into fuel flow to the engine fuel nozzles.
The FMV resolver generates a feedback signal proportional to the FMV position.
The bypass valve maintains a constant pressure drop across the FMV to ensure that the metered
fuel flow is proportional to the FMV position.
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
L1
FUEL SYSTEM (CFM56)
The FADEC computes the fuel flow that will maintain the target N1.
As the FADEC maintains this N1, it allows N2 to vary while remaining between N2 minimum and
N2 maximum. The FADEC also controls the engine parameters to :
‐ Limit acceleration and deceleration ;
‐ Avoid engine stall or flameout ;
‐ Limit maximum N1 and N2 ;
‐ Maintain air bleed pressure requirement.
The FADEC computes an N2 correction according to the bleed configuration.
Ident.: DSC-70-40-A-00001590.0001001 / 17 MAR 17
OVERSPEED GOVERNOR SYSTEM
Independent of the FADEC, the overspeed governor limits the N2 by opening the fuel bypass
valve, in the event of a malfunction that could lead to an overspeed condition.
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FUEL SYSTEM (CFM56)
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-70-40-A-00001592.0002001 / 17 MAR 17
FUEL HYDRAULIC SIGNALS
L3
Fuel hydraulic signals go to :
‐ Low Pressure Turbine Clearance Control (LPTCC) valves
(Refer to DSC-70-60 General)
‐ High Pressure Turbine Clearance Control (HPTCC) valves
(Refer to DSC-70-60 General)
‐ Rotor Active Clearance Control ( RACC ) system
(Refer to DSC-70-60 General)
‐ Variable Stator Vanes ( VSV)
The VSV system positions the compressor variable vanes.
The FADEC maintains optimum compressor efficiency at a steady state and an adequate stall
margin for transient engine operation.
VSVs are fully closed during engine start and are fully open at high thrust.
‐ Variable Bleed Valves ( VBV )
The FADEC controls the VBV s, upstream of the HP compressor. Their setting depends on
compressor inlet temperature and on N2. It varies between full open (start, low thrust, and
during fast deceleration) and full closed (high thrust) positions.
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FUEL SYSTEM (CFM56)
FLIGHT CREW
OPERATING MANUAL
IDG COOLING SYSTEM
Ident.: DSC-70-40-00001593.0001001 / 26 JUL 12
Applicable to: ALL
Some of the fuel flowing out of the HMU goes to cool the oil systems of the Integrated Drive
Generators (IDGs). It then returns to the fuel pump unit or to the tank.
The Fuel Return Valve (FRV ), controlled by the FADEC, ensures that this flow is adequate.
L3 At low engine thrust, if the oil going into the IDG is too hot, the cooling fuel is sent back to the tank
(300 kg/h).
If oil temperature continues to rise, the ECU increases the minimum N2.
If oil temperature still keeps rising, the FADEC increases the fuel flow to the tank (from 300 to
600 kg/h, depending on fuel return temperature).
The fuel return valve is always mixing hot fuel with cold fuel so that the temperature of fuel returning
to the tank stays below 100 °C (from 200 to 400 kg/h, depending on fuel return temperature).
Fuel recirculation to the tank is inhibited (FRV closed) in the following cases :
‐ at engine shutdown
‐ during takeoff and climb
‐ if :
• wing tank level is below about 300 kg (660 lb).
• there is fuel overflow in the surge tank
• fuel feed is by gravity only.
‐ when fuel temperature in the wing tank in flight is above 52.5 °C
Note:
On the ground, high fuel temperature in the wing tank or fuel overflow in the surge tank
does not inhibit the fuel recirculation to the wing tank (FRV remains open).
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FUEL SYSTEM (CFM56)
FLIGHT CREW
OPERATING MANUAL
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FUEL SYSTEM (CFM56)
FLIGHT CREW
OPERATING MANUAL
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OIL SYSTEM
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-70-50-00001603.0001001 / 21 MAR 16
Applicable to: ALL
The oil system lubricates the engine components.
It contains :
‐ the oil tank
‐ the lube and scavenge pump modules
‐ the fuel/oil heat exchanger
‐ the filters, chip detectors, pressure relief and bypass valves.
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OIL SYSTEM
FLIGHT CREW
OPERATING MANUAL
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
AIRBLEED SYSTEM (CFM56)
GENERAL
Ident.: DSC-70-60-00001604.0002001 / 21 MAR 17
Applicable to: ALL
The air bleed system supplies the aircraft with compressed air.
It uses the air for:
‐ pneumatic system (Refer to DSC-36-10-10 General)
‐ cooling the engine compartment and the turbines.
COOLING
Ident.: DSC-70-60-00001605.0002001 / 21 MAR 16
Applicable to: ALL
ROTOR ACTIVE CLEARANCE CONTROL (RACC) SYSTEM
The FADEC controls the RACC system through the HMU . The RACC system controls the
clearance between the rotor blades of the HP compressor and its stator case.
The RACC system uses fifth-stage compressor bleed air that has been modulated according to
the N2 and the flight parameters. The bleed air goes to the N°3 bearing compartment, where it is
mixed with fan boost discharge.
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AIRCRAFT SYSTEMS
ENGINES
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FLIGHT CREW
OPERATING MANUAL
AIRBLEED SYSTEM (CFM56)
Clearances are at the maximum when the RACC valve is closed.
HP TURBINE CLEARANCE CONTROL (HPTCC) SYSTEM
The FADEC controls the HPTCC system through the HMU . The HPTCC system controls the HP
turbine clearance by modulating the HP compressor bleed air flow for cooling the HP turbine case.
It optimizes HP turbine performance and reduces exhaust gas temperature.
LP TURBINE CLEARANCE CONTROL (LPTCC) SYSTEM
The FADEC controls the LPTCC system through the HMU . The LPTCC system controls LP
turbine clearance by modulating the fan bleed air flow for cooling the LP turbine case.
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THRUST REVERSER SYSTEM
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-70-70-00020918.0003001 / 17 MAR 17
Applicable to: ALL
The aircraft reverses engine thrust by using four pivoting blocker doors on each engine to deflect the
fan airstream.
A hydraulic door jack positions each door.
‐ The green circuit powers the doors on ENG 1.
‐ The yellow circuit powers the doors en ENG 2.
The FADEC controls the thrust reverser system. Each FADEC channel performs control and
monitoring functions. The systems for the two engines are independent of each other.
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THRUST REVERSER SYSTEM
FLIGHT CREW
OPERATING MANUAL
The thrust reverser system on each engine has :
‐ 4 actuators,
‐ 4 latches,
‐ Door position switches,
‐ A Hydraulic Control Unit (HCU) that :
• Pressurizes the thrust reverser hydraulic system,
• Regulates the speed of the blocker doors, and
• Supplies actuators with hydraulic power.
‐ A hydraulic shutoff valve which allows hydraulic pressure to the HCU.
Each pivoting door moves independently (the doors are not synchronized).
The total actuation time is less than two seconds.
ACTUATION LOGIC
Ident.: DSC-70-70-00020920.0001001 / 17 MAR 17
Applicable to: ALL
Deployment requires :
‐ One FADEC channel, operating with its associated throttle reverse signal ;
‐ Right and left main gear compressed signal from the corresponding LGCIUs ;
‐ A Thrust Lever Angle (TLA ) reverse signals from at least one Spoiler Elevator Computer (SEC).
Before deployment is completed, the FADEC sets reverse idle thrust on the engine that is having its
thrust reversed.
PROTECTION
Ident.: DSC-70-70-00020921.0006001 / 17 MAR 17
Applicable to: ALL
‐ IDLE PROTECTION
The FADEC will automatically select the thrust to idle :
• In case of inadvertent thrust reverser deployment (while thrust reversers are commanded stowed),
as soon as the thrust reverser feedback position is above 15 % deployed (thrust decreasing
toward idle, when the detected position is between 10 % and 15 % ).
• In case of inadvertent thrust reverser stowage (while thrust reversers are commanded deployed),
as soon as the thrust reverser feedback position is below 78 % deployed (thrust decreasing toward
idle between 90 % and 78 % ).
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
THRUST REVERSER SYSTEM
SCHEMATIC
Ident.: DSC-70-70-00020919.0006001 / 17 MAR 17
Applicable to: ALL
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THRUST REVERSER SYSTEM
FLIGHT CREW
OPERATING MANUAL
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FLIGHT CREW
OPERATING MANUAL
IGNITION AND STARTING - GENERAL
GENERAL
Ident.: DSC-70-80-10-00020922.0001001 / 17 MAR 17
Applicable to: ALL
The FADEC controls and monitors the ignition and starting system according to:
‐ The position of the ENG MODE selector
‐ The position of the ENG MASTER sw
‐ The position of the ENG MAN START pb-sw
‐ The aircraft status (flight or ground)
The FADEC receives the previous inputs from the EIVMU /EIU.
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IGNITION AND STARTING - GENERAL
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OPERATING MANUAL
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FLIGHT CREW
OPERATING MANUAL
IGNITION AND STARTING - ARCHITECTURE
ARCHITECTURE
Ident.: DSC-70-80-20-00001617.0002001 / 21 MAR 16
Applicable to: ALL
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FLIGHT CREW
OPERATING MANUAL
IGNITION AND STARTING - ARCHITECTURE
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IGNITION AND STARTING - IGNITION SYSTEM
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: DSC-70-80-30-00020923.0001001 / 17 MAR 17
Applicable to: ALL
The ignition system is for engine starting on the ground and restarting in flight. It consists of two
identical independent circuits for each engine, normally controlled by the FADEC channel A and
channel B. Each FADEC channel can control both igniters.
Note:
Supply for igniter A switches to the STAT INV BUS BAR as soon as the static inverter is
operative.
IGNITION FOR STARTING
Ident.: DSC-70-80-30-00020924.0002001 / 17 MAR 17
Applicable to: ALL
ON THE GROUND
Automatic start:
• During a first automatic start attempt only one igniter is supplied. The FADEC automatically
alternates the igniters and/or channels used in successive start sequences.
• The ignition comes on automatically when N2 reaches 16 % and cuts off automatically when N2
reaches 50 %.
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IGNITION AND STARTING - IGNITION SYSTEM
FLIGHT CREW
OPERATING MANUAL
• During an automatic start, if the first attempt fails, the FADEC automatically initiates a new start
attempt with both igniters energized.
• Manual start:
• During a manual start both igniters are supplied, when the ENG MASTER sw is ON.
• Both igniters are cut off when N2 reaches approximately 50 %.
IN FLIGHT
In case of start attempt in flight, when the ENG MASTER sw is ON, both igniters are supplied.
CONTINUOUS IGNITION
Ident.: DSC-70-80-30-00001620.0004001 / 21 MAR 16
Applicable to: ALL
Continuous ignition may be selected either manually or automatically to maintain engine combustion.
MANUAL SELECTION
In flight, continuous ignition is on when the ENG MODE selector is on IGN/START, if the
corresponding engine is running.
Only one igniter is selected. If failed, both igniters are automatically selected.
On the ground after the engine is started, because ignition cuts off automatically, the flight crew
must switch the ENG MODE selector to NORM then back to IGN/START to turn on continuous
ignition.
AUTOMATIC SELECTION
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
GENERAL
Ident.: DSC-70-80-40-00001621.0001001 / 21 MAR 16
Applicable to: ALL
The engine starting system consists of an air turbine starter and a start valve.
The start valve admits air supplied by the pneumatic system to operate the starter.
The FADEC controls the start valve electrically and bleed pressure is required for opening the start
valve. If electrical control fails when the aircraft is on the ground, a handle allows the start valve to be
operated manually.
AUTOMATIC STARTING
Applicable to: ALL
Ident.: DSC-70-80-40-10-00020932.0001001 / 21 MAR 17
GENERAL
This sequence is under the full authority of the FADEC, which controls:
‐ The start valve
‐ The igniters
‐ The fuel HP valves.
Ident.: DSC-70-80-40-10-00020933.0001001 / 21 MAR 17
PROTECTION
The FADEC :
‐ Detects a hot start, a hung start, a stall, or no light up
‐ Announces FAULT and identifies the fault in an ECAM message
‐ Runs an abort sequence if a start aborts on the ground
• Closes the HP valve
• Closes the start valve
• Turns off ignition
• Cranks the engine crank after the start abort in order to clear out fuel vapors
• Controls any additional start attempts.
Ident.: DSC-70-80-40-10-00020934.0001001 / 21 MAR 17
DRY CRANKING
Depending on the engine thermal state, the FADEC can initiate a pre-start motoring (dry cranking)
up to 60 s. Pre-start motoring is active during all ground starts and ground cranking procedures to
limit the engine core speed below the bow rotor critical speed (bow rotor protection). The motoring
time will vary depending on the residual thermal condition of the engine and depending on the
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
engine vibration level. During the engine motoring, the FADEC logic limits the maximum N2
around 30 %.
Ident.: DSC-70-80-40-10-00020935.0001001 / 21 MAR 17
WINDMILLING
For an in-flight start, the FADEC decides whether the engine is windmilling fast enough or
needs assistance from the starter in view of current engine parameters and flight environment
parameters.
Flight crew may interrupt this start sequence by moving the ENG MASTER sw to OFF.
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AIRCRAFT SYSTEMS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
AUTOMATIC STARTING SEQUENCE
Applicable to: ALL
Ident.: DSC-70-80-40-20-00020925.0001001 / 21 MAR 17
SEQUENCE OF THE AUTOMATIC START
Ident.: DSC-70-80-40-20-00020926.0001001 / 21 MAR 17
INITIAL CONFIGURATION OF THE CONTROLS
The initial configuration prior an automatic engine start is the following :
‐ The ENG MASTER sw is set to OFF
‐ The ENG MODE selector is set to NORM
‐ The ENG MAN START pb-sw is set to OFF.
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
Ident.: DSC-70-80-40-20-00020927.0001001 / 21 MAR 17
FIRST STEP
The flight crew must set the ENG MODE selector to IGN/START, leading to the following:
‐ The ENG SD page appears on the SD
‐ All engine parameters are available
‐ Pack valves automatically close.
After 30 s, if the flight crew does not set the ENG MASTER sw to ON (Refer to DSC-70-80-40
Second Step), pack valves automatically open again.
Ident.: DSC-70-80-40-20-00020928.0001001 / 21 MAR 17
SECOND STEP
The flight crew must set the ENG MASTER sw to ON, and the following steps occur:
‐ The LP fuel valve opens
‐ The engine start valve opens
‐ The ignition starts:
• On ground: when N2 > 16 %
• In flight: Immediately.
‐ The HP fuel valve opens:
• On ground: when N2 > 22 %
• In flight: when N2 > 15 %.
‐ When N2 > 50 %:
• The engine start valve closes
• The ignition stops if on ground
• The pack valves reopen if another engine is not started within 30 s.
Ident.: DSC-70-80-40-20-00020929.0001001 / 21 MAR 17
THIRD STEP
The automatic engine start is finished.
The flight crew must set the ENG START selector to NORM.
Ident.: DSC-70-80-40-20-00020930.0001001 / 21 MAR 17
INTERRUPTION OF THE AUTOMATIC START
When required by ECAM and after confirmation, the flight crew must set the ENG MASTER lever
to OFF.
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AIRCRAFT SYSTEMS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
If the flight crew sets the ENG MASTER sw to OFF, the FADEC automatically :
‐ Closes the LP and the HP fuel shutoff valves
‐ Stops to energize the ignitor
‐ Closes the engine start valve.
MANUAL STARTING
Ident.: DSC-70-80-40-00020937.0001001 / 17 MAR 17
Applicable to: ALL
If an automatic start is not successful, the flight crew can perform a manual start.
In the manual start sequence, the FADEC has limited control. As a result, the flight crew must
monitor engine acceleration.
To perform a manual start, the flight crew must :
‐ Set the ENG MODE selector to IGN/START
‐ Set the ENG MAN START pb-sw to ON
‐ Set the ENG MASTER sw to ON.
The FADEC:
‐ Opens the engine start valve when the flight crew :
• Sets the ENG MODE selector to IGN/START
• Sets the ENG MAN START pb-sw to ON
‐ Opens the HP shutoff valve, and operates both igniters when the flight crew sets the ENG
MASTER sw to ON
‐ Closes the engine start valve, and cuts off the ignition when N2 reaches 50 %.
For more information about the manual start sequence,Refer to PRO-NOR-SUP-ENG Manual
Engine Start - General.
The FADEC makes a passive survey of the engine during the starting sequence : the flight crew is
made aware of an abnormal start by a proper ECAM warning and has to interrupt the start sequence.
The FADEC has not the authority to abort the manual start :
‐ in flight
‐ on ground, except if the start EGT limit is exceeded before reaching 50 % N2. In this case only,
the FADEC aborts the start.
In flight, the FADEC always commands a starter-assisted air start.
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AIRCRAFT SYSTEMS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IGNITION AND STARTING - ENGINE STARTING SYSTEM
ENGINE VENTILATION (DRY CRANKING)
Ident.: DSC-70-80-40-00020938.0001001 / 21 MAR 17
Applicable to: ALL
A dry cranking cycle ventilates the engine to remove fuel vapors after an unsuccessful start attempt
on the ground.
The flight crew can manually select cranking by setting the ENG MODE selector to CRANK and
the ENG MAN START pb-sw to ON (ENG MASTER sw OFF). Flight crew can stop the cranking by
setting the ENG MAN START pb-sw to OFF.
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ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - OVERHEAD PANEL
ENG MAN START PANEL
Applicable to: ALL
Ident.: DSC-70-90-10-20-00018366.0001001 / 21 MAR 16
ENG MAN START Panel
Ident.: DSC-70-90-10-20-00018370.0001001 / 12 MAY 16
ENG MAN START pb-sw
Off
L13
:
‐ Aborts the manual start sequence of the associated engine, when the ENG
MODE selector is set to IGN/START and the ENG MASTER lever is set to
OFF, or
‐ Stops the dry crank process of the associated engine, when the ENG MODE
selector is set to CRANK and the ENG MASTER lever is set to OFF.
ON (in blue) :
‐ Initiates the manual start sequence of the associated engine, when the ENG
MODE selector is set to IGN/START, or
‐ Initiates the wet crank process of the associated engine, when the ENG
MODE selector is set to CRANK and the ENG MASTER lever is set to ON, or
‐ Initiates the dry crank process of the associated engine, when the ENG
MODE selector is set to CRANK and the ENG MASTER lever is set to OFF.
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - OVERHEAD PANEL
Intentionally left blank
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - PEDESTAL
ENG MODE SELECTOR AND ENG MASTER LEVERS
Applicable to: ALL
Ident.: DSC-70-90-20-30-00018367.0001001 / 12 OCT 16
ENG MODE selector and ENG MASTER Levers
Ident.: DSC-70-90-20-30-00018373.0001001 / 21 MAR 17
ENG MODE START selector
NORM
:
IGN/START :
Normal mode of operation.
Use the IGN/START position to:
‐ Initiate the automatic or manual start sequences of the associated engine,
when the ENG MASTER lever is set to OFF, or
‐ Initiate the ignitors in flight as required.
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
L13
CRANK
:
CONTROLS AND INDICATORS - PEDESTAL
Use the CRANK position to:
‐ Initiate the dry crank process of the associated engine, when the ENG
MASTER lever is set to OFF and the ENG MAN START pb-sw is set to ON.
‐ Initiate the wet crank process of the associated engine for maintenance
purpose, when the ENG MASTER lever, and the ENG MAN START pb-sw
are set to ON.
Ident.: DSC-70-90-20-30-00018371.0001001 / 12 MAY 16
ENG MASTER lever
Also called ENG MASTER sw.
ON
: The FADEC:
‐ Initiates the automatic start sequence of the associated engine, when the
ENG MODE selector is set to IGN/START, or
‐ Initiates the manual start sequence of the associated engine, when the ENG
MODE selector is set to IGN/START and the ENG MAN START pb-sw is set
to ON.
OFF
:
The FADEC:
‐ Shuts down the associated engine, or
‐ Aborts the start sequence of the associated engine.
Ident.: DSC-70-90-20-30-00018372.0001001 / 21 MAR 17
ENG 1(2) FIRE light
FIRE Light :
A fire is detected in the corresponding engine.
Refer to DSC-26-20-20 ENG 1(2) FIRE Light
ENG 1(2) FAULT light
FAULT light :
This amber light comes on, and a caution appears on ECAM, if there is:
‐ The position of the HP fuel shutoff valve is abnormal, or
‐ The automatic start sequence of the associated engine aborts, or
‐ There is a malfunction of the thrust control.
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AIRCRAFT SYSTEMS
ENGINES
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CONTROLS AND INDICATORS - PEDESTAL
FLIGHT CREW
OPERATING MANUAL
THRUST LEVERS
Applicable to: ALL
Ident.: DSC-70-90-20-40-00018368.0001001 / 28 JUL 16
Thrust Levers
Ident.: DSC-70-90-20-40-00018376.0001001 / 21 MAR 16
THRUST LEVERS
The flight crew uses the thrust levers in order to:
‐ Adjust the thrust, or
‐ Select a thrust stop or detent, or
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - PEDESTAL
‐ Control the deployment and the stowage of the associated reversers, or
‐ Adjust the associated reverse thrust.
L2
L1
The flight crew can move each thrust lever individually.
The position of the thrust levers appears on the E/WD, via a blue circle on the thrust gauge.
The flight crew can move each thrust lever forward the Idle (0) stop, when the associated thrust
reverser lever is set to the locked position.
The flight crew can move each thrust lever backward the Idle (0) stop, when the associated thrust
reverser lever is in the unlocked position.
Ident.: DSC-70-90-20-40-00018377.0001001 / 12 OCT 16
THRUST DETENTS AND STOPS
There are two stops and four detents:
‐ The Idle (0) stop,
‐ The Climb (CL) detent,
‐ The Maximum Continuous Thrust (MCT )/Flexible Take Off (FLX) detent,
‐ The Takeoff (TO )/Go-Around (GA) detent,
‐ The Rev Idle (R or REV) detent,
‐ The Rev Max (F or FULL) stop.
Ident.: DSC-70-90-20-40-00018378.0001001 / 21 MAR 16
THRUST REVERSER LEVERS
The flight crew uses the thrust reverser levers in order to unlock the associated thrust lever.
The flight crew can move each thrust reverser lever upward to the unlocked position, when the
associated thrust lever is set to the Idle (0) stop.
The thrust reverser levers are automatically reset to the locked position, when the flight crew
moves the thrust levers forward the Idle (0) stop.
Ident.: DSC-70-90-20-40-00018379.0001001 / 21 MAR 16
A/THR Instinctive Disconnect pb
L2
Pressing the A/THR instinctive disconnect pb disconnects the A/THR.
For more information about A/THR instinctive disconnect pb, Refer to DSC-22_30-90 A/THR
Disconnection - General.
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ENGINES
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CONTROLS AND INDICATORS - MAINTENANCE PANEL
FLIGHT CREW
OPERATING MANUAL
ENG FADEC GND PWR PANEL
Applicable to: ALL
Ident.: DSC-70-90-30-10-00018365.0001001 / 12 OCT 16
ENG FADEC GND PWR Panel
Ident.: DSC-70-90-30-10-00018369.0001001 / 21 MAR 16
ENG FADEC GND PWR PB-SW
Off
:
ON
:
The electrical network of the aircraft or the FADEC alternator automatically
supplies the FADEC.
On ground, when pressed the electrical network of the aircraft supplies the
FADEC when:
‐ The ENG FIRE pb-sw is not pressed,
‐ The FADEC alternator does not supply the FADEC.
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MAINTENANCE PANEL
Intentionally left blank
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AIRCRAFT SYSTEMS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - ENGINE DISPLAY
ENGINE/WARNING DISPLAY
Applicable to: ALL
Ident.: DSC-70-90-40-50-00017843.0003001 / 12 OCT 16
Engine/Warning Display
Ident.: DSC-70-90-40-50-00017845.0001001 / 21 MAR 16
A FLOOR INDICATION
L2
The alpha floor protection is active.
For more information, Refer to DSC-22_30-90 A/THR Modes - ALPHA FLOOR
Ident.: DSC-70-90-40-50-00017846.0001001 / 21 MAR 16
THRUST RATING MODE AND THRUST LIMIT VALUE
Indicates the thrust limit value and the associated thrust rating mode based on:
‐
‐
‐
‐
The position of the thrust levers,
Aircraft on ground or in flight,
The engine status, i.e. running or not running,
The data entered in the T.O and CLB panels of the FMS ACTIVE/PERF page.
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CONTROLS AND INDICATORS - ENGINE DISPLAY
FLIGHT CREW
OPERATING MANUAL
Ident.: DSC-70-90-40-50-00017847.0003001 / 21 MAR 16
Ident.: DSC-70-90-40-50-00018201.0001001 / 21 MAR 16
THRUST RATING MODE
The thrust rating modes are:
TOGA
: Takeoff or go-around (TOGA) thrust rating mode is selected.
MCT
: Maximum Continuous Thrust (MCT) rating mode is selected.
CLB
: Climb (CLB) thrust rating mode is selected.
FLX
: Flexible (FLX) takeoff thrust rating mode is selected.
DCLB
: Derated Climb (DCLB) thrust rating mode is selected.
D04
: Derated Takeoff thrust rating mode is selected.
There are several levels of derated takeoff: D04, D08, D12, D16, D20, ...
GA SOFT
: Go-around Soft (GA SOFT) thrust rating mode is selected.
MREV
: Maximum Reverse (MREV) thrust rating mode is selected.
Ident.: DSC-70-90-40-50-00018203.0001001 / 21 MAR 16
THRUST LIMIT VALUE
L2
N1 value
: Indicates the N1 limit value associated with the thrust rating mode.
The thrust limit value disappears when the thrust reversers are selected.
Ident.: DSC-70-90-40-50-00017849.0001001 / 21 MAR 16
FLEX TEMPERATURE
Cyan
:
Dashes in cyan
:
Indicates the flexible temperature that the flight crew entered in the T.O
panel of the FMS PERF page, when the FLX rating mode is selected
Indicates that the Static Air Temperature is above the flexible
temperature.
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - ENGINE DISPLAY
Ident.: DSC-70-90-40-50-00018209.0001001 / 21 MAR 16
IDLE INDICATION
Both engines are at idle speed, and the aircraft is in flight.
Pulses during 10 s, and then remains steady.
L2
Ident.: DSC-70-90-40-50-00018210.0001001 / 21 MAR 16
AVAIL INDICATION
The engine is started, and at or above idle.
On ground, appears steady during 10 s after a successful start. In flight, pulses during 1 min after
a successful relight.
The AVAIL Indication disappears when the flight crew moves the thrust lever forward the idle
detent.
L2
Ident.: DSC-70-90-40-50-00018211.0001001 / 21 MAR 16
REV INDICATION
L12
REV in green :
On ground, the thrust reverser system is fully deployed.
REV in amber :
The thrust reverser system is unlocked.
In flight, the REV indication pulses during 9 s and then remains steady.
Ident.: DSC-70-90-40-50-00018213.0001001 / 21 MAR 16
EGT INDICATOR
Ident.: DSC-70-90-40-50-00018216.0002001 / 21 MAR 16
CURRENT EGT
L12
Green
:
The current EGT is in normal range.
The scale goes from 0 °C to 1 000 °C.
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FLIGHT CREW
OPERATING MANUAL
Amber
Red
:
:
CONTROLS AND INDICATORS - ENGINE DISPLAY
The current EGT exceeds the EGT amber limit.
The current EGT exceeds the EGT red limit.
Ident.: DSC-70-90-40-50-00018218.0003001 / 21 MAR 16
EGT LIMIT
L2
The amber line indicates the maximum EGT (i.e. the EGT limit).
The maximum EGT is:
‐ 725 °C, during the engine start sequence on ground, or
‐ 915 °C, in all other cases.
The EGT limit does not appear:
‐ When a takeoff or a go-around mode is selected, or
‐ When the thrust reversers are selected, or
‐ If the alpha floor protection is activated.
Ident.: DSC-70-90-40-50-00018219.0001001 / 21 MAR 16
EGT EXCEEDANCE
The EGT exceedance is the highest value that the EGT reached.
The EGT exceedance appears when:
‐ The current EGT exceeds the EGT red limit, or
‐ The EGT exceeded the EGT red limit.
L2
The red mark no longer appears at the next engine start sequence on ground, or after a
maintenance action.
Ident.: DSC-70-90-40-50-00018220.0003001 / 21 MAR 16
EGT RED LINE
L2
The EGT red line appears between the EGT red limit and the end of the scale.
The EGT red limit is 950 °C.
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - ENGINE DISPLAY
Ident.: DSC-70-90-40-50-00018228.0001001 / 21 MAR 16
N1 INDICATOR
Ident.: DSC-70-90-40-50-00018229.0003001 / 04 JUL 17
CURRENT N1
L12
L12
Green
Amber
:
:
The current N1 is in normal range.
The current N1 exceeds the N1 limit.
Red
:
The current N1 exceeds the N1 red limit.
N1 red limit is 104 %.
Dashed
:
The accuracy of the N1 measurement is degraded.
Two amber dashes appear over the last digit.
Ident.: DSC-70-90-40-50-00018231.0001001 / 21 MAR 16
N1 TREND
The green triangle indicates the direction of the N1 trend, when the A/THR mode is active.
Ident.: DSC-70-90-40-50-00018232.0001001 / 21 MAR 16
N1 COMMAND
Indicates the N1 target, when the A/THR mode is active.
Ident.: DSC-70-90-40-50-00018233.0001001 / 21 MAR 16
TRANSIENT N1
The four green arcs indicate the difference between the N1 command and the current N1 , when
the A/THR is active.
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AIRCRAFT SYSTEMS
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FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - ENGINE DISPLAY
Ident.: DSC-70-90-40-50-00018235.0001001 / 21 MAR 16
THRUST LEVER POSITION
The blue circle indicates the position of the thrust lever.
In manual mode, the blue circle corresponds to the N1 value reached after the stabilization of
the engine parameters.
Ident.: DSC-70-90-40-50-00018236.0001001 / 21 MAR 16
N1 LIMIT
L2
The amber mark indicates the N1 limit.
This corresponds to the maximum N1 value when the thrust levers are in TO/GA detent.
Ident.: DSC-70-90-40-50-00018237.0001001 / 21 MAR 16
N1 EXCEEDANCE
L2
The N1 exceedance is the highest value that the N1 reached.
The N1 exceedance appears when the current N1 exceeds the N1 red limit.
The N1 exceedance remains even if the N1 value decreases below the N1 red limit.
The red mark no longer appears at the next engine start sequence on ground, or after a
maintenance action.
Ident.: DSC-70-90-40-50-00018238.0003001 / 21 MAR 16
N1 RED LINE
L2
The N1 red line appears between the N1 red limit and the end of the scale.
The N1 red limit is 104 %.
Ident.: DSC-70-90-40-50-00018239.0002001 / 21 MAR 16
N2
L12
L12
In a grey box :
Green:
:
The engine start sequence or the crank process is in progress.
N2 is in normal range.
Red
:
N2 exceeds the N2 red limit.
N2 red limit is 105 %.
A red cross appears.
The red cross no longer appears at the next engine start sequence on
ground, or after a maintenance action.
Dashed
:
The accuracy of the N2 measurement is degraded.
Two amber dashes appear over the last digit.
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ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - ENGINE DISPLAY
Ident.: DSC-70-90-40-50-00018243.0001001 / 21 MAR 16
FUEL FLOW
Green
Note:
:
The fuel flow is normal.
If the system detects a discrepancy between the N1 , N2 , EGT and fuel flow values
on the FADEC -DMC bus and the corresponding displayed values, an amber CHECK
appears underneath the affected parameter.
Ident.: DSC-70-90-40-50-00018244.0001001 / 21 MAR 16
THRUST BUMP INDICATION
Green
Amber
:
:
Cyan
:
Indicates that the thrust bump is engaged.
When on the ground, indicates that the thrust bump is selected but not
engaged.
When on the ground, Indicates that the thrust bump is selected.
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ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - ENGINE DISPLAY
ENG SD PAGE
Applicable to: ALL
Ident.: DSC-70-90-40-60-00018259.0006001 / 21 MAR 16
ENG SD page
Ident.: DSC-70-90-40-60-00018230.0001001 / 21 MAR 16
FUEL USED INDICATION
L12
Green
:
Indicates the fuel used by each engine.
This value automatically resets on ground, at the next engine start.
Appears in multiples of 10 kg (20 lb).
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L12
Dashed
:
CONTROLS AND INDICATORS - ENGINE DISPLAY
The value accuracy is degraded.
Two amber dashes appear over all five digits.
This occurs when the Fuel Flow is not valid in flight, for more than 1 min.
Ident.: DSC-70-90-40-60-00018260.0001001 / 21 MAR 16
FUEL FILTER CLOG INDICATION
Indicates that the pressure loss across the fuel filter is excessive.
Ident.: DSC-70-90-40-60-00018262.0002001 / 22 MAR 16
OIL QUANTITY
L12
Green
:
Pulses green :
The oil quantity is in normal range.
The scale goes from 0 to 22 QT.
The oil quantity goes below the oil advisory limit (3 QT), that corresponds to the
amber mark.
The needle and the oil quantity value pulse green.
The indication pulses, when oil quantity goes below 3.25 QT , and remains
pulsing as long as oil quantity is below 4.75 QT.
Ident.: DSC-70-90-40-60-00018261.0002001 / 21 MAR 16
OIL PRESSURE
L12
L12
Green
:
Pulses green :
The oil pressure is in normal range.
The scale goes from 0 to 100 PSI.
The oil pressure is:
‐ Above the upper advisory limit, or
The upper advisory limit is 90 PSI.
The oil pressure stops pulsing when oil pressure goes below 85 PSI.
‐ Between the upper red threshold and the lower advisory limit, when N2 is
above 75 %.
L12
The advisory limit is 16 PSI.
The oil pressure stops pulsing, when oil pressure goes below 20 PSI.
Red
:
The oil pressure is in the red range.
The red range is between 0 and 13 PSI.
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ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - ENGINE DISPLAY
Ident.: DSC-70-90-40-60-00018263.0002001 / 21 MAR 16
OIL TEMPERATURE
Green
:
Pulses green :
Amber
:
The oil temperature is in normal range.
The oil temperature is between 140 °C and 155 °C for less than 15 min.
The oil temperature is:
‐ Between 140 °C and 155 °C for more than 15 min, or
‐ Above 155 °C.
Ident.: DSC-70-90-40-60-00018266.0001001 / 21 MAR 16
OIL FILTER CLOG INDICATION
Indicates that the pressure loss across the oil filter is excessive.
Ident.: DSC-70-90-40-60-00018267.0001001 / 21 MAR 16
N1 , N2 VIBRATIONS
Green
:
Pulses green :
The vibration of the LP (HP) rotor is in normal range.
The level of LP (HP) rotor vibration is excessive.
Ident.: DSC-70-90-40-60-00018268.0002001 / 21 MAR 16
STARTING SEQUENCE INDICATION
Ident.: DSC-70-90-40-60-00018269.0001001 / 21 MAR 16
IGNITION INDICATION
:
The igniter A (B) is used for the engine start sequence.
:
Both igniters A and B are used for the engine start sequence or continuous
ignition.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
DSC-70-90-40 P 10/12
05 SEP 17
AIRCRAFT SYSTEMS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - ENGINE DISPLAY
Ident.: DSC-70-90-40-60-00018270.0001001 / 21 MAR 16
START VALVE
:
The engine start valve is fully closed.
:
The engine start valve is fully open.
Ident.: DSC-70-90-40-60-00018271.0001001 / 21 MAR 16
STARTER INLET PRESSURE
Green
Amber
:
:
The starter inlet pressure is normal.
The starter inlet pressure is either:
‐ Abnormally high, or
‐ Abnormally low (below 21 PSI, when N2 is above 10 % and the starter
valve is not closed).
Ident.: DSC-70-90-40-60-00018272.0006001 / 21 MAR 16
NACELLE TEMPERATURE INDICATION
L12
The nacelle temperature indication appears when the nacelle temperature of at least one engine
goes above the advisory limit if not during the start sequence.
Green
: The nacelle temperature is normal.
Pulses green :
The nacelle temperature goes above the advisory limit.
The advisory limit is 240 °C.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
DSC-70-90-40 P 11/12
05 SEP 17
AIRCRAFT SYSTEMS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - ENGINE DISPLAY
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-70-90-40 P 12/12
05 SEP 17
AIRCRAFT SYSTEMS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MEMO DISPLAY
MEMO DISPLAY
Applicable to: ALL
Ident.: DSC-70-90-50-A-00018777.0001001 / 13 MAY 16
IGNITION
:
This memo appears in green when continuous ignition is activated on any engine.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
DSC-70-90-50 P 1/2
24 JAN 17
AIRCRAFT SYSTEMS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CONTROLS AND INDICATORS - MEMO DISPLAY
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
DSC-70-90-50 P 2/2
24 JAN 17
PROCEDURES
Intentionally left blank
PROCEDURES
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TABLE OF CONTENTS
PRO-ABN Abnormal and Emergency Procedures
PRO-NOR Normal Procedures
PRO-SPO Special Operations
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-PLP-TOC P 1/2
05 SEP 17
PROCEDURES
PRELIMINARY PAGES
A318/A319/A320/A321
TABLE OF CONTENTS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-PLP-TOC P 2/2
05 SEP 17
PROCEDURES
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
M
(1)
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU Title
DU identification
DU date
PRO-ABNSystem Reset Table
NG01118
ABN-RESET
PRO-ABNSystem Reset Table - AIR
00021167.0001001
20 MAR 17
ABN-RESET
Criteria: K10463, K6443, K9458
Applicable to: ALL
Impacted DU: 00021069 System Reset Table - AIR
Reason for issue:
The TDU is issued to provide the ACSC C/B reset procedure to apply in the case of "PACK 1(2) REGUL FAULT"
triggered on ground for aircraft equipped with ACSC 1803B0000-02.
PRO-ABNSystem Reset Table - WHEEL
00021059.0001001
20 MAR 17
ABN-RESET
Criteria: SA
Applicable to: ALL
Impacted DU: 00021058 System Reset Table - WHEEL
Reason for issue:
The BSCU reset procedure for WHEEL N/W STRG FAULT is amended with a temporary procedure, in order to
better address the spurious alerts that are currently encountered in-service.
‐ Under the very specific conditions defined in the procedure, the flight crews can continue the flight without
troubleshooting after a successful BSCU reset.
‐ For aircraft with BSCU standard 10: The root cause of the spurious alerts that were triggered during taxiing with
BSCU standard 10 has been cancelled. Therefore, the associated reset procedure has been removed.
PRO-ABN-FWS
[QRH] Multiple Undue ECAM Alerts
Criteria: P8671, P9824
Applicable to: ALL
Impacted DU: NONE
Reason for issue:
This TDU was re-issued to update the list of possible undue ECAM alerts.
This TDU is cancelled with the EIS2 S8-2 Standard (MP P10527)
PRO-ABN-NAV
NAV TCAS FAULT
PRO-ABN-NAV
NAV TCAS FAULT
Criteria: 31-1373, 31-1414, P2590, P5669
Applicable to: ALL
Impacted DU: 00012434 NAV TCAS FAULT (If Installed)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
00012928.0001001
17 MAR 17
NG01075
00015480.0017001
14 FEB 14
Continued on the following page
PRO-PLP-LETDU P 1/6
05 SEP 17
PROCEDURES
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
M
(1)
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
Continued from the previous page
Localization
DU Title
DU identification
DU date
Reason for issue:
Following the introduction of a TCAS monitoring function in the Flight Warning Computer (FWC ) F6 and F7, an
issue has been detected on aircraft equipped with HONEYWELL TCAS computers.
To operate, the TCAS needs to receive the ADR barometric altitude through the active transponder and the aircraft
heading through IR1.
As a consequence, on ground, an undue NAV TCAS FAULT alert is triggered when:
‐ The ADIRUs are set to OFF or,
‐ IR 1 is not aligned: at aircraft power up before IR 1 alignment or during transit when performing a fast or a
complete alignment of IR1.
As soon as the ADIRU s are powered and the IR 1 is aligned, the NAV TCAS FAULT automatically disappears.
Therefore, on ground, if the alert is triggered while the ADIRU s are OFF, or while IR1 is not yet aligned, the flight
crew can disregard the alert.
The FWC F8 corrects the issue.
PRO-NOR-SOP-10
Taxi
NG00715
PRO-NOR-SOP-10
Radar
00015299.0002001
03 AUG 17
Criteria: 34-1443, P7929
Applicable to: ALL
Impacted DU: 00015298 Taxi - Radar
Reason for issue:
When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft.
In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on
and below aircraft path.
At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some
cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the
aircraft descends closer to the precipitation level.
Therefore, this Temporary Revision is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN
should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if:
‐ If the weather is good, or not significant, in order to check that the radar is operating correctly: down tilt until
displaying ground echoes
‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual
tilt according to standard technique
‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of
suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until
the weather is detected or the ground clutter appears on the upper part of the display.
In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual
gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases,
ground clutter may also be displayed as a result of low settings and/or increased gain.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-PLP-LETDU P 2/6
05 SEP 17
PROCEDURES
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
M
(1)
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
Continued from the previous page
Localization
DU Title
DU identification
DU date
PRO-NOR-SOP-14
Climb
NG00723
PRO-NOR-SOP-14
Climb - Initial Climb
00013057.0006001
29 JUN 16
Criteria: P3379, P7425, P9207, SA
Applicable to: ALL
Impacted DU: 00010245 Climb - Initial Climb
Reason for issue:
Issue 2:
The temporary information is reissued to provide more information concerning BPS issue in line with EASA SIB
2016-05.
Issue 1:
The temporary revision is issued to advise operators that above the transition level, when the flight crew selects
"STD" on the FCU, the last QNH or QFE barometric pressure setting is transmitted to the ground, instead of the
standard pressure value (1 013 hPa ).
Only the FCU selected altitude, if used by the ATC on ground, may be misinterpreted. The real aircraft altitude
transmitted to the ground is not affected, because the standard barometric altitude is transmitted, regardless of the
barometric setting selected on the FCU.
In addition, the "STD" value is correctly transmitted to other aircraft systems.
PRO-NOR-SOP-14
Climb - Radar
00013047.0003001
03 MAR 14
Criteria: 34-1443, P7929, SA
Applicable to: ALL
Impacted DU: 00010259 Climb - Radar
Reason for issue:
When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft.
In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on
and below aircraft path.
At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some
cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the
aircraft descends closer to the precipitation level.
Therefore, this Temporary Revision is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN
should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if:
‐ If the weather is good, or not significant, in order to check that the radar is operating correctly: down tilt until
displaying ground echoes
‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual
tilt according to standard technique
‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of
suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until
the weather is detected or the ground clutter appears on the upper part of the display.
In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual
gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases,
ground clutter may also be displayed as a result of low settings and/or increased gain.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-PLP-LETDU P 3/6
05 SEP 17
PROCEDURES
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
M
(1)
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
Continued from the previous page
Localization
DU Title
DU identification
DU date
PRO-NOR-SOP-15
Cruise
NG00734
PRO-NOR-SOP-15
Cruise - Radar Tilt
00013068.0006001
20 SEP 16
Criteria: 34-1443, P7929, SA
Applicable to: ALL
Impacted DU: 00010291 Cruise - Radar Tilt
Reason for issue:
When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft.
In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on
and below aircraft path.
At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some
cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the
aircraft descends closer to the precipitation level.
Therefore, this Temporary Revision is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN
should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if:
‐ The weather is good, or not significant, in order to check that the radar is operating correctly: down tilt until
displaying ground echoes
‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual
tilt according to standard technique
‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of
suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until
the weather is detected or the ground clutter appears on the upper part of the display.
In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual
gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases,
ground clutter may also be displayed as a result of low settings and/or increased gain.
PRO-NOR-SOP-16
Descent Preparation
PRO-NOR-SOP-16
Descent PREPARATION - Radar
Criteria: 34-1443, P7929, SA
Applicable to: ALL
Impacted DU: 00011545 Descent Preparation - Radar
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
NG00916
00013353.0003001
03 MAR 14
Continued on the following page
PRO-PLP-LETDU P 4/6
05 SEP 17
PROCEDURES
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
M
(1)
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
Continued from the previous page
Localization
DU Title
DU identification
DU date
Reason for issue:
When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft.
In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on
and below aircraft path.
At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some
cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the
aircraft descends closer to the precipitation level.
Therefore, this Temporary Revision is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN
should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if:
‐ If the weather is good, or not significant, in order to check that the radar is operating correctly: down tilt until
displaying ground echoes
‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual
tilt according to standard technique
‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of
suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until
the weather is detected or the ground clutter appears on the upper part of the display.
In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual
gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases,
ground clutter may also be displayed as a result of low settings and/or increased gain.
PRO-NOR-SOP-18-B Initial Approach
PRO-NOR-SOP-18-B Initial Approach - Radar
Criteria: 34-1443, P7929, SA
Applicable to: ALL
Impacted DU: 00014647 Initial Approach - Radar
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
NG01260
00014648.0003001
03 MAR 14
Continued on the following page
PRO-PLP-LETDU P 5/6
05 SEP 17
PROCEDURES
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
M
(1)
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
Continued from the previous page
Localization
DU Title
DU identification
DU date
Reason for issue:
When in the AUTO position, the MultiScan AUTO mode adjusts the tilt according to the altitude of the aircraft.
In cruise, MULTISCAN function provides a large view of the weather ahead, ie display of weather cells located on
and below aircraft path.
At low altitudes (below FL 200), the tilt is adjusted upward to manage clutter from strong ground targets. In some
cases, the weather may be low-lying and therefore may be below the radar beam and not be displayed until the
aircraft descends closer to the precipitation level.
Therefore, this Temporary Revision is issued to indicate that, when the Multiscan is in the AUTO position, the GAIN
should be manually set to +4 when the aircraft is below FL 200.
In addition, the flight crew should temporarily set the MULTISCAN sw to MAN, if:
‐ If the weather is good, or not significant, in order to check that the radar is operating correctly: down tilt until
displaying ground echoes
‐ The weather display is ambiguous or unexpected, in order to better analyze the weather situation using manual
tilt according to standard technique
‐ In particular below FL 200, for situations with low-level weather, weather with low reflectivity or in front of
suspected active cells, the flight crew should switch to Manual mode and adjust the tilt setting downward until
the weather is detected or the ground clutter appears on the upper part of the display.
In addition, the flight crew may increase the manual gain control to display lower reflectivity targets. The manual
gain control can be increased in both AUTO and Manual modes to display lower levels of weather. In both cases,
ground clutter may also be displayed as a result of low settings and/or increased gain.
(1) Evolution code : N=New, R=Revised, E=Effectivity
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-PLP-LETDU P 6/6
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY
PROCEDURES
Intentionally left blank
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-ABN-00 INTRODUCTION
Content.....................................................................................................................................................................A
Procedure Layout.....................................................................................................................................................B
Abnormal and Emergency Callouts.........................................................................................................................C
PRO-ABN-ABN-ADV [ADV] ECAM ADVISORY
ECAM Advisory Conditions..................................................................................................................................... A
PRO-ABN-ABN-MEM [MEM] MEMORY ITEMS
[MEM] Memory Items.............................................................................................................................................. A
PRO-ABN-ABN-QRH [QRH] PROCEDURES
[QRH] Procedures....................................................................................................................................................A
PRO-ABN-ABN-RESET [RESET] SYSTEM RESET
System Reset - General..........................................................................................................................................A
System Reset Table................................................................................................................................................ B
PRO-ABN-A-ICE A-ICE
[QRH] DOUBLE AOA HEAT FAILURE................................................................................................................... A
ANTI ICE ALL PITOT.............................................................................................................................................. B
ANTI ICE CAPT(F/O) TAT...................................................................................................................................... C
ANTI ICE CAPT + F/O PITOT................................................................................................................................ D
ANTI ICE CAPT + STBY PITOT.............................................................................................................................E
ANTI ICE CAPT PITOT or L(R) STAT or AOA.......................................................................................................F
ANTI ICE CAPT PROBES...................................................................................................................................... G
ANTI ICE ENG 1(2) VALVE CLSD......................................................................................................................... H
ANTI ICE ENG 1(2) VALVE OPEN.......................................................................................................................... I
ANTI ICE F/O + STBY PITOT.................................................................................................................................J
ANTI ICE F/O PITOT or L( R) STAT or AOA.........................................................................................................K
ANTI ICE F/O PROBES.......................................................................................................................................... L
ANTI ICE L + R WINDSHIELD...............................................................................................................................M
ANTI ICE L(R) WINDOW........................................................................................................................................ N
ANTI ICE L(R) WINDSHIELD................................................................................................................................. O
ANTI ICE STBY PITOT or L(R) STAT or AOA.......................................................................................................P
ANTI ICE STBY PROBES...................................................................................................................................... Q
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-PLP-TOC P 1/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
PRO-ABN-AIR AIR
[QRH] Engine 1+2 Bleed Fault................................................................................................................................A
AIR APU BLEED FAULT.........................................................................................................................................B
AIR APU BLEED LEAK...........................................................................................................................................C
AIR BLEED 1(2) OFF..............................................................................................................................................D
AIR COND CTL 1(2) - A(B) FAULT........................................................................................................................E
AIR ENG 1(2) BLEED ABNORM PR...................................................................................................................... F
AIR ENG 1(2) BLEED FAULT................................................................................................................................ G
AIR ENG 1(2) BLEED LO TEMP (OPPOSITE BLEED AVAILABLE)..................................................................... H
AIR ENG 1(2) BLEED LO TEMP (OPPOSITE BLEED NOT AVAILABLE).............................................................. I
AIR ENG 1+2 BLEED LO TEMP.............................................................................................................................J
AIR ENG 1(2) BLEED HI TEMP............................................................................................................................. K
AIR ENG 1(2) BLEED NOT CLSD.......................................................................................................................... L
AIR ENG 1(2) HP VALVE FAULT.......................................................................................................................... M
AIR FWD(AFT) CRG VENT FAULT .............................................................................................................. N
AIR L(R) WING or ENG 1(2) BLEED LEAK...........................................................................................................O
AIR L(R) WNG LEAK DET FAULT......................................................................................................................... P
AIR PACK 1(2) FAULT........................................................................................................................................... Q
AIR PACK 1+2 FAULT............................................................................................................................................R
AIR PACK 1(2) OFF................................................................................................................................................S
AIR PACK 1(2) OVHT............................................................................................................................................. T
AIR PACK 1(2) REGUL FAULT..............................................................................................................................U
AIR X BLEED FAULT..............................................................................................................................................V
PRO-ABN-APU APU
APU AUTO (EMER) SHUT DOWN.........................................................................................................................A
APU FIRE DET FAULT........................................................................................................................................... B
APU FIRE LOOP A(B) FAULT................................................................................................................................C
PRO-ABN-APUF APU FIRE
APU FIRE
.............................................................................................................................................A
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-PLP-TOC P 2/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-AUTO_FLT AUTO FLT
Continued from the previous page
AUTO FLT A/THR LIMITED....................................................................................................................................A
AUTO FLT A/THR OFF...........................................................................................................................................B
AUTO FLT AP OFF
...............................................................................................................................C
AUTO FLT FAC 1(2) FAULT.................................................................................................................................. D
AUTO FLT FAC 1 + 2 FAULT................................................................................................................................ E
AUTO FLT FCU 1(2) FAULT...................................................................................................................................F
AUTO FLT FCU 1 + 2 FAULT................................................................................................................................G
AUTO FLT REAC W/S DET FAULT.......................................................................................................................H
AUTO FLT RUD TRIM 1(2) FAULT......................................................................................................................... I
AUTO FLT RUD TRIM SYS.................................................................................................................................... J
AUTO FLT RUD TRV LIM 1(2)...............................................................................................................................K
AUTO FLT RUD TRV LIM SYS.............................................................................................................................. L
AUTO FLT YAW DAMPER 1(2)............................................................................................................................. M
AUTO FLT YAW DAMPER SYS.............................................................................................................................N
PRO-ABN-AVNCS AVIONICS SMOKE
AVIONICS SMOKE ................................................................................................................................................ A
PRO-ABN-BLEED BLEED
BLEED MONITORING FAULT................................................................................................................................ A
PRO-ABN-BRAKES BRAKES
[MEM] LOSS OF BRAKING
.................................................................................................................. A
[QRH] ASYMMETRIC BRAKING.............................................................................................................................B
[QRH] RESIDUAL BRAKING.................................................................................................................................. C
BRAKES A/SKID N/WS FAULT or ANTI SKID N/WS OFF....................................................................................D
BRAKES ALTN BRK FAULT...................................................................................................................................E
BRAKES ALTN L(R) RELEASED............................................................................................................................F
BRAKES AUTO BRK FAULT..................................................................................................................................G
BRAKES BRK Y ACCU LO PR.............................................................................................................................. H
BRAKES HOT........................................................................................................................................................... I
BRAKES NORM + ALTN FAULT............................................................................................................................ J
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-PLP-TOC P 3/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
BRAKES NORM BRK FAULT................................................................................................................................. K
BRAKES
BRAKES
BRAKES
BRAKES
BRAKES
PARK BRK FAULT ......................................................................................................................... L
PARK BRK LO PR..................................................................................................................................M
PARK BRK ON........................................................................................................................................N
RELEASED..............................................................................................................................................O
SYS 1(2) FAULT......................................................................................................................................P
PRO-ABN-NWS BRAKES-N/WS
BRAKES-N/WS MINOR FAULT.............................................................................................................................. A
PRO-ABN-CAB_PR CAB PR
[QRH] CABIN OVERPRESSURE............................................................................................................................A
CAB PR EXCESS CAB ALT
................................................................................................................. B
CAB PR EXCES RESIDUAL PR
.......................................................................................................... C
CAB PR LDG ELEV FAULT................................................................................................................................... D
CAB PR LO DIFF PR..............................................................................................................................................E
CAB PR OFV NOT OPEN ..................................................................................................................................... F
CAB PR SAFETY VALVE OPEN........................................................................................................................... G
CAB PR SYS 1(2) FAULT...................................................................................................................................... H
CAB PR SYS 1+2 FAULT........................................................................................................................................ I
PRO-ABN-C_B C/B
C/B TRIPPED.......................................................................................................................................................... A
PRO-ABN-COM COM
COM ACARS FAULT ..................................................................................................................................... A
COM CIDS 1 + 2 FAULT........................................................................................................................................ B
COM HF 1(2) DATA FAULT .........................................................................................................................C
COM SATCOM DATA FAULT ....................................................................................................................... D
COM SATCOM FAULT .................................................................................................................................E
COM SINGLE PTT STUCK ............................................................................................................................F
COM VHF 1(2)(3) /HF 1(2) EMITTING ..........................................................................................................G
COM VHF 3 DATA FAULT ...........................................................................................................................H
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-PLP-TOC P 4/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-COND COND
Continued from the previous page
COND FWD CAB/AFT CAB/CKPT DUCT OVHT................................................................................................... A
COND FWD(AFT) CARGO DUCT OVHT ......................................................................................................B
COND FWD(AFT) CRG HEAT FAULT ..........................................................................................................C
COND FWD(AFT) CRG ISOL VALVE ........................................................................................................... D
COND HOT AIR FAULT..........................................................................................................................................E
COND L+R CAB FAN FAULT.................................................................................................................................F
COND LAV + GALLEY FAN FAULT...................................................................................................................... G
COND TRIM AIR SYS FAULT................................................................................................................................H
PRO-ABN-CONFIG CONFIG
CONFIG L(R) SIDESTICK FAULT (BY TAKE OVER)
.......................................................................... A
CONFIG PARK BRK ON
.......................................................................................................................B
CONFIG PITCH TRIM NOT IN T.O RANGE
........................................................................................ C
CONFIG RUD TRIM NOT IN T.O RANGE
........................................................................................... D
CONFIG SLATS (FLAPS) NOT IN T.O CONFIG
..................................................................................E
CONFIG SPD BRK NOT RETRACTED
................................................................................................ F
PRO-ABN-DATALINK DATALINK
DATALINK ATSU FAULT........................................................................................................................................ A
DATALINK COMPANY FAULT................................................................................................................................B
PRO-ABN-DOOR DOOR
[QRH] COCKPIT DOOR FAULT............................................................................................................................. A
DOOR L(R)(FWD)(AFT) AVIONICS (IN FLIGHT)...................................................................................................B
DOOR L(R)(FWD)(AFT) AVIONICS (ON GROUND)..............................................................................................C
DOOR L(R) FWD(AFT) CABIN (IN FLIGHT)..........................................................................................................D
DOOR L(R) FWD(AFT) CABIN (ON GROUND)..................................................................................................... E
DOOR L(R) FWD(AFT) EMER EXIT (IN FLIGHT)..................................................................................................F
DOOR L(R) FWD(AFT) EMER EXIT (ON GROUND)............................................................................................ G
DOOR FWD(AFT)(BULK) CARGO (IN FLIGHT).................................................................................................... H
DOOR FWD(AFT)(BULK) CARGO (ON GROUND).................................................................................................I
PRO-ABN-EIS EIS
[QRH] Display Unit Failure...................................................................................................................................... A
EIS DMC 1(2)(3) FAULT......................................................................................................................................... B
EIS DMC/FWC COM FAULT.................................................................................................................................. C
Continued on the following page
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PRO-ABN-PLP-TOC P 5/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-ELEC ELEC
Continued from the previous page
[QRH] C/B Tripped.................................................................................................................................................. A
[QRH] ELEC EMER CONFIG SYS REMAINING....................................................................................................B
ELEC AC BUS 1 FAULT.........................................................................................................................................C
ELEC AC BUS 2 FAULT.........................................................................................................................................D
ELEC AC ESS BUS ALTN......................................................................................................................................E
ELEC AC ESS BUS FAULT....................................................................................................................................F
ELEC AC ESS BUS SHED.....................................................................................................................................G
ELEC APU GEN FAULT......................................................................................................................................... H
ELEC BAT 1(2) FAULT............................................................................................................................................ I
ELEC BAT 1(2) OFF................................................................................................................................................J
ELEC BCL 1(2) FAULT........................................................................................................................................... K
ELEC DC BAT BUS FAULT.................................................................................................................................... L
ELEC DC BUS 1 FAULT........................................................................................................................................M
ELEC DC BUS 2 FAULT........................................................................................................................................ N
ELEC DC BUS 1+2 FAULT.................................................................................................................................... O
ELEC DC EMER CONFIG...................................................................................................................................... P
ELEC DC ESS BUS FAULT................................................................................................................................... Q
ELEC DC ESS BUS SHED.....................................................................................................................................R
ELEC EMER CONFIG
...........................................................................................................................S
ELEC EMER GEN 1 LINE OFF.............................................................................................................................. T
ELEC ESS BUSES ON BAT
.................................................................................................................U
ELEC GEN 1(2) or APU GEN OVERLOAD............................................................................................................V
ELEC GEN 1(2) FAULT......................................................................................................................................... W
ELEC GEN 1(2) OFF.............................................................................................................................................. X
ELEC IDG 1(2) DISCONNECTED.......................................................................................................................... Y
ELEC IDG 1(2) OIL LO PR/OVHT.......................................................................................................................... Z
ELEC STATIC INV FAULT................................................................................................................................... AA
ELEC TR 1(2) FAULT...........................................................................................................................................AB
PRO-ABN-ENG ENG
[QRH] ENG DUAL FAILURE - FUEL REMAINING
..............................................................................A
[QRH] ENG DUAL FAILURE - NO FUEL REMAINING
....................................................................... B
[QRH] ENG RELIGHT IN FLIGHT.......................................................................................................................... C
[QRH] ENGINE TAILPIPE FIRE............................................................................................................................. D
[QRH] HIGH ENGINE VIBRATION......................................................................................................................... E
[QRH] On Ground - Non ENG Shutdown after ENG Master OFF.......................................................................... F
Continued on the following page
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PRO-ABN-PLP-TOC P 6/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
[QRH] One Engine Inoperative - Circling Approach............................................................................................... G
[QRH] One Engine Inoperative - Straight-In Approach...........................................................................................H
ENG 1(2) BLEED STATUS FAULT (IN FLIGHT).....................................................................................................I
ENG 1(2) BLEED STATUS FAULT (ON GROUND)............................................................................................... J
ENG COMPRESSOR VANE................................................................................................................................... K
ENG 1(2) COMPRESSOR VANE............................................................................................................................L
ENG 1(2) CTL VALVE FAULT............................................................................................................................... M
ENG DUAL FAILURE
............................................................................................................................N
ENG 1(2) EIU FAULT............................................................................................................................................. O
ENG 1(2) FADEC A(B) FAULT............................................................................................................................... P
ENG 1(2) FADEC ALTERNATOR.......................................................................................................................... Q
ENG 1(2) FADEC FAULT....................................................................................................................................... R
ENG 1(2) FADEC HI TEMP.................................................................................................................................... S
ENG 1(2) FAIL......................................................................................................................................................... T
ENG 1(2) FIRE (IN FLIGHT)
............................................................................................................... U
ENG 1(2) FIRE (ON GROUND)
............................................................................................................ V
ENG 1(2) FIRE DET FAULT.................................................................................................................................. W
ENG 1(2) FIRE LOOP A(B) FAULT........................................................................................................................X
ENG 1(2) FUEL CTL FAULT.................................................................................................................................. Y
ENG 1(2) FUEL FILTER CLOG.............................................................................................................................. Z
ENG 1(2) FUEL RETURN VALVE........................................................................................................................AA
ENG 1(2) HP FUEL VALVE..................................................................................................................................AB
ENG 1(2) IGN FAULT (IGN A or B Fault)............................................................................................................AC
ENG 1(2) IGN FAULT (IGN A+B FAULT)............................................................................................................ AD
ENG 1(2) LOW N1 (On Ground).......................................................................................................................... AE
ENG 1(2) N1 or N2 or EGT or FF DISCREPANCY............................................................................................. AF
ENG 1(2) N1/N2/EGT OVER LIMIT..................................................................................................................... AG
ENG 1(2) OIL FILTER CLOG...............................................................................................................................AH
ENG 1(2) OIL HI TEMP......................................................................................................................................... AI
ENG 1(2) OIL LO PR
.......................................................................................................................... AJ
ENG 1(2) ONE TLA FAULT..................................................................................................................................AK
ENG 1(2) OVSPD PROT FAULT..........................................................................................................................AL
ENG 1(2) PROBES FAULT..................................................................................................................................AM
ENG 1(2) REV ISOL FAULT................................................................................................................................ AN
ENG 1(2) REV PRESSURIZED........................................................................................................................... AO
ENG REV SET...................................................................................................................................................... AP
ENG 1(2) REV SWITCH FAULT.......................................................................................................................... AQ
Continued on the following page
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PRO-ABN-PLP-TOC P 7/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
1(2) REVERSE UNLOCKED....................................................................................................................... AR
1(2) REVERSER FAULT..............................................................................................................................AS
1(2) SENSOR FAULT.................................................................................................................................. AT
1(2) SHUT DOWN....................................................................................................................................... AU
1(2) STALL................................................................................................................................................... AV
1(2) START FAULT.....................................................................................................................................AW
1(2) START VALVE FAULT.........................................................................................................................AX
ENG 1(2) THR LEVER ABV IDLE
...................................................................................................... AY
ENG 1(2) THR LEVER DISAGREE...................................................................................................................... AZ
ENG 1(2) THR LEVER FAULT.............................................................................................................................BA
ENG THR LEVERS NOT SET..............................................................................................................................BB
ENG THRUST LOCKED.......................................................................................................................................BC
ENG TYPE DISAGREE........................................................................................................................................ BD
ENG VIB SYS FAULT...........................................................................................................................................BE
ENG
ENG
ENG
ENG
ENG
ENG
ENG
PRO-ABN-F_CTL F/CTL
[QRH] Landing with Slats or Flaps Jammed...........................................................................................................A
[QRH] RUDDER JAM.............................................................................................................................................. B
[QRH] STABILIZER JAM.........................................................................................................................................C
ACTIVE CONTROL LAW........................................................................................................................................ D
ELEVATORS AND STABILIZER CONTROL AFTER FAILURE............................................................................. E
F/CTL AIL SERVO FAULT...................................................................................................................................... F
F/CTL ALTN LAW................................................................................................................................................... G
F/CTL DIRECT LAW............................................................................................................................................... H
F/CTL ELAC 1(2) FAULT (ONE COMPUTER FAILED)...........................................................................................I
F/CTL ELAC 1(2) FAULT (BOTH COMPUTERS FAILED)..................................................................................... J
F/CTL ELAC 1(2) PITCH FAULT............................................................................................................................ K
F/CTL ELEV SERVO FAULT...................................................................................................................................L
F/CTL FCDC 1(2) FAULT.......................................................................................................................................M
F/CTL FCDC 1+2 FAULT........................................................................................................................................N
F/CTL FLAP ATTACH SENSOR............................................................................................................................ O
F/CTL FLAPS FAULT/LOCKED.............................................................................................................................. P
F/CTL FLAP LVR NOT ZERO
.............................................................................................................. Q
F/CTL FLAP SYS 1(2) FAULT................................................................................................................................R
F/CTL FLAPS/SLATS FAULT/LOCKED..................................................................................................................S
F/CTL GND SPLR 5 FAULT................................................................................................................................... T
F/CTL GND SPLR / 1+2 / 3+4 / FAULT.................................................................................................................U
F/CTL GND SPLR NOT ARMED............................................................................................................................ V
Continued on the following page
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FCOM
PRO-ABN-PLP-TOC P 8/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
F/CTL L(R) AIL FAULT.......................................................................................................................................... W
F/CTL L(R) ELEV FAULT........................................................................................................................................X
F/CTL L+R ELEV FAULT
...................................................................................................................... Y
F/CTL L(R) SIDESTICK FAULT.............................................................................................................................. Z
F/CTL SEC 1(2)(3) FAULT................................................................................................................................... AA
F/CTL SIDESTICK PRIORITY.............................................................................................................................. AB
F/CTL SLAT(FLAP) TIP BRK FAULT...................................................................................................................AC
F/CTL SLATS AND FLAPS FAULT IN CONF 0.................................................................................................. AD
F/CTL SLATS FAULT/LOCKED............................................................................................................................AE
F/CTL SLAT SYS 1(2) FAULT..............................................................................................................................AF
F/CTL SPD BRK 2 (3+4) FAULT......................................................................................................................... AG
F/CTL SPD BRK DISAGREE (SURFACES 3+4 AFFECTED)............................................................................. AH
F/CTL SPD BRK DISAGREE (SURFACES 2+3+4 AFFECTED)...........................................................................AI
F/CTL SPD BRK FAULT....................................................................................................................................... AJ
F/CTL SPD BRK STILL OUT................................................................................................................................AK
F/CTL SPLR FAULT..............................................................................................................................................AL
F/CTL STABILIZER JAM......................................................................................................................................AM
PRO-ABN-FUEL FUEL
[QRH] FUEL IMBALANCE.......................................................................................................................................A
[QRH] FUEL LEAK.................................................................................................................................................. B
[QRH] GRAVITY FUEL FEEDING.......................................................................................................................... C
FUEL ACT XFR FAULT .................................................................................................................................D
FUEL ACT PUMP LO PR .............................................................................................................................. E
FUEL APU LP VALVE FAULT................................................................................................................................ F
FUEL AUTO FEED FAULT.....................................................................................................................................G
FUEL CTR TK PUMP 1(2) LO PR......................................................................................................................... H
FUEL CTR TK PUMPS LO PR................................................................................................................................ I
FUEL CTR TK PUMPS OFF................................................................................................................................... J
FUEL ENG 1(2) LP VALVE OPEN......................................................................................................................... K
FUEL FQI CH 1(2) FAULT...................................................................................................................................... L
FUEL L (R) OUTER (INNER) TK HI TEMP........................................................................................................... M
FUEL L (R) OUTER (INNER) TK LO TEMP.......................................................................................................... N
FUEL L (R) OUTER XFR CLOSED........................................................................................................................O
FUEL L (R) OUTER XFR OPEN.............................................................................................................................P
Continued on the following page
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FCOM
PRO-ABN-PLP-TOC P 9/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
FUEL L (R) TK PUMP 1(2) LO PR........................................................................................................................ Q
FUEL L (R) TK PUMP 1 + 2 LO PR (CENTER TANK EMPTY).............................................................................R
FUEL L (R) TK PUMP 1 + 2 LO PR (CENTER TANK NOT EMPTY)................................................................... S
FUEL L (R) WING TK LO LVL................................................................................................................................T
FUEL L + R WING TK LO LVL.............................................................................................................................. U
FUEL X FEED VALVE FAULT................................................................................................................................V
PRO-ABN-FWS FWS
[QRH] Multiple Undue ECAM Alerts........................................................................................................................A
FWS FWC 1 + 2 FAULT.........................................................................................................................................B
FWS FWC 1(2) FAULT........................................................................................................................................... C
FWS OEB/FWC DISCREPANCY............................................................................................................................D
FWS SDAC 1 + 2 FAULT....................................................................................................................................... E
FWS SDAC 1(2) FAULT..........................................................................................................................................F
PRO-ABN-HYD HYD
HYD B ELEC PUMP LO PR or OVHT................................................................................................................... A
HYD B RSVR LO AIR PR.......................................................................................................................................B
HYD B RSVR LO LVL............................................................................................................................................ C
HYD B RSVR OVHT............................................................................................................................................... D
HYD G ENG 1 PUMP LO PR (PTU OPERATIVE).................................................................................................E
HYD G ENG 1 PUMP LO PR (PTU INOPERATIVE)............................................................................................. F
HYD G RSVR LO AIR PR...................................................................................................................................... G
HYD G RSVR LO LVL............................................................................................................................................ H
HYD G RSVR OVHT................................................................................................................................................ I
HYD Y ELEC PUMP LO PR or OVHT.................................................................................................................... J
HYD Y ENG 2 PUMP LO PR (PTU OPERATIVE)................................................................................................. K
HYD Y ENG 2 PUMP LO PR (PTU INOPERATIVE).............................................................................................. L
HYD Y RSVR LO AIR PR...................................................................................................................................... M
HYD Y RSVR LO LVL............................................................................................................................................ N
HYD Y RSVR OVHT...............................................................................................................................................O
HYD B+Y SYS LO PR
.......................................................................................................................... P
HYD G+B SYS LO PR
..........................................................................................................................Q
HYD G+Y SYS LO PR
..........................................................................................................................R
HYD PTU FAULT.................................................................................................................................................... S
HYD RAT FAULT.....................................................................................................................................................T
Continued on the following page
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PRO-ABN-PLP-TOC P 10/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-LG L/G
Continued from the previous page
[QRH] Landing with Abnormal L/G..........................................................................................................................A
[QRH] L/G GRAVITY EXTENSION......................................................................................................................... B
L/G DOORS NOT CLOSED....................................................................................................................................C
L/G GEAR NOT DOWN
........................................................................................................................ D
L/G GEAR NOT DOWNLOCKED
..........................................................................................................E
L/G GEAR NOT UPLOCKED.................................................................................................................................. F
L/G GEAR UPLOCK FAULT...................................................................................................................................G
L/G LGCIU 1(2) FAULT.......................................................................................................................................... H
L/G LGCIU 1+2 FAULT............................................................................................................................................ I
L/G SHOCK ABSORBER FAULT (SHOCK ABSORBER EXTENDED ON GROUND)........................................... J
L/G SHOCK ABSORBER FAULT (SHOCK ABSORBER NOT EXTENDED AFTER LIFTOFF)............................. K
L/G SYS DISAGREE............................................................................................................................................... L
PRO-ABN-MISC MISC
[MEM] EMER DESCENT
.......................................................................................................................A
[MEM] Stall Recovery
............................................................................................................................B
[MEM] Stall Warning At Lift-Off
.............................................................................................................C
[QRH] BOMB ON BOARD...................................................................................................................................... D
[QRH] COCKPIT WINDSHIELD / WINDOW ARCING............................................................................................E
[QRH] COCKPIT WINDSHIELD / WINDOW CRACKED........................................................................................ F
[QRH] DITCHING
.................................................................................................................................. G
[QRH] EMER EVAC
.............................................................................................................................. H
[QRH] EMER LANDING ALL ENG FAILURE
.........................................................................................I
[QRH] FORCED LANDING
.................................................................................................................... J
[QRH] OVERWEIGHT LANDING............................................................................................................................ K
[QRH] Severe Turbulence........................................................................................................................................L
[QRH] TAILSTRIKE.................................................................................................................................................M
[QRH] VOLCANIC ASH ENCOUNTER ................................................................................................................. N
PRO-ABN-NAV NAV
[MEM] Unreliable Speed Indication......................................................................................................................... A
[QRH] ADR 1+2+3 FAULT...................................................................................................................................... B
[QRH] ADR CHECK PROC.....................................................................................................................................C
[QRH] IR Alignment in ATT Mode.......................................................................................................................... D
NAV ADR 1(2)(3) FAULT........................................................................................................................................ E
NAV ADR 1+2(1+3)(2+3) FAULT............................................................................................................................ F
NAV ADR DISAGREE.............................................................................................................................................G
Continued on the following page
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PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
PRELIMINARY PAGES - TABLE OF CONTENTS
FLIGHT CREW
OPERATING MANUAL
NAV
NAV
NAV
NAV
Continued from the previous page
ALTI DISCREPANCY..................................................................................................................................... H
CAPT(F/O)(STBY) AOA FAULT.......................................................................................................................I
ATT DISCREPANCY....................................................................................................................................... J
BARO REF DISCREPANCY...........................................................................................................................K
NAV
NAV
NAV
NAV
NAV
NAV
NAV
NAV
NAV
NAV
GPS 1(2) FAULT .................................................................................................................................. M
GPWS FAULT.................................................................................................................................................N
GPWS TERR DET FAULT.............................................................................................................................O
HDG DISCREPANCY..................................................................................................................................... P
IAS DISCREPANCY....................................................................................................................................... Q
ILS 1(2)(1+2) FAULT...................................................................................................................................... R
IR 1(2)(3) FAULT............................................................................................................................................ S
IR 1+2(1+3)(2+3) FAULT................................................................................................................................ T
IR DISAGREE.................................................................................................................................................U
IR NOT ALIGNED...........................................................................................................................................V
NAV FM/GPS POS DISAGREE ..................................................................................................................... L
NAV PRED W/S DET FAULT .......................................................................................................................W
NAV RA 1 AND 2 FAULT (DUAL RA FAILURE)....................................................................................................X
NAV RA 1(2) FAULT............................................................................................................................................... Y
NAV RA DEGRADED.............................................................................................................................................. Z
NAV TCAS FAULT ...................................................................................................................................... AA
NAV TCAS STBY..................................................................................................................................................AB
Stall Warning
.......................................................................................................................................AC
PRO-ABN-OVERSPEED OVERSPEED
OVERSPEED
....................................................................................................................................... A
PRO-ABN-RECORDER RECORDER
RECORDER DFDR FAULT.....................................................................................................................................A
RECORDER SYS FAULT....................................................................................................................................... B
PRO-ABN-SMOKE SMOKE
[QRH] SMOKE / FUMES / AVNCS SMOKE
......................................................................................... A
[QRH] REMOVAL OF SMOKE / FUMES
.............................................................................................B
[QRH] SMOKE / FIRE FROM LITHIUM BATTERY................................................................................................C
SMOKE AFT CARGO SMOKE
.................................................................................................... D
SMOKE AFT CRG DET FAULT .................................................................................................................... E
Continued on the following page
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PRO-ABN-PLP-TOC P 12/14
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PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
SMOKE FWD CARGO SMOKE
Continued from the previous page
................................................................................................... F
SMOKE FWD(AFT) CRG BTL 1(2) FAULT ...................................................................................................G
SMOKE FWD CRG DET FAULT ...................................................................................................................H
SMOKE DET FAULT................................................................................................................................................ I
SMOKE LAVATORY DET FAULT........................................................................................................................... J
SMOKE LAVATORY SMOKE
............................................................................................................... K
PRO-ABN-SURV SURV
[MEM] EGPWS Cautions.........................................................................................................................................A
[MEM] EGPWS Warnings
......................................................................................................................B
[MEM] TCAS WARNINGS
.....................................................................................................................C
[MEM] WINDSHEAR
............................................................................................................................. D
[MEM] WINDSHEAR AHEAD
................................................................................................................E
PRO-ABN-VENT VENT
VENT
VENT
VENT
VENT
AVNCS SYS FAULT.....................................................................................................................................A
BLOWER FAULT.......................................................................................................................................... B
EXTRACT FAULT.........................................................................................................................................C
SKIN VALVE FAULT.................................................................................................................................... D
PRO-ABN-WHEEL WHEEL
[QRH] WHEEL TIRE DAMAGE SUSPECTED........................................................................................................A
WHEEL HYD SEL FAULT.......................................................................................................................................B
WHEEL N/W STRG FAULT....................................................................................................................................C
WHEEL TYRE LO PR ................................................................................................................................... D
PRO-ABN-W_A_ICE WING A.ICE
WING A.ICE L(R) HI PR......................................................................................................................................... A
WING A.ICE L(R) VALVE OPEN (FAILURE DETECTED IN FLIGHT)...................................................................B
WING A.ICE L(R) VALVE OPEN (FAILURE DETECTED ON GROUND)..............................................................C
WING A.ICE OPEN ON GND................................................................................................................................. D
WING A.ICE SYS FAULT (ONE WING VALVE REMAINS CLOSED WHEN THE WING ANTI-ICE IS TURNED ON)E
WING A.ICE SYS FAULT (THE WING ANTI-ICE IS TURNED ON AFTER ONE ENGINE SHUTDOWN OR AFTER
THE LOSS OF ONE BLEED)..................................................................................................................................F
Continued on the following page
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PRO-ABN-PLP-TOC P 13/14
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-ABN-90 Detailed Cabin / Cockpit Evacuation Procedure
Continued from the previous page
General.....................................................................................................................................................................A
Cockpit-Assigned Duties for Evacuation................................................................................................................. B
Cabin Crew-Assigned Areas for Evacuation...........................................................................................................C
Communications...................................................................................................................................................... D
On Ground Evacuation............................................................................................................................................ E
Cockpit Evacuation through Window.......................................................................................................................F
Evacuation on Water...............................................................................................................................................G
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PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
INTRODUCTION
FLIGHT CREW
OPERATING MANUAL
CONTENT
Ident.: PRO-ABN-ABN-00-00020862.0001001 / 20 APR 17
Applicable to: ALL
L2
Abnormal and Emergency procedures involve actions that the flight crew must perform to ensure
the overall safety of the flight, and adequate workload.
For more information about the management of abnormal operations, Refer to FCTM/AOP-30-10
Introduction.
Abnormal and Emergency Procedure Overview
L1
L2
L1
L2
L1
L2
[ADV] ECAM ADVISORY
The [ADV ] ECAM ADVISORY section provides direct access to the list of all advisories that can
be displayed on the ECAM SD pages. The [ADV ] section is also available in the QRH.
For more information, Refer to [ADV] ECAM Advisory.
Advisories are system parameters that start to deviate from their usual operational range.
However, an advisory does not require flight crew actions, except monitoring.
For more information about Advisory function, Refer to DSC-31-20 System Pages.
[MEM] MEMORY ITEMS
The [MEM] MEMORY ITEMS menu provides direct access to the list of memory items.
For more information, Refer to [MEM] Memory Items.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-ABN-ABN-00 P 1/10
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PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
INTRODUCTION
FLIGHT CREW
OPERATING MANUAL
L1
L2
L1
L2
L1
The content of the memory items are described in the applicable sub-sections of the abnormal and
emergency procedures.
Memory items are procedures, or critical immediate actions of an ECAM /QRH /OEB procedure,
that the flight crew must apply by memory to ensure a safe flight path. In some time-critical
situations, the flight crew has no time to refer to the ECAM and/or to the QRH.
For more information, Refer to FCTM/AOP-10-40 Abnormal and Emergency Procedures.
[QRH] PROCEDURES
The [QRH ] PROCEDURES menu provides direct access to the list of all the FCOM abnormal and
emergency procedures that are also in the QRH.
For more information, Refer to [QRH] Procedures.
The content of the QRH procedures are described in the applicable sub-sections of the abnormal
and emergency procedures.
Note:
Only the FCOM version of a procedure provides layer 2 and 3 information for
consultation purpose.
[RESET] SYSTEM RESET
L2
L1
The [RESET] SYSTEM RESET section provides direct access to the table listing all the system
resets that are permitted, and the condition to apply them. The [RESET] section is also available in
the QRH.
For direct access to the table, Refer to [RESET] System Reset.
SUB-SECTIONS OF ABNORMAL AND EMERGENCY PROCEDURES
This part of the FCOM describes the detailed content of all abnormal and emergency procedures.
All procedures are grouped in sub-sections that can be system related (e.g. AIR, FUEL, etc.) or
non-system related (e.g. MISC, T.O, CONFIG, etc.).
The sub-sections are sorted by alphabetic order.
For each sub-section, procedures are listed in the following order:
1. The memory items
The title of the memory items starts with the [MEM] prefix
2. The abnormal and emergency procedures of the QRH
The title of these procedures starts with the [QRH] prefix
3. The ECAM procedures.
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PROCEDURE LAYOUT
Applicable to: ALL
Ident.: PRO-ABN-ABN-00-A-00020863.0001001 / 17 MAR 17
GENERAL
The presentation of procedures is, as far as practicable, identical to the way it is displayed on the
ECAM. The abbreviations are identical to those used on the cockpit panels.
All actions and information displayed on ECAM are provided in large letters. Other information, not
on ECAM, is provided in small letters.
Expanded information is as far as practicable provided in layer 2. This information:
‐ Identifies the particular failures
‐ Explains actions for which the reason is not self-evident
‐ Provides some background on the reasons and /or the effects of a given action.
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FCOM presentation of ABN or EMER procedures
Ident.: PRO-ABN-ABN-00-A-00020864.0001001 / 17 MAR 17
PROCEDURE TITLE
The title of an abnormal or emergency procedure, displayed on the ECAM, appears on white
background.
Abnormal procedure displayed on ECAM (amber caution) :
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Emergency procedure displayed on ECAM (red warning) :
The title of an abnormal or emergency procedure, that does not appear on the ECAM is on a grey
background.
Abnormal procedure not displayed on ECAM :
Emergency procedure not displayed on ECAM :
SEVERAL ALERTS UNDER THE SAME TITLE
When applicable, several alerts may be grouped under the same procedure title. However,
depending on the failure, the actions that the flight crew should perform may differ.
Note:
Alerts that have the same procedure title may be differentiated by a subtitle (e.g. ENG
FIRE (On Ground) versus ENG FIRE (In Flight)).
Ident.: PRO-ABN-ABN-00-A-00020865.0001001 / 17 MAR 17
ANNUNCIATIONS
When applicable, the annunciations section provides:
‐ The triggering conditions, that describe the cause of the alert activation
‐ The flight phase inhibition.
FLIGHT PHASE INHIBITION
The Flight Phase Inhibition section indicates the flight phases during which the alert is inhibited.
In the below example, the alert is inhibited in flight phase 1, and 10.
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L2
For more information, Refer to DSC-31-15 Flight Phases.
Ident.: PRO-ABN-ABN-00-A-00020866.0001001 / 17 MAR 17
PROCEDURES AND STATUS
The Procedure and Status section provides the procedure and the Status (including approach
procedure, limitations, inoperative systems, etc.), with additional information when relevant.
CONDITIONS
BLACK SQUARE
When several procedures appear under the same title, a black square marks the starting point
of each procedure.
For example:
Black squares also indicate parts of a procedure among which only one is applicable.
For example:
The ECAM does not display black squares.
BLACK DOT
If an action depends on a precondition, a black dot identifies the precondition. If the precondition
appears on ECAM, it appears in LARGE LETTERS. If not, it appears in small letters.
For example:
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INDENTATION
Indentation is used in order to identify when an action depends on a precondition/flight
phase/procedure.
For example:
‐ The APPR SPEED is equal to VREF +30 kt only if the flaps are locked, because "APPR
SPEED......VREF +30" is indented below "• If flaps locked".
‐ The MAX SPEED of 250 kt does not depend on the flaps locked condition because it is
aligned with "• If Flaps locked". Therefore, MAX SPEED has to be respected whether the
flaps are locked or not.
MEMORY ITEMS
Memory items are items that the flight crew must memorize, in order to be able to rapidly apply
them, without referring to the ECAM , and/or to the QRH.
Memory items are surrounded by a black box in the FCOM /QRH procedure , in order to enable
the flight crew to easily identify them.
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Memory items
ABNORMAL AND EMERGENCY CALLOUTS
Applicable to: ALL
Ident.: PRO-ABN-ABN-00-B-00011915.0001001 / 17 MAR 17
ECAM PROCEDURES
1. "ECAM ACTION" is commanded by PF when required.
2. "CLEAR __ (title of the system) ?" is asked by the PM for confirmation by the PF, that all actions
have been taken/reviewed on the present WARNING/CAUTION or SYSTEM PAGE. e.g.:
CLEAR HYDRAULIC ?
3. "CLEAR __ (title of the system)" is the command by the PF that the action and review is
confirmed. For status page; REMOVE STATUS will be used.
4. "ECAM ACTIONS COMPLETE" is the announcement by the PM that all APPLICABLE
ACTIONS have been completed.
5. Should the PF require an action from the PM during ECAM procedures, the order "STOP
ECAM" will be used. When ready to resume the ECAM the order "CONTINUE ECAM" will be
used.
Ident.: PRO-ABN-ABN-00-B-00020059.0001001 / 17 MAR 17
EMERGENCY CALL
Some abnormal/emergency procedures require flight and cabin crews to use specific phraseology
when communicating with each other. To ensure effective communication between the flight and
cabin crews, the standard phraseology may be recalled at the preflight phase.
FROM
cockpit
TO
cabin
Cockpit
Cabin
cockpit
cabin
PHRASEOLOGY
REMARKS
Passenger Address (PA) System:
The Purser, or any other cabin
"PURSER TO COCKPIT, PLEASE!"
crewmember, must go to the cockpit
Passenger Address (PA) System:
An emergency evacuation may soon be required.
"ATTENTION CREW! AT STATIONS!"
Passenger Address (PA) System:
The captain decides that an
"CABIN CREW and PASSENGERS
evacuation is not required
REMAIN SEATED!"
Continued on the following page
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INTRODUCTION
FLIGHT CREW
OPERATING MANUAL
cockpit
cabin
cabin
cockpit
Passenger Address (PA) System:
"PASSENGERS EVACUATE!"
Interphone:
"PRIO CAPT"
Continued from the previous page
The captain orders an immediate evacuation
Any crew member can make such
a call. The flight crew must reply.
Ident.: PRO-ABN-ABN-00-B-00011916.0001001 / 31 AUG 17
MEMORY ITEMS
The aim of such callouts is to callout the appropriate procedure by calling out, in most cases,
the title of the procedure. This will allow the crew to be aware of the situation and be prepared to
properly react (crew coordination, task sharing and communication).
GPWS
As soon as avoidance manoeuver is envisaged.
"PULL UP TOGA"
REACTIVE WINDSHEAR
"WINDSHEAR TOGA"
UNRELIABLE SPEED INDICATION
"UNRELIABLE SPEED"
TCAS
For aircraft equipped with AP/FD TCAS function :
As soon as a Traffic Advisory (TA) is triggered:
‐ If the AP/FD TCAS mode is armed : "TCAS blue"
‐ If the AP/FD TCAS mode does not arm : "TCAS, I have control"
For aircraft not equipped with AP/FD TCAS function :
As soon as a Traffic Advisory (TA) is triggered: "TCAS, I have control".
EMERGENCY DESCENT
"EMERGENCY DESCENT"
LOSS OF BRAKING
"LOSS OF BRAKING"
STALL RECOVERY
As soon as any stall indication is recognized.
"STALL, I have control"
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STALL WARNING AT LIFT-OFF
"STALL, TOGA 15°"
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[ADV] ECAM ADVISORY
FLIGHT CREW
OPERATING MANUAL
ECAM ADVISORY CONDITIONS
Applicable to: ALL
SYSTEM
CONDITIONS
RECOMMENDED ACTION
Ident.: PRO-ABN-ABN-ADV-A-00012117.0003001 / 17 MAR 17
APU
EGT > EGT MAX -33 °C (inhibited during
APU start)
OIL QTY (message LOW OIL LEVEL
pulsing)
Ident.: PRO-ABN-ABN-ADV-A-00012107.0004001 / 31 AUG 17
CAB VERTICAL SPEED
V/S > 1 800 ft/min
CAB PR
CAB ALTITUDE
altitude ≥ 8 800 ft
ΔP ≥ 1.5 PSI in phase 7
Ident.: PRO-ABN-ABN-ADV-A-00012112.0001001 / 17 MAR 17
IDG OIL TEMP ≥ 147 °C
ELEC
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If there is no oil leak, then the remaining oil quantity allows
normal APU operation for about 10 h.
CPC changeover is recommended:
MODE SEL : MAN
Wait 10 s then:
MODE SEL: AUTO
PACK FLOW: HI
MODE SEL : MAN
Manual pressure control
If the cargo freight permits, set FWD ISOL VALVE: OFF to
reduce the rate of cabin altitude increase.
LDG ELEV : ADJUST
If unsuccessful:
MODE SEL : MAN
Manual pressure control
Reduce IDG load if possible (GALLEY or GEN OFF).
If required, restore when temperature has dropped.
Restrict use of generator to short time, if temperature rises
again excessively.
Continued on the following page
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SYSTEM
[ADV] ECAM ADVISORY
Continued from the previous page
RECOMMENDED ACTION
CONDITIONS
Ident.: PRO-ABN-ABN-ADV-A-00012122.0002001 / 02 MAY 17
OIL PRESS
P < 16 PSI
OIL PRESS
P > 90 PSI
OIL TEMP
T > 140 °C
‐ If oil pressure is between 16 and 13 PSI
(advisory), continue normal operation.
‐ If oil pressure is below 13 PSI (red indication) without
the ENG OIL LO PR ECAM warning, continue normal
engine operation (it can be assumed that the oil pressure
transducer is faulty).
In both cases, monitor other engine parameters especially oil
temperature and oil quantity.
Monitor other engine parameters closely for symptoms of
engine malfunction.
If high oil pressure is not accompanied by other abnormal
indications operate engine normally for remainder of flight.
Record high oil pressure and corresponding N2 readings for
maintenance action.
A rise in oil temperature during normal steady-state
operation indicates a system malfunction and should be
closely monitored for other symptoms of engine malfunction.
Note:
ENG
If the OIL TEMP rise follows thrust reduction,
increasing thrust may reduce oil temperature.
In addition, a rise in oil temperature could be related to the
IDG oil cooling system. To reduce oil temperature rise before
limits are reached, the following are recommended:
1. Low Speed - Increase engine speed to increase fuel flow
and thereby cool IDG oil.
2. High Speed - Reduce generator load or turn off
generator. If oil temperature continues to rise,
mechanically disconnect IDG.
OIL QTY
< 3 qt
NAC TEMP ≥ 240 °C
VIBRATION
N1 ≥ 6 units
N2 ≥ 4.3 units
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If oil quantity low at high power setting, expect level increase
after power reduction.
Monitor affected engine oil parameters and crosscheck with
other engine - If pressure and temperature remain normal,
continue normal operation.
Monitor engine parameters and crosscheck with other
engine
Refer to PRO-ABN-ENG [QRH] HIGH ENGINE VIBRATION
Continued on the following page
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[ADV] ECAM ADVISORY
FLIGHT CREW
OPERATING MANUAL
SYSTEM
Ident.: PRO-ABN-ABN-ADV-A-00012114.0001001 / 21 MAR 17
Difference between wing fuel quantities
greater than 1 500 kg (3 307 lb)
FUEL
Fuel temp greater than 45 °C in inner cell,
or 55 °C in outer cell
Fuel temp lower than -40 °C in inner or
outer cell
Ident.: PRO-ABN-ABN-ADV-A-00012119.0028001 / 17 MAR 17
OXY
Continued from the previous page
RECOMMENDED ACTION
CONDITIONS
CKPT OXY
Pulsing green:
When pressure is < 800 PSI.
Amber:
When pressure is < 400 PSI.
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FUEL MANAGEMENT: CHECK
If a fuel leak is suspected, Refer to PRO-ABN-FUEL [QRH]
FUEL LEAK.
For limitations, Refer to LIM-FUEL Maximum Allowed Fuel
Imbalance
GALLEY: OFF
Consider descending to a lower altitude and/or increasing
Mach to increase TAT.
If mask is not being used, check if it is correctly stowed,
Refer to DSC-35-20-10 Mask Stowage.
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[ADV] ECAM ADVISORY
FLIGHT CREW
OPERATING MANUAL
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[MEM] MEMORY ITEMS
FLIGHT CREW
OPERATING MANUAL
[MEM] MEMORY ITEMS
Applicable to: ALL
Ident.: PRO-ABN-ABN-MEM-ABN-MEM-00020871.0001001 / 17 MAR 17
BRAKES
[MEM] LOSS OF BRAKING (Refer to procedure)
Ident.: PRO-ABN-ABN-MEM-ABN-MEM-00020948.0001001 / 17 MAR 17
MISC
[MEM] EMER DESCENT (Refer to procedure)
[MEM] STALL RECOVERY (Refer to procedure)
[MEM] STALL WARNING AT LIFT OFF (Refer to procedure)
Ident.: PRO-ABN-ABN-MEM-ABN-MEM-00020949.0001001 / 01 JUN 17
NAV
[MEM] UNRELIABLE SPEED INDICATION (Refer to procedure)
Ident.: PRO-ABN-ABN-MEM-ABN-MEM-00020950.0002001 / 17 MAR 17
SURV
[MEM] GPWS/EGPWS CAUTIONS (Refer to procedure)
[MEM] GPWS/EGPWS WARNINGS (Refer to procedure)
[MEM] TCAS WARNINGS (Refer to procedure)
[MEM] WINDSHEAR (Refer to procedure)
[MEM] WINDSHEAR AHEAD (Refer to procedure)
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[MEM] MEMORY ITEMS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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[QRH] PROCEDURES
FLIGHT CREW
OPERATING MANUAL
[QRH] PROCEDURES
Applicable to: ALL
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021342.0002001 / 17 MAR 17
A-ICE
[QRH] DOUBLE AOA HEAT FAILURE (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021355.0001001 / 17 MAR 17
AIR
[QRH] ENGINE 1+2 BLEED FAULT (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021352.0002001 / 17 MAR 17
BRAKES
[QRH] ASYMMETRIC BRAKING (Refer to procedure)
[QRH] RESIDUAL BRAKING (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021343.0001001 / 17 MAR 17
CAB PR
[QRH] CABIN OVERPRESSURE (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021346.0001001 / 17 MAR 17
DOOR
[QRH] COCKPIT DOOR FAULT (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021511.0001001 / 17 MAR 17
EIS
[QRH] DISPLAY UNIT FAILURE (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021345.0002001 / 17 MAR 17
ELEC
[QRH] C/B TRIPPED (Refer to procedure)
[QRH] ELEC EMER CONFIG SYS REMAINING (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021356.0001001 / 17 MAR 17
ENG
[QRH] ENG DUAL FAILURE - FUEL REMAINING (Refer to procedure)
[QRH] ENG DUAL FAILURE - NO FUEL REMAINING (Refer to procedure)
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[QRH] PROCEDURES
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG RELIGHT IN FLIGHT (Refer to procedure)
[QRH] ENG STALL (Refer to procedure)
[QRH] ENG TAILPIPE FIRE (Refer to procedure)
[QRH] HIGH ENGINE VIBRATION (Refer to procedure)
[QRH] ON GROUND - NON ENG SHUTDOWN AFTER ENG MASTER OFF (Refer to procedure)
[QRH] ONE ENGINE INOPERATIVE - CIRCLING APPROACH (Refer to procedure)
[QRH] ONE ENGINE INOPERATIVE - STRAIGHT-IN APPROACH (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021347.0001001 / 17 MAR 17
F/CTL
[QRH] LANDING WITH SLATS OR FLAPS JAMMED (Refer to procedure)
[QRH] RUDDER JAM (Refer to procedure)
[QRH] STABILIZER JAM (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021348.0001001 / 17 MAR 17
FUEL
[QRH] FUEL IMBALANCE (Refer to procedure)
[QRH] FUEL LEAK (Refer to procedure)
[QRH] GRAVITY FUEL FEEDING (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021350.0002001 / 17 MAR 17
FWS
[QRH] MULTIPLE UNDUE ECAM ALERTS (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021353.0001001 / 17 MAR 17
L/G
[QRH] LANDING WITH ABNORMAL L/G (Refer to procedure)
[QRH] L/G GRAVITY EXTENSION (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021358.0001001 / 22 MAR 17
MISC
[QRH] BOMB ON BOARD (Refer to procedure)
[QRH] COCKPIT WINDSHIELD / WINDOW ARCING (Refer to procedure)
[QRH] COCKPIT WINDSHIELD / WINDOW CRACKED (Refer to procedure)
[QRH] DITCHING (Refer to procedure)
[QRH] EMER EVAC (Refer to procedure)
[QRH] EMER LANDING (Refer to procedure)
[QRH] FORCED LANDING (Refer to procedure)
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[QRH] PROCEDURES
FLIGHT CREW
OPERATING MANUAL
[QRH] OVERWEIGHT LANDING (Refer to procedure)
[QRH] SEVERE TURBULENCE (Refer to procedure)
[QRH] TAILSTRIKE (Refer to procedure)
[QRH] VOLCANIC ASH ENCOUNTER (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021354.0001001 / 17 MAR 17
NAV
[QRH] ADR 1+2+3 FAULT (Refer to procedure)
[QRH] ADR CHECK PROC (Refer to procedure)
[QRH] IR ALIGNMENT IN ATT MODE (Refer to procedure)
[QRH] NAV FM / GPS POS DISAGREE (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00020870.0001001 / 17 MAR 17
SMOKE
[QRH] SMOKE / FUMES / AVNCS SMOKE (Refer to procedure)
[QRH] REMOVAL OF SMOKE / FUMES (Refer to procedure)
[QRH] SMOKE / FIRE FROM LITHIUM BATTERY (Refer to procedure)
Ident.: PRO-ABN-ABN-QRH-ABN-QRH-00021512.0001001 / 17 MAR 17
WHEEL
[QRH] WHEEL TIRE DAMAGE SUSPECTED (Refer to procedure)
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[QRH] PROCEDURES
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
SYSTEM RESET - GENERAL
Applicable to: ALL
Ident.: PRO-ABN-ABN-RESET-A-00012644.0001001 / 17 MAR 17
Some systems that operate abnormally can be recovered by a reset. The flight crew can perform a
system reset with the use of:
‐ The associated cockpit control, or
‐ The associated circuit breaker.
WARNING
Only perform one reset at a time, unless indicated differently.
Ident.: PRO-ABN-ABN-RESET-A-00012645.0001001 / 17 MAR 17
Guidelines to reset a system:
‐ Set the related normal cockpit control to OFF, or pull the corresponding circuit breaker
‐ Wait 3 s if a normal cockpit control is used, or 5 s if a circuit breaker is used (unless a different
time is indicated)
‐ Set the related normal cockpit control to ON, or push the corresponding circuit breaker
‐ Wait 3 s for the end of the reset.
Note:
The flight crew should report any in-flight reset to the maintenance.
Ident.: PRO-ABN-ABN-RESET-A-00014340.0001001 / 22 MAR 17
On ground:
Reset ECU (CFM) or EEC (IAE) or EIU only when engine shut down.
Reset BSCU only when aircraft stopped.
Systems not listed in the System Reset Table can be reset following the guidelines described
above.
In flight:
WARNING
The flight crew can attempt a system reset only when:
‐ An ECAM /OEB /FCOM /QRH procedure requests to reset the system, or
‐ The System Reset Table permits.
CAUTION
Do not pull the following circuit breakers:
‐ SFCC
‐ ECU or EEC or EIU.
Note:
Before taking any action on the cockpit C/B s, both the PF and PM must crosscheck
and ensure the C/B label corresponds to the affected system.
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[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
Refer to System Reset Table.
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[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
SYSTEM RESET TABLE
Applicable to: ALL
ECAM
System
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: PRO-ABN-ABN-RESET-B-00012654.0001001 / 20 MAR 17
A-ICE
ANTI ICE
L(R)/WINDSHIELD
(WINDOW)
(WHC)
Refer to PRO-ABN-A-ICE ANTI ICE L(R) WINDSHIELD, if applicable.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
B→
PRO-ABN-ABN-RESET P 3/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: PRO-ABN-ABN-RESET-B-00021069.0001001 / 20 MAR 17
Impacted by TDU: 00021167 System Reset Table - AIR
AIR ENG 1(2) BLEED
FAULT or
AIR ENG 1(2) BLEED
ABNORM PR
(Engine Bleed Supply
System)
Note:
Do not attempt more than one reset.
On ground or in flight
• If the PACK (non-affected side) is operative, and
If the Wing Anti-Ice is OFF:
‐ ENG BLEED (affected side)...............................OFF
▪ If the ENG BLEED (affected side) pb-sw FAULT light is on:
‐ Delay application of the reset until FAULT light extinguishes.
▪ If the ENG BLEED (affected side) pb-sw FAULT light is off:
‐ X BLEED................................................AUTO
‐ PACK (affected side)..................................ON
‐ ENG BLEED (affected side).......................ON
‐ Check that the affected Engine Bleed Valve is open on the BLEED
SD page.
• If AIR ENG (AFFECTED) BLEED FAULT alert or AIR ENG
(AFFECTED) BLEED ABNORM PR alert reoccurs, or
If Engine Bleed Valve (affected side) not open on the BLEED
SD page:
- ENG BLEED (affected side)...............OFF
- X BLEED.........................................OPEN
AIR
AIR ENG 1(2) BLEED
NOT CLSD
(Engine Bleed Supply
System)
Note:
Record the ENG BLEED reset in the logbook (successful or
unsuccessful).
Note:
Do not attempt more than one reset.
On ground only
‐ ENG BLEED (affected side)...............................OFF
▪ If the ENG BLEED (affected side) pb-sw FAULT light is on:
‐ Delay application of the reset until FAULT light extinguishes.
▪ If the ENG BLEED (affected side) pb-sw FAULT light is off:
‐ ENG BLEED (affected side).......................ON
‐ Check that the affected Engine Bleed Valve is closed on the BLEED SD
page.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 4/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Note:
Record the ENG BLEED reset in the logbook (successful or
unsuccessful).
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 5/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: TDU / PRO-ABN-ABN-RESET-B-00021167.0001001 / 20 MAR 17
Impacted DU: 00021069 System Reset Table - AIR
AIR PACK 1(2) REGUL
FAULT
(ACSC)
On ground only:
‐ Pull C/B s W21 and W22 on 122VU
‐ Pull C/B s X21 and X22 on 122VU
‐ Pull C/B s Y18, Y20 and Y21 on 122VU
‐ Pull C/B D8 on 49VU
‐ Wait 5 s before pushing all the C/Bs.
AIR
AIR ENG 1(2) BLEED
FAULT or
AIR ENG 1(2) BLEED
ABNORM PR
(Engine Bleed Supply
System)
Note:
During the reset, a small increase of the engine thrust may be
observed (N1 or EPR, as applicable). If the parking brake is set,
vibrations can occur.
Note:
Do not attempt more than one reset.
On ground or in flight
• If the PACK (non-affected side) is operative, and
If the Wing Anti-Ice is OFF:
‐ ENG BLEED (affected side)...............................OFF
▪ If the ENG BLEED (affected side) pb-sw FAULT light is on:
‐ Delay application of the reset until FAULT light extinguishes.
▪ If the ENG BLEED (affected side) pb-sw FAULT light is off:
‐ X BLEED................................................AUTO
‐ PACK (affected side)..................................ON
‐ ENG BLEED (affected side).......................ON
‐ Check that the affected Engine Bleed Valve is open on the BLEED
SD page.
• If AIR ENG (AFFECTED) BLEED FAULT alert or AIR ENG
(AFFECTED) BLEED ABNORM PR alert reoccurs, or
If Engine Bleed Valve (affected side) not open on the BLEED
SD page:
- ENG BLEED (affected side)...............OFF
- X BLEED.........................................OPEN
Note:
Record the ENG BLEED reset in the logbook (successful or
unsuccessful).
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 6/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
System malfunction
or ECAM Alert
(Affected System)
AIR ENG 1(2) BLEED
NOT CLSD
(Engine Bleed Supply
System)
Continued from the previous page
Reset Procedure
Note:
Do not attempt more than one reset.
On ground only
‐ ENG BLEED (affected side)...............................OFF
▪ If the ENG BLEED (affected side) pb-sw FAULT light is on:
‐ Delay application of the reset until FAULT light extinguishes.
▪ If the ENG BLEED (affected side) pb-sw FAULT light is off:
‐ ENG BLEED (affected side).......................ON
‐ Check that the affected Engine Bleed Valve is closed on the BLEED SD
page.
Note:
Record the ENG BLEED reset in the logbook (successful or
unsuccessful).
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 7/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: PRO-ABN-ABN-RESET-B-00021067.0001001 / 21 MAR 17
AUTO FLT FCU 1(2)
FAULT
(FCU)
In flight:
‐ Pull the C/B B05 on 49VU for FCU 1, or M21 on 121VU for FCU 2
‐ Push it after 5 s
‐ Check the displayed targets and the barometer reference, and correct
them if necessary.
On ground:
‐ Pull the C/B B05 on 49VU for FCU 1, or M21 on 121VU for FCU 2
‐ Push it after 5 s
‐ If AUTO FLT FCU 1+2 FAULT disappears, check the displayed targets
and barometer reference, and correct them if necessary (RESET
successful)
‐ If AUTO FLT FCU 1+2 FAULT remains, pull both C/B B05 on 49VU and
M21 on 121VU
‐ Push them after 7 min , with a delay of less than 5 s between side 1 and 2
‐ Wait at least 30 s for FCU 1 and FCU 2 safety tests completion
‐ Check the displayed targets and barometer reference, and correct them if
necessary (RESET successful).
AUTO FLT
AUTO FLT FCU 1 + 2
FAULT
(FCU)
In flight:
‐ Pull the C/B B05 on 49VU for FCU 1, and then pull M21 on 121VU for
FCU 2
‐ Push them after 5 s
‐ Check the displayed targets and the barometer reference, and correct
them if necessary.
On ground:
‐ Pull the C/B B05 on 49VU for FCU 1, and then pull M21 on 121VU for
FCU 2
‐ Push the C/Bs after 5 s
‐ If AUTO FLT FCU 1(2) FAULT disappears, check the displayed targets
and barometer reference, and correct them if necessary (RESET
successful)
‐ If AUTO FLT FCU 1(2) FAULT remains, pull again both C/B B05 on 49VU
and M21 on 121VU
‐ Push them after 7 min , with a delay of less than 5 s between side 1 and 2
‐ Wait at least 30 seconds for FCU 1 and FCU 2 safety tests completion
‐ Check the displayed targets and barometer reference, and correct them if
necessary (RESET successful)
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 8/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
FCU targets are synchronized on current aircraft values and displayed as
selected targets.
‐ Re–enter the barometer altimeter setting value, if necessary.
AUTO FLT YAW DAMPER
1(2) FAULT
(FAC 1(2))
AUTO FLT REAC W/S
DET FAULT
(FAC 1+2)
One MCDU locked or
blank
(MCDU)
Both MCDU locked
or blank or FMGC
malfunction
(FMGC)
Refer to PRO-ABN-AUTO_FLT AUTO FLT YAW DAMPER 1(2), if applicable.
For Reactive Windshear Detection Fault. Depending on aircraft
configuration, Refer to PRO-ABN-AUTO_FLT AUTO FLT REAC W/S DET
FAULT or Refer to PRO-ABN-W_S WINDSHEAR DET FAULT.
On ground, or in fligth:
‐ Pull the C/B for the locked or blanck MCDU and push it back after 10 s.
The circuit breakers for the MCDUs are:
• AUTO FLT /MCDU 1 B1 ON 49 VU (Overhead Panel)
• AUTO FLT /MCDU 2 N20 ON 121 VU (Right Rear Maintenance Panel)
• AUTO FLT /MCDU 3 N21 ON 121 VU (Right Rear Maintenance Panel)
On ground:
‐ Apply external power or APU generator power
‐ Wait 2 min before resetting the FMGC circuit breakers
‐ FD 1(or 2) (OFF)
‐ Pull the C/B of the affected FMGC and reset it after 10 s.
The circuit breakers for the FMGCs are:
• AUTO FLT /FMGC 1 B2 ON 49 VU (Overhead Panel)
• AUTO FLT /FMGC 2 M17 ON 121 VU (Right Rear Maintenance Panel)
CAUTION
Note:
Always wait 1 min after the "PLEASE WAIT" message
disappears from the MCDU , before engaging or
reengaging the FD s and the AP of the reset FMGC.
Due to electrical transient, MANUAL FMGS RESET procedure
may be unsuccessful. If so, the flight crew may attempt the same
procedure with engines not running.
In flight:
‐ FD 1(or 2) (OFF)
‐ Pull the C/B of the affected FMGC and reset it after 10 s.
The circuit breakers for the FMGCs are:
• AUTO FLT /FMGC 1 B2 ON 49 VU (Overhead Panel)
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 9/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
System malfunction
or ECAM Alert
(Affected System)
Continued from the previous page
Reset Procedure
• AUTO FLT /FMGC 2 M17 ON 121 VU (Right Rear Maintenance Panel)
CAUTION
Always wait 1 min after the "PLEASE WAIT" message
disappears from the MCDU , before engaging or
reengaging the FD s and the AP of the reset FMGC.
Ident.: PRO-ABN-ABN-RESET-B-00021056.0001001 / 20 MAR 17
BRAKES SYS 1(2) FAULT
or
BRAKES BSCU CH 1(2)
FAULT
(BSCU)
On ground:
‐ STOP aircraft
‐ Set PARK BRK handle to ON
‐ Confirm that towing bar is disconnected
‐ Set A/SKID & N/W STRG sw to OFF
‐ Set A/SKID & N/W STRG sw to ON.
• IF UNSUCCESSFUL:
‐ Pull C/B s M33 and M34 on 121VU for BSCU channel 1
‐ Pull C/B s M36 and M35 on 121VU for BSCU channel 2
‐ Push C/Bs.
BRAKES
After a successful reset, resume to normal operation.
Note:
After any BSCU reset:
1. Check brake efficiency
2. Record BSCU reset in the logbook.
In flight:
When landing gear is up only:
‐ Set A/SKID & N/W STRG sw to OFF
‐ Set A/SKID & N/W STRG sw to ON
‐ If required, rearm the autobrake.
When landing gear is down: reset not authorized.
Note:
After any BSCU reset:
‐ Record BSCU reset in the logbook.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 10/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: PRO-ABN-ABN-RESET-B-00021089.0010001 / 20 MAR 17
COM CIDS 1+2 FAULT
On ground, or in flight:
and/or Loss of Passenger
‐ Pull the C/Bs in the following order:
Adress and/or Loss of
P13 and P14 on 121VU
Cabin Interphone
G01 and G02 on 49VU
(CIDS)
M05 and M06 on 121VU
‐ Wait 10 s, then
‐ Push the C/Bs in the following order: M05, M06, G01, G02, P13 , P14
‐ After CIDS reset, wait approximately 4 min, before recovering normal
operation.
COM
Uncommanded EVAC horn
On ground, or in flight:
activation
Press the EVAC HORN SHUT OFF pb. Set the EVAC CAPT & PURS/CAPT
(CIDS)
sw to the CAPT only position. Wait for 3 s.
• IF UNSUCCESSFUL:
‐ Pull the C/B s for DIR 2 in the following order: G02 on 49VU , M06 on
121VU.
• IF UNSUCCESSFUL:
‐ Pull the C/B s for DIR 1 in the following order: G01 on 49VU , M05
on 121VU
‐ Wait for 1 min, then:
‐ Push the C/B s for DIR 2 in the following order: M06 , G02 .
‐ After CIDS reset, wait approximately 4 min, before recovering
normal operation.
Frozen RMP
(RMP)
FAP freezing
(FAP)
On ground, or in flight:
The flight crew must reset all the RMP s one after the other via the RMP
control panel:
‐ Set RMP ON/OFF sw to OFF position
‐ Wait 5 s
‐ Set RMP ON/OFF sw to ON position.
On ground, or in flight:
‐ Pull FAP C/B s in the following order: H01 C/B on 49VU , Q14 on 121VU
‐ Wait 10 s, then
‐ Push the C/Bs in the following order: Q14, H01 C/B.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 11/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: PRO-ABN-ABN-RESET-B-00012659.0001001 / 03 AUG 17
ATSU Malfunction
(ATSU)
The ATSU reset should be attempted, only if:
‐ Key selection has no effect on the DCDU or any of the MCDU ATSU
DATALINK submenus
‐ ADS-C or CPDLC are inoperative
When the ATSU is reset, the following connections are no longer active:
‐ CPDLC:
• The flight crew should send a notification to the ATC center to
re-establish the CPDLC connection
DATALINK
‐ ADS-C:
• As no ADS-C disconnect message is sent, the ATC center(s) assumes
that the ADS-C connection is still alive
• The flight crew must check that ADS-C is ARMED or ON.
On ground or in flight:
‐ Pull the C/B s in the following order: L16, L15 on 121VU
‐ Wait 5 s, then
‐ Push the C/Bs in the following order: L15, L16.
Ident.: PRO-ABN-ABN-RESET-B-00014274.0001001 / 20 MAR 17
DOOR
Flickering or total loss of
the video camera display
(on the SD) accompanied
by the "VIDEO NOT
AVAIL" message.
(CDSS)
On ground, or in flight:
‐ Set the VIDEO rotary selector to OFF, on the center pedestal VIDEO
panel
‐ Set the COCKPIT DOOR VIDEO pb-sw to OFF, on the overhead panel
‐ Wait 2 min, then
‐ Set the COCKPIT DOOR VIDEO pb-sw back to ON, on the overhead
panel
‐ Wait 15 s, then
‐ Set the VIDEO rotary selector to ″CKPT ENTRY″, on the center pedestal
VIDEO panel.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 12/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: PRO-ABN-ABN-RESET-B-00012650.0001001 / 20 MAR 17
ELEC
GPU cannot be connected
On ground only:
to the aircraft
The GPU cannot be connected to the electrical network of the aircraft (AVAIL
(GAPCU)
light is OFF):
• If at least one power source (IDG 1 or 2, APU GEN or batteries) is
connected to the electrical network of the aircraft
‐ Reset the EXT PWR pb switch on 35VU (Press and release).
• If no power source is connected to the electrical network of the aircraft
‐ Set the BAT 1 pb-sw and BAT 2 pb-sw to AUTO.
Ident.: PRO-ABN-ABN-RESET-B-00012660.0001001 / 20 MAR 17
ENG
ENG 1(2) FADEC A(B)
FAULT
(FADEC)
Refer to PRO-ABN-ENG ENG 1(2) FADEC A(B) FAULT, if applicable.
Ident.: PRO-ABN-ABN-RESET-B-00012652.0001001 / 20 MAR 17
F/CTL
F/CTL ELAC 1(2) FAULT Refer to PRO-ABN-F/CTL section for associated procedure, if applicable.
F/CTL ALTN LAW
F/CTL ELAC 1(2) PITCH
FAULT
(ELAC)
ELAC or SEC malfunction ELAC or SEC may be reset.
(ELAC or SEC)
WARNING
Do not reset more than one computer at a time.
It is possible to reset flight control computers in flight,
event if not requested by the ECAM, provided only one
reset is performed at a time.
Note:
When an ELAC reset is performed on ground the crew must
check the pitch trim position. If a reset is performed on ground,
the flight crew must then perform a flight control check, Refer to
PRO-NOR-SOP-10-TAXI.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 13/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: PRO-ABN-ABN-RESET-B-00012653.0018001 / 20 MAR 17
FUEL
Loss of fuel quantity
indication or Simultaneous
triggering of FUEL L
OUTER XFR CLOSED
and FUEL R OUTER XFR
CLOSED, although FUEL
SD indicates no anomaly.
(FQIC)
On ground, or in flight:
‐ Pull the 3 C/Bs:
• Channel 1 (A13 on 49VU)
• Channel 2 (M27 on 121VU)
• Channel 1 and 2 (L26 on 121VU).
‐ Wait 5 s, before pushing the 3 C/Bs.
Note:
The fuel quantity indication will be re-established within 1 min.
Ident.: PRO-ABN-ABN-RESET-B-00012655.0002001 / 20 MAR 17
FWS FWC 1(2) FAULT
(FWC)
FWC
On ground:
Pull, then push, the C/B of the affected FWC:
‐ FWC 1 (F01 on 49VU)
‐ FWC 2 (Q7 on 121VU).
Wait 50 s after pushing the C/Bs.
In flight:
Pull, then push, the C/B of the affected FWC:
‐ FWC 1 (F01 on 49VU)
‐ FWC 2 (Q7 on 121VU).
Ident.: PRO-ABN-ABN-RESET-B-00021057.0001001 / 21 MAR 17
L/G LGCIU 1(2) FAULT
(LGCIU 1(2))
L/G
On ground only:
The flight crew must depressurize the green hydraulic system before
resetting the LGCIU:
‐ ENG 1 PUMP OFF
‐ PTU OFF.
When there is no green hydraulic pressure:
‐ To reset LGCIU 1:
• Pull C/B Q34 on 121VU , then C09 on 49VU
• Wait for 15 s , then push the C/Bs.
‐ To reset LGCIU 2:
• Pull C/B Q35 on 121VU
• Wait for 15 s , then push the C/B.
After the LGCIU reset, restore green hydraulic pressure (ENG 1 PUMP ON,
PTU AUTO).
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 14/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: PRO-ABN-ABN-RESET-B-00012657.0048001 / 20 MAR 17
NAV GPWS FAULT and
NAV GPWS TERR DET
FAULT
(EGPWS)
NAV TCAS FAULT
(TCAS)
NAV
ISIS malfunction
(ISIS)
On ground, or in flight:
Perform the following reset when both alerts are displayed at the same time.
‐ Pull C/B P07 on 121VU,
‐ Set GPWS SYS pb and GPWS TERR pb to ON,
‐ Wait 5 s, then push the C/B.
On ground only:
‐ Pull C/B K10 on 121VU.
‐ Wait 5 s, then push the C/B.
On ground only:
With aircraft not moving:
‐ Pull C/B F12 on 49VU,
‐ Wait 5 s, then push the C/B,
‐ Normal operation is expected after approximately 2 min.
Note:
In the case of small aircraft motion during the C/B reset (refueling,
cargo loading conditions, etc.), the ATT red flag may appear
on the ISIS. In this case, press the RST P/B for 2 s wait 2 min
additional to recover normal operation.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 15/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: PRO-ABN-ABN-RESET-B-00012651.0016001 / 20 MAR 17
SMOKE DET FAULT
(CIDS-SDF)
SMOKE
On ground, or in flight:
Apply the following actions in the presented order:
‐ Pull the C/B s C05 and C06 on 49VU , T17 and T18 on 122VU
‐ Wait 10 s, then
‐ Push simultaneously the C/B s C05 and C06 on 49VU
‐ Within 2 s push simultaneously the C/B s T17 and T18 on 122VU
‐ After CIDS reset, wait approximately 4 min before recovering normal
operation.
SMOKE LAVATORY DET
On ground, or in flight:
FAULT
with all lavatories declared Apply the following actions in the presented order:
‐ Pull the C/B s P13 and P14 on 121VU , G01 and G02 on 49VU , M05
inoperative on the FAP
or M06 and M06 or M07 on 121VU
(CIDS or CIDS-SDF)
‐ Wait 10 s, then
‐ Push the C/B s in the following order: M05 or M06 and M06 or M07 on
121VU , G01 and G02 on 49VU, P13 and P14 on 121VU.
‐ After CIDS reset, wait approximately 4 min before recovering normal
operation.
If unsuccessful, on ground only:
Apply the following actions in the presented order:
‐ Pull the C/B s C06 and C05 on 49VU , T17 and T18 on 122VU.
‐ Wait 10 s, then
‐ Push simultaneously the C/B s C06 and C05 on 49VU
‐ Within 2 s push simultaneously the C/B s T17 and T18 on 122VU
‐ After CIDS reset, wait approximately 4 min before recovering normal
operation.
SMOKE FWD (AFT)
CARGO DET FAULT
SMOKE FWD (AFT) CRG
1/2 BTL FAULT
(CIDS-SDF)
On ground:
Apply the following actions in the presented order:
‐ Pull the C/B s C06 and C05 on 49VU , T17 and T18 on 122VU
‐ Wait 10 s, then
‐ Push simultaneously the C/B s C06 and C05 on 49VU
‐ Within 2 s push simultaneously the C/B s T17 and T18 on 122VU
‐ After CIDS reset, wait approximately 4 min before recovering normal
operation.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 16/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: PRO-ABN-ABN-RESET-B-00021071.0001001 / 20 MAR 17
VENT
VENT AVNCS SYS
FAULT
(AEVC)
On ground only:
‐ Pull C/B Y17 on 122VU
‐ Wait 5 s before pushing the C/B.
Ident.: PRO-ABN-ABN-RESET-B-00021068.0001001 / 20 MAR 17
WINDSHEAR DET FAULT For Reactive Windshear Detection Fault. Depending on aircraft
configuration, refer to PRO-ABN-22 AUTO FLT REAC W/S DET FAULT or to
WINDSHEAR or AUTO FLT REAC W/S PRO-ABN-22 WINDSHEAR DET FAULT.
DET FAULT
(FAC 1+2)
Ident.: PRO-ABN-ABN-RESET-B-00021058.0001001 / 20 MAR 17
Impacted by TDU: 00021059 System Reset Table - WHEEL
WHEEL N.W STEER
FAULT
or
WHEEL N/W STRG
FAULT
(BSCU)
WHEEL
On ground only:
‐ STOP aircraft
‐ Set PARK BRK handle to ON
‐ Confirm that towing bar is disconnected
‐ Set A/SKID & N/W STRG sw to OFF
‐ Set A/SKID & N/W STRG sw to ON.
In the case of a WHEEL N/W STRG FAULT, the flight crew may attempt a
BSCU reset. However, even if the BSCU reset is successful, the flight crew
must return to the gate for troubleshooting. The taxi speed must not exceed
10 kt.
Note:
After any BSCU reset:
1. Check brake efficiency
2. Record the BSCU reset in the logbook.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-ABN-RESET P 17/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
[RESET] SYSTEM RESET
FLIGHT CREW
OPERATING MANUAL
ECAM
System
Continued from the previous page
System malfunction
or ECAM Alert
(Affected System)
Reset Procedure
Ident.: TDU / PRO-ABN-ABN-RESET-B-00021059.0001001 / 20 MAR 17
Impacted DU: 00021058 System Reset Table - WHEEL
WHEEL N.W STEER
FAULT
or
WHEEL N/W STRG
FAULT
(BSCU)
On ground only:
Case A
If the three conditions below are fulfilled:
‐ the WHEEL N/W STRG FAULT alert was triggered just after engine start
‐ the N/W STRG DISC memo was displayed before the start of the
pushback (before the aircraft starts moving)
‐ the N/W STRG DISC memo remained displayed even after the pushback
is finished (nosewheel steering selector bypass pin is in the steering
position).
Apply the below reset procedure.
If the ECAM alert disappears after the reset, the flight crew may continue the
flight without troubleshooting.
WHEEL
Case B
In all other cases, including in case of doubt on the above conditions,
troubleshooting must be performed before continuing the flight, even if the
ECAM alert disappears after the reset. For a return to the gate :
‐ Apply the below reset procedure
‐ The taxi speed must not exceed 10 kt.
Reset Procedure:
‐ STOP aircraft
‐ Set PARK BRK handle to ON
‐ Confirm that towing bar is disconnected
‐ Set A/SKID & N/W STRG sw to OFF
‐ Set A/SKID & N/W STRG sw to ON.
Note:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
After any BSCU reset:
1. Check brake efficiency
2. Check absence of aircraft veering
3. Record the BSCU reset in the logbook.
←B
PRO-ABN-ABN-RESET P 18/18
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
[QRH] DOUBLE AOA HEAT FAILURE
Ident.: PRO-ABN-A-ICE-00010253.0002001 / 17 MAR 17
Applicable to: ALL
In the case of double failure of alpha probe heaters, the choice made by the computers among the
3 ADR values may be erroneous.
One of affected ADRs...................................................................................................................OFF
Keep preferably ADR 1 available as ADR1 is supplied in EMER ELEC config.
NAV ADR 1(2)(3) FAULT
In the case of disagreement between the two remaining ADR s, the NAV ADR DISAGREE ECAM
alert will trigger.
ANTI ICE ALL PITOT
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-U-00017184.0003001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating systems of the CAPT , F/O and STBY pitot probes are
failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
PRO-ABN-A-ICE P 1/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE ALL PITOT (Cont'd)
Ident.: PRO-ABN-A-ICE-U-00018180.0004001 / 21 MAR 17
L2
In the case of simultaneous pitot icing and in the same amount, ADR 1, ADR 2, and ADR 3 speeds
will be in agreement, but incorrect. The following ECAM procedure avoids that the flight controls
use erroneous, but coherent, sources.
L1
ADR 1(2)(3) P/B............................................................................................................................ OFF
Depending on the status of the static, AOA , and TAT heating, the ECAM requires that either ADR
1, 2 or 3 be switched OFF.
L2
Note:
In the case of subsequent, significant, speed discrepancy between the two remaining
ADR s, the “ADR DISAGREE” ECAM caution will trigger.
L1
IF ICING EXPECTED:
ADR 2(3) P/B..........................................................................................................................OFF
L2
Depending on the status of the static, AOA , and TAT heating, the ECAM requires that either
ADR 2 or 3 be switched OFF.
L1
UNREL SPD PROC........................................................................................................... APPLY
L2
Only one ADR is available, and the corresponding pitot probe may be affected by ice accretion.
Be prepared to use the UNRELIABLE SPEED INDICATION procedure (Refer to procedure).
L12
ASSOCIATED PROCEDURES
NAV ADR FAULT
Single ADR FAULT or double ADR FAULT ECAM cautions may trigger, depending on the
number of ADRs switched OFF.
L12
ASSOCIATED PROCEDURES
F/CTL ALTN LAW
(PROT LOST)
Alternate law becomes active, if:
‐ One ADR was already switched OFF, and the two remaining ADRs are not in agreement, or
‐ Two ADRs were switched OFF.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-A-ICE P 2/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE ALL PITOT (Cont'd)
Ident.: PRO-ABN-A-ICE-U-00018298.0002001 / 21 MAR 16
STATUS
IF ICING EXPECTED:
ADR 2(3) P/B............................................................. OFF
UNREL SPD PROC............................................... APPLY
INOP SYS
CAPT PITOT
F/O PITOT
STBY PITOT
CAPT PROBES
F/O PROBES
(1)
(2)
(3)
STBY PROBES
STEEP APPR (If in ALTN
LAW)
(1)
(2)
(3)
(If all CAPT PROBES heating is lost)
(If all F/O PROBES heating is lost)
(If all STBY PROBES heating is lost)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-ABN-A-ICE P 3/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE CAPT(F/O) TAT
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-E-00017171.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating system of the corresponding probe is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-A-ICE-E-00018299.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-A-ICE-E-00018889.0001001 / 21 MAR 16
STATUS
INOP SYS
CAPT(F/O) TAT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-A-ICE P 4/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE CAPT + F/O PITOT
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-R-00017177.0003001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating systems of the CAPT and F/O pitot probes are failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PRO-ABN-A-ICE P 5/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE CAPT + F/O PITOT (Cont'd)
Ident.: PRO-ABN-A-ICE-R-00018300.0002001 / 21 MAR 17
L2
In the case of simultaneous pitot icing and in the same amount, ADR 1 and ADR 2 speeds will be
in agreement, but incorrect. Therefore, flight controls will consider the remaining correct source as
being faulty, and will reject the only correct source. The following ECAM procedure avoids that the
flight controls use two erroneous, but coherent, sources.
L1
If ADR 3 operative and ON:
ADR 1(2) P/B..........................................................................................................................OFF
L2
Depending on the status of the static, AOA, and TAT heating, the ECAM requires that either
ADR 1 or 2 be switched OFF
Note:
L1
L2
L1
L2
L1
L2
In the case of subsequent, significant, speed discrepancy between the two remaining
ADR s, the “ADR DISAGREE” ECAM caution will trigger.
If ADR 3 failed or OFF:
No action is required, as long as there are no icing conditions, in order to keep two independent
speed sources.
IF ICING EXPECTED:
ADR 1(2) P/B................................................................................................................... OFF
Depending on the status of the static, AOA, and TAT heating, the ECAM requires that
either ADR 1 or 2 be switched OFF.
UNREL SPD PROC.....................................................................................................APPLY
Only one ADR is available, and the corresponding pitot probe may be affected by ice
accretion. Be prepared to use the UNRELIABLE SPEED INDICATION procedure (Refer to
procedure).
L1
ASSOCIATED PROCEDURES
NAV ADR FAULT
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
PRO-ABN-A-ICE P 6/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE CAPT + F/O PITOT (Cont'd)
Ident.: PRO-ABN-A-ICE-R-00018301.0002001 / 21 MAR 16
STATUS
If ADR 3 failed or OFF:
IF ICING EXPECTED:
ADR 1(2) P/B.......................................................OFF
UNREL SPD PROC........................................ APPLY
(1)
(2)
INOP SYS
CAPT PITOT
F/O PITOT
CAPT PROBES
F/O PROBES
(1)
(2)
(If all CAPT PROBES heating is lost)
(If all F/O PROBES heating is lost)
ANTI ICE CAPT + STBY PITOT
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-S-00017178.0003001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating systems of the CAPT and STBY pitot probes are failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
PRO-ABN-A-ICE P 7/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE CAPT + STBY PITOT (Cont'd)
Ident.: PRO-ABN-A-ICE-S-00018302.0002001 / 21 MAR 17
L2
In the case of simultaneous pitot icing and in the same amount, ADR 1 and ADR 3 speeds will be in
agreement, but incorrect. Flight controls will consider the remaining correct source as being faulty,
and will reject the only correct source. The following ECAM procedure avoids that the flight controls
use two erroneous, but coherent, sources.
L1
If ADR 2 operative and ON:
ADR 1(3) P/B..........................................................................................................................OFF
L2
Depending on the status of the static, AOA, and TAT heating, the ECAM requires that either
ADR 1 or 3 be switched OFF
Note:
L1
L2
L1
L2
L1
L2
In the case of subsequent, significant, speed discrepancy between the two remaining
ADR s, the “ADR DISAGREE” ECAM caution will trigger.
If ADR 2 failed or OFF:
No action is required, as long as there are no icing conditions, in order to keep two independent
speed sources.
IF ICING EXPECTED:
ADR 1(3) P/B................................................................................................................... OFF
Depending on the status of the static, AOA, and TAT heating, the ECAM requires that
either ADR 1 or 3 be switched OFF.
UNREL SPD PROC.....................................................................................................APPLY
Only one ADR is available, and the corresponding pitot probe may be affected by ice
accretion. Be prepared to use the UNRELIABLE SPEED INDICATION procedure (Refer to
procedure).
L1
ASSOCIATED PROCEDURES
NAV ADR FAULT
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
PRO-ABN-A-ICE P 8/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE CAPT + STBY PITOT (Cont'd)
Ident.: PRO-ABN-A-ICE-S-00018303.0002001 / 21 MAR 16
STATUS
If ADR 2 failed or OFF:
IF ICING EXPECTED:
ADR 1(3) P/B.......................................................OFF
UNREL SPD PROC........................................ APPLY
(1)
(2)
INOP SYS
CAPT PITOT
STBY PITOT
CAPT PROBES
STBY PROBES
(1)
(2)
(If all CAPT PROBES heating is lost)
(If all STBY PROBES heating is lost)
ANTI ICE CAPT PITOT OR L(R) STAT OR AOA
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-C-00017169.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating system of the corresponding probe is failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F →
PRO-ABN-A-ICE P 9/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE CAPT PITOT OR L(R) STAT OR AOA (Cont'd)
Ident.: PRO-ABN-A-ICE-C-00018310.0002001 / 21 MAR 16
L2
AIR DATA SWTG ...................................................................................................................CAPT 3
ADR 3 supplies data to PFD 1 and ND 1.
Note:
AIR DATA SWTG should not be selected to CAPT 3 if ADR 3 is not available.
Ident.: PRO-ABN-A-ICE-C-00018900.0001001 / 21 MAR 16
STATUS
INOP SYS
CAPT PITOT
CAPT L(R) STAT
CAPT AOA
ANTI ICE CAPT PROBES
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-G-00017173.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the captain probe heat computer is failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G →
PRO-ABN-A-ICE P 10/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE CAPT PROBES (Cont'd)
Ident.: PRO-ABN-A-ICE-G-00010255.0002001 / 05 AUG 10
AIR DATA SWTG.................................................................................................................... CAPT 3
L2
Note:
AIR DATA SWTG should not be selected to CAPT 3 if ADR 3 is not available.
Ident.: PRO-ABN-A-ICE-G-00010256.0001001 / 05 AUG 10
STATUS
INOP SYS
CAPT PROBES
ANTI ICE ENG 1(2) VALVE CLSD
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-J-00017163.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the valve is abnormally closed.
Flight Phase Inhibition:
Ident.: PRO-ABN-A-ICE-J-00010269.0001001 / 05 AUG 10
AVOID ICING CONDITIONS
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← G to H →
PRO-ABN-A-ICE P 11/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE ENG 1(2) VALVE CLSD (Cont'd)
Ident.: PRO-ABN-A-ICE-J-00010270.0001001 / 05 AUG 10
STATUS
INOP SYS
AVOID ICING CONDITIONS
ENG 1 (2) A. ICE
ANTI ICE ENG 1(2) VALVE OPEN
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-K-00017162.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the valve is abnormally open.
Flight Phase Inhibition:
Ident.: PRO-ABN-A-ICE-K-00010272.0001001 / 05 AUG 10
THRUST LIM PENALTY
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← H to I →
PRO-ABN-A-ICE P 12/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE ENG 1(2) VALVE OPEN (Cont'd)
Ident.: PRO-ABN-A-ICE-K-00010273.0001001 / 05 AUG 10
STATUS
THRUST LIM PENALTY
ANTI ICE F/O + STBY PITOT
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-T-00017179.0003001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating systems of the F/O and STBY pitot probes are failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← I to J →
PRO-ABN-A-ICE P 13/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE F/O + STBY PITOT (Cont'd)
Ident.: PRO-ABN-A-ICE-T-00018307.0002001 / 21 MAR 17
L2
In the case of simultaneous pitot icing and in the same amount, ADR 2 and ADR 3 speeds will be
in agreement, but incorrect. Therefore, flight controls will consider the remaining correct source as
being faulty, and will reject the only correct source. The following ECAM procedure avoids that the
flight controls use two erroneous, but coherent, sources.
L1
If ADR 1 operative and ON:
ADR 2(3) P/B..........................................................................................................................OFF
L2
Depending on the status of the static, AOA , and TAT heating, the ECAM requires that either
ADR 2 or 3 be switched OFF.
Note:
L1
L2
L1
L2
L1
L2
In the case of subsequent, significant, speed discrepancy between the two remaining
ADR s, the “ADR DISAGREE” ECAM caution will trigger.
If ADR 1 failed or OFF:
No action is required, as long as there are no icing conditions, in order to keep two independent
speed sources.
IF ICING EXPECTED:
ADR 2(3) P/B................................................................................................................... OFF
Depending on the status of the static, AOA , and TAT heating, the ECAM requires that
either ADR 2 or 3 be switched OFF.
UNREL SPD PROC.....................................................................................................APPLY
Only one ADR is available, and the corresponding pitot probe may be affected by ice
accretion. Be prepared to use the UNRELIABLE SPEED INDICATION procedure (Refer to
procedure).
L1
ASSOCIATED PROCEDURES
NAV ADR FAULT
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←J→
PRO-ABN-A-ICE P 14/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE F/O + STBY PITOT (Cont'd)
Ident.: PRO-ABN-A-ICE-T-00018308.0002001 / 21 MAR 16
STATUS
If ADR 1 failed or OFF:
IF ICING EXPECTED:
ADR 2(3) P/B.......................................................OFF
UNREL SPD PROC........................................ APPLY
(1)
(2)
INOP SYS
F/O PITOT
STBY PITOT
F/O PROBES
(1)
STBY PROBES
(2)
(If all F/O PROBES heating is lost)
(If all STBY PROBES heating is lost)
ANTI ICE F/O PITOT OR L( R) STAT OR AOA
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-D-00017170.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating system of the corresponding probe is failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← J to K →
PRO-ABN-A-ICE P 15/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE F/O PITOT OR L( R) STAT OR AOA (Cont'd)
Ident.: PRO-ABN-A-ICE-D-00018309.0002001 / 21 MAR 16
L2
AIR DATA SWTG........................................................................................................................F/O 3
ADR 3 supplies data to PFD 2 and ND 2.
Note:
AIR DATA SWTG should not be selected to F/O 3 if ADR 3 is not available.
Ident.: PRO-ABN-A-ICE-D-00018901.0001001 / 21 MAR 16
STATUS
INOP SYS
F/O PITOT
F/O L(R) STAT
F/O AOA
ANTI ICE F/O PROBES
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-H-00017174.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the F/O probe heat computer is failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← K to L →
PRO-ABN-A-ICE P 16/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE F/O PROBES (Cont'd)
Ident.: PRO-ABN-A-ICE-H-00010261.0002001 / 05 AUG 10
AIR DATA SWTG........................................................................................................................F/O 3
L2
Note:
AIR DATA SWTG should not be selected to F/O 3 if ADR 3 is not available.
Ident.: PRO-ABN-A-ICE-H-00010263.0001001 / 05 AUG 10
STATUS
INOP SYS
F/O PROBES
ANTI ICE L + R WINDSHIELD
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-B-00017167.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating system of both windshields is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-A-ICE-B-00010236.0001001 / 25 FEB 14
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← L to M →
PRO-ABN-A-ICE P 17/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE L + R WINDSHIELD (Cont'd)
Ident.: PRO-ABN-A-ICE-B-00010237.0001001 / 05 AUG 10
STATUS
INOP SYS
WSHLD HEAT
ANTI ICE L(R) WINDOW
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-V-00017168.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating system of the left(right) cockpit window is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-A-ICE-V-00010234.0001001 / 25 FEB 14
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← M to N →
PRO-ABN-A-ICE P 18/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE L(R) WINDOW (Cont'd)
Ident.: PRO-ABN-A-ICE-V-00010235.0001001 / 05 AUG 10
STATUS
INOP SYS
L(R) WNDW HEAT
ANTI ICE L(R) WINDSHIELD
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-A-00017166.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating system of the left(right) windshield is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-A-ICE-A-00010232.0001001 / 25 FEB 14
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← N to O →
PRO-ABN-A-ICE P 19/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE L(R) WINDSHIELD (Cont'd)
Ident.: PRO-ABN-A-ICE-A-00010233.0001001 / 05 AUG 10
STATUS
INOP SYS
L(R) WSHLD HEAT
ANTI ICE STBY PITOT OR L(R) STAT OR AOA
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-F-00017172.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the heating system of the corresponding probe is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-A-ICE-F-00010250.0001001 / 25 FEB 14
Crew awareness.
L2
If standby instruments are used, monitor air data information.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← O to P →
PRO-ABN-A-ICE P 20/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE STBY PITOT OR L(R) STAT OR AOA (Cont'd)
Ident.: PRO-ABN-A-ICE-F-00010251.0001001 / 05 AUG 10
STATUS
INOP SYS
STBY PITOT
STBY L(R) STAT
STBY AOA
ANTI ICE STBY PROBES
Applicable to: ALL
Ident.: PRO-ABN-A-ICE-I-00017176.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the standby probe heat computer is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-A-ICE-I-00010265.0001001 / 25 FEB 14
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← P to Q →
PRO-ABN-A-ICE P 21/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
A-ICE
FLIGHT CREW
OPERATING MANUAL
ANTI ICE STBY PROBES (Cont'd)
Ident.: PRO-ABN-A-ICE-I-00010266.0001001 / 05 AUG 10
STATUS
INOP SYS
STBY PROBES
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←Q
PRO-ABN-A-ICE P 22/22
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
[QRH] ENGINE 1+2 BLEED FAULT
Ident.: PRO-ABN-AIR-00017611.0001001 / 21 MAR 17
Applicable to: ALL
Apply this procedure when both engine bleed supply systems are failed.
At ANY TIME of the procedure, if CAB PR EXCESS CAB ALT alert triggers: APPLY ECAM
PROC
If AIR ENG 1 BLEED FAULT alert or AIR ENG 1 BLEED ABNORM PR alert
and
If AIR ENG 2 BLEED FAULT alert or AIR ENG 2 BLEED ABNORM PR alert:
X BLEED .............................................................................................................................SHUT
ENG 1 BLEED ..................................................................................................... OFF THEN ON
ENG 2 BLEED ..................................................................................................... OFF THEN ON
If reset unsuccessful (NO engine bleed recovered):
DESCENT TO FL 100 / MEA -MORA......................................................................INITIATE
L2
Descend rapidly to FL 100 / MEA -MORA, to prevent excessive cabin altitude.
L1
ENG 1 BLEED..................................................................................................................OFF
ENG 2 BLEED..................................................................................................................OFF
APU BLEED..................................................................................................................... OFF
APU..............................................................................................................................START
WING A.ICE..................................................................................................................... OFF
AVOID ICING CONDITIONS
If APU available:
When at or below FL 200:
KEEP WING A.ICE OFF
L2
APU BLEED must not be used for wing anti-ice.
L1
APU BLEED.......................................................................................................... ON
L2
When APU BLEED is ON and pressurization is recovered, reduce rate of descent
and consider MAX FL 200.
L1
If APU bleed available:
MAX FL: 200
ENG 1 BLEED................................................................................................ON
ENG 2 BLEED................................................................................................ON
APU BLEED..................................................................................................OFF
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-ABN-AIR P 1/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
[QRH] ENGINE 1+2 BLEED FAULT (Cont'd)
If no engine bleed recovered:
APU BLEED.............................................................................................ON
ENG 1 BLEED....................................................................................... OFF
ENG 2 BLEED....................................................................................... OFF
L2
L1
WING A.ICE NOT AVAILABLE
If PACK 1 inoperative:
X BLEED.......................................................................................OPEN
To supply the PACK 2 from the APU bleed.
If APU bleed not available:
CONTINUE DESCENT TO FL 100 / MEA-MORA
APU BLEED..................................................................................................OFF
When at or below FL 100 / MEA-MORA:
ENG 1 BLEED......................................................................................... ON
ENG 2 BLEED......................................................................................... ON
If no engine bleed recovered:
ENG 1 BLEED.................................................................................OFF
ENG 2 BLEED.................................................................................OFF
WING A.ICE NOT AVAILABLE
When CAB PR ΔP < 1 psi:
RAM AIR..................................................................................... ON
MAX FL: 100 / MEA-MORA
If APU not available:
CONTINUE DESCENT TO FL 100 / MEA-MORA
APU BLEED...............................................................................................................OFF
When at or below FL 100 / MEA-MORA:
ENG 1 BLEED...................................................................................................... ON
ENG 2 BLEED...................................................................................................... ON
If no engine bleed recovered:
ENG 1 BLEED..............................................................................................OFF
ENG 2 BLEED..............................................................................................OFF
WING A.ICE NOT AVAILABLE
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-ABN-AIR P 2/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
[QRH] ENGINE 1+2 BLEED FAULT (Cont'd)
When CAB PR ΔP < 1 psi:
RAM AIR.................................................................................................. ON
MAX FL: 100 / MEA-MORA
If at least one engine bleed failed due to bleed leak or engine fire or Start Air Valve failed
open:
DESCENT TO FL 100 / MEA -MORA............................................................................ INITIATE
L2
Descend rapidly to FL 100 / MEA -MORA, to prevent excessive cabin altitude.
L1
X BLEED.............................................................................................................................. SHUT
ENG 1 BLEED........................................................................................................................ OFF
ENG 2 BLEED........................................................................................................................ OFF
APU BLEED............................................................................................................................OFF
APU.................................................................................................................................... START
WING A.ICE............................................................................................................................OFF
AVOID ICING CONDITIONS
If AIR ENG 2 BLEED FAULT alert or AIR ENG 2 BLEED ABNORM PR alert:
When at or below FL 100 / MEA-MORA:
ENG 2 BLEED.............................................................................................................ON
If engine 2 bleed not recovered:
ENG 2 BLEED.................................................................................................... OFF
WING A.ICE NOT AVAILABLE
When CAB PR ΔP < 1 psi:
RAM AIR.........................................................................................................ON
MAX FL: 100 / MEA-MORA
L2
L1
L2
If AIR ENG 1 BLEED FAULT alert or AIR ENG 1 BLEED ABNORM PR alert:
If APU available:
When at or below FL 200:
KEEP WING A.ICE OFF
APU BLEED must not be used for wing anti-ice.
APU BLEED.......................................................................................................... ON
When APU BLEED is ON and pressurization is recovered, reduce rate of descent
and consider MAX FL 200.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-ABN-AIR P 3/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
[QRH] ENGINE 1+2 BLEED FAULT (Cont'd)
L1
If APU bleed available:
MAX FL: 200
ENG 1 BLEED................................................................................................ON
APU BLEED..................................................................................................OFF
If engine 1 bleed not recovered:
APU BLEED.............................................................................................ON
ENG 1 BLEED....................................................................................... OFF
WING A.ICE NOT AVAILABLE
If APU bleed not available:
CONTINUE DESCENT TO FL 100 / MEA-MORA
APU BLEED..................................................................................................OFF
When at or below FL 100 / MEA-MORA:
ENG 1 BLEED......................................................................................... ON
If engine 1 bleed not recovered:
ENG 1 BLEED.................................................................................OFF
WING A.ICE NOT AVAILABLE
When CAB PR ΔP < 1 psi:
RAM AIR..................................................................................... ON
MAX FL: 100 / MEA-MORA
If APU not available:
CONTINUE DESCENT TO FL 100 / MEA-MORA
APU BLEED...............................................................................................................OFF
When at or below FL 100 / MEA-MORA:
ENG 1 BLEED...................................................................................................... ON
If engine 1 bleed not recovered:
ENG 1 BLEED..............................................................................................OFF
WING A.ICE NOT AVAILABLE
When CAB PR ΔP < 1 psi:
RAM AIR.................................................................................................. ON
MAX FL: 100 / MEA-MORA
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-ABN-AIR P 4/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
[QRH] ENGINE 1+2 BLEED FAULT (Cont'd)
If neither AIR ENG 1(2) BLEED FAULT alert nor AIR ENG 1(2) BLEED ABNORM PR
alert on any side:
NO ENGINE BLEED CAN BE RECOVERED
WING A.ICE NOT AVAILABLE
When at or below FL 100 / MEA-MORA
and
CAB PR ΔP < 1 psi:
RAM AIR......................................................................................................................ON
MAX FL: 100 / MEA-MORA
AIR APU BLEED FAULT
Applicable to: ALL
Ident.: PRO-ABN-AIR-G-00017375.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the APU is running and the position of the APU bleed valve disagrees
with the selected position of the APU BLEED pb-sw.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-G-00017552.0001001 / 21 MAR 16
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
PRO-ABN-AIR P 5/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR APU BLEED FAULT (Cont'd)
Ident.: PRO-ABN-AIR-G-00011266.0001001 / 05 AUG 10
STATUS
INOP SYS
APU BLEED (If valve closed)
AIR APU BLEED LEAK
Applicable to: ALL
Ident.: PRO-ABN-AIR-F-00017376.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the APU bleed leak detection loop detects a temperature above
124 °C.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-F-00017553.0001001 / 21 MAR 16
L2
APU BLEED (IF NOT CLOSED)...................................................................................................OFF
When the APU BLEED pb-sw is ON, the FAULT light remains on.
When the APU BLEED pb-sw is OFF, the FAULT light goes off when the overheat disappears.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-ABN-AIR P 6/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR APU BLEED LEAK (Cont'd)
Ident.: PRO-ABN-AIR-F-00011100.0001001 / 05 AUG 10
STATUS
INOP SYS
APU BLEED
AIR BLEED 1(2) OFF
Applicable to: ALL
Ident.: PRO-ABN-AIR-AA-00017374.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the ENG 1(2) BLEED pb-sw is abnormally set to OFF.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-AA-00017555.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
PRO-ABN-AIR P 7/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR COND CTL 1(2) - A(B) FAULT
Applicable to: ALL
Ident.: PRO-ABN-AIR-AC-00017315.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the lane A(B) of ACSC 1(2) is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-AC-00018084.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-AIR-AC-00010777.0001001 / 05 AUG 10
STATUS
INOP SYS
COND CTL 1(2)-A(B)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-AIR P 8/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1(2) BLEED ABNORM PR
Applicable to: ALL
Ident.: PRO-ABN-AIR-B-00017378.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the regulated pressure in the engine bleed duct is abnormal.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-B-00017584.0005001 / 21 MAR 16
If wing anti-ice is off, and both packs are on:
PACK FLOW............................................................................................................................. LO
L2
The PACK FLOW selector must be set to LO, due to precooler performance.
L1
If wing anti-ice is on, and both packs are on:
PACK (AFFECTED)................................................................................................................OFF
L2
One pack must be closed when the flight crew uses wing anti-ice because of precooler
performance.
L1
X BLEED.................................................................................................................................... OPEN
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PRO-ABN-AIR P 9/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1(2) BLEED ABNORM PR (Cont'd)
Ident.: PRO-ABN-AIR-B-00011089.0001001 / 05 AUG 10
STATUS
INOP SYS
ONE PACK ONLY IF WAI ON
ENG 1(2) BLEED
PACK 1(2) (If closed)
AIR ENG 1(2) BLEED FAULT
Applicable to: ALL
Ident.: PRO-ABN-AIR-C-00017369.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the engine 1(2) is running and:
‐ The engine bleed air pressure is above 57 PSI (+3/-0), or
‐ The engine bleed air temperature is above:
‐ 257 °C for more than 55 s
‐ 270 °C for more than 15 s
‐ 290 °C for more than 5 s.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G →
PRO-ABN-AIR P 10/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1(2) BLEED FAULT (Cont'd)
Ident.: PRO-ABN-AIR-C-00017605.0005001 / 21 MAR 16
L2
L1
ENG BLEED (AFFECTED, IF NOT AUTOMATICALLY CLOSED)...............................................OFF
When the ENG BLEED pb-sw is ON, the FAULT light remains on.
When the ENG BLEED pb-sw is OFF, the FAULT light goes off when the failure (overheat or
overpressure) disappears.
If wing anti-ice is off and both packs are on:
PACK FLOW............................................................................................................................. LO
The PACK FLOW selector must be set to LO, due to precooler performance.
If wing anti-ice is on and both packs are on:
PACK (AFFECTED)................................................................................................................OFF
L2
One pack must be closed when the flight crew uses wing anti-ice because of precooler
performance.
L1
X BLEED.................................................................................................................................... OPEN
Ident.: PRO-ABN-AIR-C-00011092.0001001 / 05 AUG 10
STATUS
INOP SYS
ONE PACK ONLY IF WAI ON
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
ENG 1(2) BLEED
PACK 1(2) (If closed)
←G
PRO-ABN-AIR P 11/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1(2) BLEED LO TEMP
(OPPOSITE BLEED AVAILABLE)
Applicable to: ALL
Ident.: PRO-ABN-AIR-M-00017379.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the associated engine bleed supplies bleed air at a temperature below
150 °C in flight and the WING A-ICE pb-sw is set to ON.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-M-00017560.0001001 / 21 MAR 16
A/THR............................................................................................................................................ OFF
THR LEVER (AFFECTED ENGINE)...................................................................................ADVANCE
L2 The thrust lever of the affected engine must be advanced, with the autothrust OFF.
Low bleed temperature may be due to low outside air temperature. Therefore, increasing engine
thrust may increase bleed temperature and clear the ECAM caution.
L1
IF UNSUCCESSFUL:
X BLEED..............................................................................................................................OPEN
ENG BLEED (AFFECTED).....................................................................................................OFF
ASSOCIATED PACK (IF OPPOSITE PACK ON).................................................................. OFF
L2
One pack must be closed, when the flight crew uses wing anti-ice, due to precooler
performance.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H→
PRO-ABN-AIR P 12/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1(2) BLEED LO TEMP (Cont'd)
(OPPOSITE BLEED AVAILABLE)
Ident.: PRO-ABN-AIR-M-00011115.0001001 / 21 AUG 15
STATUS
INOP SYS
ENG 1(2) BLEED
PACK 1(2) (If selected OFF)
AIR ENG 1(2) BLEED LO TEMP
(OPPOSITE BLEED NOT AVAILABLE)
Applicable to: ALL
Ident.: PRO-ABN-AIR-N-00018208.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the associated engine bleed supplies bleed air at a temperature below
150 °C in flight and the WING A-ICE pb-sw is set to ON.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← H to I →
PRO-ABN-AIR P 13/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1(2) BLEED LO TEMP (Cont'd)
(OPPOSITE BLEED NOT AVAILABLE)
Ident.: PRO-ABN-AIR-N-00017561.0001001 / 21 MAR 16
A/THR............................................................................................................................................ OFF
THR LEVER (AFFECTED ENGINE)...................................................................................ADVANCE
L2 The thrust lever of the affected engine must be advanced, with the autothrust OFF.
Low bleed temperature may be due to low outside air temperature. Therefore, increasing engine
thrust may increase bleed temperature and clear the ECAM caution.
L1
IF UNSUCCESSFUL:
WING A. ICE.......................................................................................................................... OFF
AVOID ICING CONDITIONS
Ident.: PRO-ABN-AIR-N-00011117.0003001 / 17 MAR 17
STATUS
INOP SYS
AVOID ICING CONDITIONS
IF SEVERE ICE ACCRETION:
MIN SPD...............................................VLS +10 / G DOT
MANEUVER WITH CARE
LDG DIST PROC...................................................APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I
WING A. ICE
PRO-ABN-AIR P 14/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1+2 BLEED LO TEMP
Applicable to: ALL
Ident.: PRO-ABN-AIR-O-00017381.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both engine bleeds supply bleed air at a temperature below 150 °C in
flight and the WING A-ICE pb-sw is set to ON.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-O-00011118.0001001 / 05 AUG 10
A/THR ...........................................................................................................................................OFF
THR LEVERS......................................................................................................................ADVANCE
L2 The thrust lever of the affected engine must be advanced, with the autothrust OFF.
Low bleed temperature may be due to low outside air temperature. Therefore, increasing engine
thrust may increase bleed temperature and clear the ECAM caution.
L1
IF UNSUCCESSFUL:
WING A. ICE.......................................................................................................................... OFF
AVOID ICING CONDITIONS
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J→
PRO-ABN-AIR P 15/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1+2 BLEED LO TEMP (Cont'd)
Ident.: PRO-ABN-AIR-O-00011119.0003001 / 17 MAR 17
STATUS
INOP SYS
AVOID ICING CONDITIONS
IF SEVERE ICE ACCRETION:
MIN SPD...............................................VLS +10 / G DOT
MANEUVER WITH CARE
LDG DIST PROC...................................................APPLY
WING A. ICE
AIR ENG 1(2) BLEED HI TEMP
Applicable to: ALL
Ident.: PRO-ABN-AIR-P-00017391.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the precooler outlet temperature is above 240 °C.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← J to K →
PRO-ABN-AIR P 16/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1(2) BLEED HI TEMP (Cont'd)
Ident.: PRO-ABN-AIR-P-00014306.0001001 / 21 AUG 15
If wing anti-ice off:
PACK 2 (1)............................................................................................................................. OFF
If wing anti-ice on and opposite pack off:
Note:
If Wing Anti-Ice is required (icing conditions) while operating with one PACK, consider
switching OFF the remaining pack, if aircraft’s altitude permits.
PACK 1 (2) OR WAI...............................................................................................................OFF
If wing anti-ice on and affected pack off:
PACK 2 (1) OR WAI...............................................................................................................OFF
Ident.: PRO-ABN-AIR-P-00014307.0005001 / 17 MAR 17
L12
STATUS
INOP SYS
AVOID ICING CONDITIONS
IF SEVERE ICE ACCRETION:
MIN SPD.................................................. VLS+10/G DOT
Note:
WING A. ICE
In the case of severe ice accretion, with wing
anti-ice failed, the Angle-of-Attack (AOA)
protections remain efficient.
MANEUVER WITH CARE
LDG DIST PROC...................................................APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←K
PRO-ABN-AIR P 17/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1(2) BLEED NOT CLSD
Applicable to: ALL
Ident.: PRO-ABN-AIR-A-00017372.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the engine bleed valve fails to close:
‐ During engine start or when APU BLEED pb-sw is set to ON
‐ At engine shutdown or when APU BLEED pb-sw is set to OFF with engine not running.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-A-00017562.0001001 / 21 MAR 16
ENG BLEED (AFFECTED)........................................................................................................... OFF
L2
Note:
The warning may be triggered due to residual pressure between the HP or IP valves and
the engine bleed valve after:
‐ Engine shutdown, or
‐ APU BLEED pb-sw is selected OFF with engine not running.
Ident.: PRO-ABN-AIR-A-00011087.0001001 / 05 AUG 10
STATUS
INOP SYS
ONE PACK ONLY IF WAI ON
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
ENG 1(2) BLEED
L
PRO-ABN-AIR P 18/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR ENG 1(2) HP VALVE FAULT
Applicable to: ALL
Ident.: PRO-ABN-AIR-H-00017384.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the HP valve is abnormally closed.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-H-00011103.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-AIR-H-00011104.0001001 / 05 AUG 10
STATUS
AIR PRESS LOW AT IDLE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
M
PRO-ABN-AIR P 19/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR FWD(AFT) CRG VENT FAULT
Applicable to: ALL
Ident.: PRO-ABN-AIR-AE-00017337.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the forward(aft) cargo ventilation fan is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-AE-00017933.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-AIR-AE-00017934.0001001 / 21 MAR 16
STATUS
INOP SYS
FWD(AFT) CRG HEAT
FWD(AFT) CRG VENT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
N
PRO-ABN-AIR P 20/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR L(R) WING OR ENG 1(2) BLEED LEAK
Applicable to: ALL
Ident.: PRO-ABN-AIR-D-00017370.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
The AIR L(R) WING LEAK alert triggers when both wing bleed leak detection loops detect a
temperature above 124 °C .
The AIR ENG 1(2) BLEED LEAK alert triggers when the pylon bleed leak detection loop detects
a temperature above 204 °C and engine 1(2) is running.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-D-00017563.0001001 / 21 MAR 16
L2
L1
ENG BLEED (AFFECTED, IF NOT AUTOMATICALLY CLOSED)...............................................OFF
When the ENG BLEED pb-sw is ON, the FAULT light remains on.
When the ENG BLEED pb-sw is OFF, the FAULT light goes off when the overheat disappears.
If left wing or engine 1 bleed leak:
APU BLEED (IF NOT CLOSED)............................................................................................ OFF
X BLEED (IF NOT CLOSED).....................................................................................................SHUT
WING ANTI-ICE............................................................................................................................ OFF
AVOID ICING CONDITIONS
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
O→
PRO-ABN-AIR P 21/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR L(R) WING OR ENG 1(2) BLEED LEAK (Cont'd)
Ident.: PRO-ABN-AIR-D-00011096.0003001 / 17 MAR 17
STATUS
INOP SYS
AVOID ICING CONDITIONS
IF SEVERE ICE ACCRETION:
MIN SPD...............................................VLS +10 / G DOT
MANEUVER WITH CARE
LDG DIST PROC...................................................APPLY
WING A.ICE
ENG 1(2) BLEED
PACK 1(2)
AIR L(R) WNG LEAK DET FAULT
Applicable to: ALL
Ident.: PRO-ABN-AIR-J-00017387.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both wing bleed leak detection loops are inoperative in one wing.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-J-00011107.0001001 / 25 FEB 14
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← O to P →
PRO-ABN-AIR P 22/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR L(R) WNG LEAK DET FAULT (Cont'd)
Ident.: PRO-ABN-AIR-J-00011108.0005001 / 17 MAR 11
STATUS
INOP SYS
L(R) WNG LK DET
AIR PACK 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-AIR-AF-00017290.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The position of the pack flow control valve disagrees with the commanded position, or
‐ The pack valve is closed.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-AF-00010712.0001001 / 05 AUG 10
PACK (AFFECTED)...................................................................................................................... OFF
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← P to Q →
PRO-ABN-AIR P 23/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR PACK 1(2) FAULT (Cont'd)
Ident.: PRO-ABN-AIR-AF-00010713.0002001 / 16 NOV 11
STATUS
INOP SYS
If ACSC 1 failed:
CKPT AT FIXED TEMP
If ACSC 2 failed:
CAB AT FIXED TEMP
PACK 1(2)
COND CTL 1(2)
FWD CRG HEAT (If ACSC
1 failed)
AIR PACK 1+2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-AIR-AG-00017292.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both ACSCs are failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← Q to R →
PRO-ABN-AIR P 24/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR PACK 1+2 FAULT (Cont'd)
Ident.: PRO-ABN-AIR-AG-00017935.0001001 / 21 MAR 16
L2
PACK (AFFECTED)...................................................................................................................... OFF
The fault light goes off, when the failure disappears.
Note:
L1
L2
L1
The rate at which the cabin altitude increases may be minimized by closing the FWD
CARGO ISOL VALVE , if the cargo freight permits.
DESCENT TO FL 100/MEA.
Descend to FL 100, or MEA, whichever is higher.
WHEN DIFF PR < 1 PSI AND FL BELOW 100:
RAM AIR...................................................................................................................................ON
MAX FL........................................................................................................................... 100/MEA
If FAULT was due to an overheat:
ASSOCIATED PROCEDURES
AIR PACK 1 (2) OVHT
WHEN PACK OVHT OUT:
PACK (AFFECTED)........................................................................................................... ON
Ident.: PRO-ABN-AIR-AG-00017936.0002001 / 17 MAR 17
STATUS
If packs not recovered:
MAX FL............................................................... 100/MEA
CKPT AT FIXED TEMP
CAB AT FIXED TEMP
If FAULT was due to an overheat:
WHEN PACK OVHT OUT:
PACK (AFFECTED)........................................ ON
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←R
INOP SYS
PACK 1 + 2
COND CTL 1
COND CTL 2
FWD CRG HEAT
PRO-ABN-AIR P 25/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR PACK 1(2) OFF
Applicable to: ALL
Ident.: PRO-ABN-AIR-AJ-00017294.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the PACK 1(2) pb-sw is set to OFF and no failure is detected.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-AJ-00017941.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-AIR-AJ-00010715.0001001 / 05 AUG 10
STATUS
INOP SYS
PACK 1(2)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
S
PRO-ABN-AIR P 26/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR PACK 1(2) OVHT
Applicable to: ALL
Ident.: PRO-ABN-AIR-AK-00017284.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the pack compressor outlet temperature rises above 260 °C.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-AK-00017942.0001001 / 21 MAR 16
L2
L1
PACK (AFFECTED)...................................................................................................................... OFF
High flow is automatically selected on the remaining pack.
Fault light goes off, when the overheat disappears.
WHEN PACK OVHT OUT:
PACK (AFFECTED)..................................................................................................................ON
Ident.: PRO-ABN-AIR-AK-00010711.0001001 / 10 JAN 11
STATUS
WHEN PACK OVHT OUT:
PACK (AFFECTED)..................................................... ON
(1)
INOP SYS
PACK 1(2)
(1)
(If pack not recovered)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
T
PRO-ABN-AIR P 27/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR PACK 1(2) REGUL FAULT
Applicable to: ALL
Ident.: PRO-ABN-AIR-AL-00017298.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the temperature regulation performance is degraded.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-AL-00018089.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-AIR-AL-00010719.0003001 / 10 JAN 11
STATUS
INOP SYS
PACK 1(2) REGUL
HOT AIR
(1)
(2)
(1)
(2)
(In case of By Pass Valve or RAM Air Inlet failure)
(In case of Flow Control Valve in backup mode)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
U
PRO-ABN-AIR P 28/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR X BLEED FAULT
Applicable to: ALL
Ident.: PRO-ABN-AIR-E-00017383.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the crossbleed valve position disagrees with the X-BLEED selector
position.
Flight Phase Inhibition:
Ident.: PRO-ABN-AIR-E-00011097.0001001 / 05 AUG 10
L2
L1
X BLEED.............................................................................................................................. MAN CTL
Select OPEN, when the APU BLEED pb-sw is ON, or for engine start, or when WING ANTI-ICE
pb-sw is ON and one bleed is inoperative.
Select SHUT in other cases.
If manual opening inoperative, and only one bleed available:
WING ANTI ICE......................................................................................................................OFF
AVOID ICING CONDITIONS
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
V→
PRO-ABN-AIR P 29/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AIR
FLIGHT CREW
OPERATING MANUAL
AIR X BLEED FAULT (Cont'd)
Ident.: PRO-ABN-AIR-E-00017612.0002001 / 21 MAR 16
STATUS
If manual opening inoperative, and only one bleed
available:
AVOID ICING CONDITIONS
IF SEVERE ICE ACCRETION:
MIN SPD........................................ VLS +10 / G DOT
MANEUVER WITH CARE
INOP SYS
WING A.ICE
X BLEED
LDG DIST PROC...................................................APPLY
X BLEED MAN CTL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←V
PRO-ABN-AIR P 30/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
APU
FLIGHT CREW
OPERATING MANUAL
APU AUTO (EMER) SHUT DOWN
Applicable to: ALL
Ident.: PRO-ABN-APU-A-00016876.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
The APU AUTO SHUT DOWN alert triggers when an automatic shutdown of the APU occurs
for a reason other than a fire.
The APU EMER SHUT DOWN triggers when:
‐ The APU SHUT OFF sw on the External Power Panel is pushed or,
‐ The APU FIRE pb is pushed or,
‐ An APU fire on ground is detected.
Flight Phase Inhibition:
Ident.: PRO-ABN-APU-A-00018193.0001001 / 21 MAR 16
MASTER SW.................................................................................................................................OFF
Ident.: PRO-ABN-APU-A-00010106.0001001 / 05 AUG 10
STATUS
INOP SYS
APU
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-APU P 1/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
APU
FLIGHT CREW
OPERATING MANUAL
APU FIRE DET FAULT
Applicable to: ALL
Ident.: PRO-ABN-APU-D-00021359.0001001 / 17 MAR 17
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ Both loops are inoperative, or
‐ Fire Detector Unit is inoperative.
Flight Phase Inhibition:
Ident.: PRO-ABN-APU-D-00021360.0001001 / 17 MAR 17
Crew awareness.
Ident.: PRO-ABN-APU-D-00021361.0001001 / 17 MAR 17
STATUS
INOP SYS
APU FIRE DET
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PRO-ABN-APU P 2/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
APU
FLIGHT CREW
OPERATING MANUAL
APU FIRE LOOP A(B) FAULT
Applicable to: ALL
Ident.: PRO-ABN-APU-B-00021362.0001001 / 17 MAR 17
ANNUNCIATIONS
Flight Phase Inhibition:
Ident.: PRO-ABN-APU-B-00021363.0001001 / 17 MAR 17
L2
Crew awareness.
Ident.: PRO-ABN-APU-B-00021364.0001001 / 17 MAR 17
STATUS
INOP SYS
APU LOOP A(B)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-APU P 3/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
APU
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-APU P 4/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
APU FIRE
FLIGHT CREW
OPERATING MANUAL
APU FIRE
Applicable to: ALL
Ident.: PRO-ABN-APUF-C-00017402.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ Fire is detected by both loops, or
‐ Fire is detected by one loop when the other loop is faulty, or
‐ A rupture occurs in both loops within 5 s.
Flight Phase Inhibition:
Ident.: PRO-ABN-APUF-C-00017925.0001001 / 21 MAR 16
LAND ASAP
APU FIRE P/B............................................................................................................................ PUSH
APU LP valve closes.
Aural warning stops.
APU FIRE pb-sw remains on, as long as a fire is detected.
L1 AGENT AFTER 10 S................................................................................................................ DISCH
L2 The 10 s delay allows the airflow to decrease, which increases the effect of the agent.
Automatic countdown on the ECAM.
L1 MASTER SW.................................................................................................................................OFF
L2 Do not attempt to restart the APU.
L2
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-ABN-APUF P 1/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
APU FIRE
FLIGHT CREW
OPERATING MANUAL
APU FIRE (Cont'd)
Ident.: PRO-ABN-APUF-C-00012211.0001001 / 16 NOV 11
STATUS
INOP SYS
APU
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-ABN-APUF P 2/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT A/THR LIMITED
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-S-00016943.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when A/THR is active but thrust levers are set below CL detent (2 engines),
or MCT detent (1 engine).
This caution is repeated every 5 s as long as the thrust lever are not moved.
Flight Phase Inhibition:
Ident.: PRO-ABN-AUTO_FLT-S-00018689.0001001 / 21 MAR 16
L2
THR LEVERS.............................................................................................................................MOVE
Thrust lever must be set in the relevant detent.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-AUTO_FLT P 1/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT A/THR OFF
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-L-00016941.0002001 / 20 APR 17
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when this warning is displayed only for involuntary disconnection. The amber
A/THR OFF and ENG THRUST LOCKED messages are displayed in the left lower part of
ECAM upper DU.
For voluntary disconnection, an amber A/THR OFF message is displayed on the right lower
part of ECAM upper DU.
Flight Phase Inhibition:
Ident.: PRO-ABN-AUTO_FLT-L-00018694.0002001 / 21 MAR 16
L2
If the A/THR is failed, the flight crew may recover it by engaging the other AP , and then trying to
re-engage the A/THR.
Note:
L1
L2
If the A/THR is recovered with AP 2, A/THR will be lost again at AP 2 disengagement.
THR LEVERS.............................................................................................................................MOVE
If the thrust levers are not moved within 5 s, the “ENG THRUST LOCKED” warning is displayed
(Refer to PRO-ABN-ENG ENG THRUST LOCKED).
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-ABN-AUTO_FLT P 2/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT A/THR OFF (Cont'd)
Ident.: PRO-ABN-AUTO_FLT-L-00010469.0001001 / 05 AUG 10
STATUS
INOP SYS
CAT 2 ONLY
A/THR
CAT 3
AUTO FLT AP OFF
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-K-00016947.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when this warning is displayed only for involuntary disconnection.
For voluntary disconnection, a red AP OFF message is displayed in the right lower part of
ECAM upper DU.
Flight Phase Inhibition:
Ident.: PRO-ABN-AUTO_FLT-K-00018695.0001001 / 21 MAR 16
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-ABN-AUTO_FLT P 3/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT AP OFF (Cont'd)
Ident.: PRO-ABN-AUTO_FLT-K-00017453.0002001 / 21 MAR 16
STATUS
INOP SYS
AP (Affected)
CAT 2
(1)
GLS AUTOLAND
(1)
(1)
(If both AP lost)
AUTO FLT FAC 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-G-00016911.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one FAC computer is failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
PRO-ABN-AUTO_FLT P 4/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT FAC 1(2) FAULT (Cont'd)
Ident.: PRO-ABN-AUTO_FLT-G-00010457.0001001 / 05 AUG 10
FAC (AFFECTED)....................................................................................................... OFF THEN ON
IF UNSUCCESSFUL:
FAC (AFFECTED).................................................................................................................. OFF
L2
All functions are performed by the remaining FAC.
Ident.: PRO-ABN-AUTO_FLT-G-00017506.0001001 / 21 MAR 16
L12
STATUS
INOP SYS
BOTH PFD ON SAME FAC
(1)
See
CAT 3 SINGLE ONLY
(1)
CAT 3 DUAL
FAC 1(2)
Characteristic speeds, displayed on the two PFD s, are computed by the same FAC.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PRO-ABN-AUTO_FLT P 5/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT FAC 1 + 2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-H-00016926.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the two FAC computers are failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
PRO-ABN-AUTO_FLT P 6/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT FAC 1 + 2 FAULT (Cont'd)
Ident.: PRO-ABN-AUTO_FLT-H-00017454.0002001 / 22 MAR 17
RUD WITH CARE ABV 160 KT
Depending on when the failure occurs, the rudder travel limiter system may not be in the correct
position for the flight speed. Therefore, to prevent damage to the aircraft structure, use the rudder
with care, when the speed is above 160 kt.
At slats’ extension, full rudder travel authority is recovered.
L1 FAC 1 ......................................................................................................................... OFF THEN ON
FAC 2.......................................................................................................................... OFF THEN ON
IF UNSUCCESSFUL:
FAC 1 + 2...............................................................................................................................OFF
L2
With FAC 1 + 2 inoperative, the rudder travel limit system, rudder trim control, yaw damper and
PFD characteristic speeds are lost.
L2
L12
ASSOCIATED PROCEDURES
L1
L2
F/CTL ALTN LAW
(PROT LOST)
F/CTL normal laws are lost. All protections, except maneuver protections, are lost.
MAX SPEED...................................................................................................................... 320 KT
Speed is limited, due to the loss of high-speed protections.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
PRO-ABN-AUTO_FLT P 7/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT FAC 1 + 2 FAULT (Cont'd)
Ident.: PRO-ABN-AUTO_FLT-H-00017456.0006001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320 KT
RUD WITH CARE ABV 160 KT
APPR PROC
INOP SYS
WNDSHEAR DET
(1)
(1)
FOR LDG............................................................ USE FLAP 3
This line is replaced by "FOR LDG : USE FLAP 3" when
CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3...........................................................ON
Displayed, when flaps in CONF 3.
APPR SPD....................................................... VREF + 10 KT
LDG DIST PROC......................................................... APPLY
REAC W/S DET
F/CTL PROT
FAC 1 + 2
AP 1 + 2
A/THR
CAT 2
GLS AUTOLAND
STEEP APPR
ROW/ROP
ALTN LAW : PROT LOST
WHEN L/G DN : DIRECT LAW
(2)
See
(1)
(2)
(The REAC W/S DET inop sys replaces the WNDSHEAR DET inop sys on aircraft equipped with
the PWS )
At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-ABN-AUTO_FLT P 8/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT FCU 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-J-00016923.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when only one FCU channel remain operative.
Flight Phase Inhibition:
Ident.: PRO-ABN-AUTO_FLT-J-00010464.0001001 / 05 AUG 10
L2
BARO REF........................................................................................................................... X CHECK
One FCU channel is lost:
Therefore, crosscheck the barometric reference settings on the FCU and PFDs.
Ident.: PRO-ABN-AUTO_FLT-J-00010465.0001001 / 05 AUG 10
STATUS
INOP SYS
FCU 1(2)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-ABN-AUTO_FLT P 9/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT FCU 1 + 2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-I-00016946.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the FCU is completely loss.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G→
PRO-ABN-AUTO_FLT P 10/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT FCU 1 + 2 FAULT (Cont'd)
Ident.: PRO-ABN-AUTO_FLT-I-00017463.0001001 / 21 MAR 16
L2
PFD BARO REF: STD ONLY
With both FCU channels failed, the barometer reference automatically goes to 1 013 hPa.
Use standby altimeter, and change this to the actual barometer setting.
Do not insert the MDA (MDH) value on the MCDU PERF APPR Page (because the PFD altitude is
referenced to STD, and not to the correct barometric value).
The PM must then perform the standard callouts ("HUNDRED ABOVE"and "MINIMUM"), using the
STBY altimeter.
In addition:
‐ All FCU controls are inoperative.
‐ A/THR , AP 1 + 2, and FD 1 + 2 are not available.
(Except in LAND or GO AROUND mode where only A/THR is lost).
‐ On PFD:
• Altitude alert is inoperative.
• ILS/GLS /MLS deviation scales are displayed.
• Flight path vector is displayed.
• Mach indication is inoperative.
• FMA is lost except in LAND or GA mode.
‐ On ND:
• ROSE NAV mode with map (80 NM range) is displayed.
• VOR /ADF needles:
Needle 1 is related to VOR1 only.
Needle 2 is related to ADF 2 only (ADF 1 if ADF2 not installed).
(VOR selection on DDRMI is not affected)
(ADF selection on DDRMI (if available) is not affected).
• The weather radar image may be lost. If the image remains displayed it must be disregarded.
In all cases, red "WXR RNG" message is displayed.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
PRO-ABN-AUTO_FLT P 11/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT FCU 1 + 2 FAULT (Cont'd)
Ident.: PRO-ABN-AUTO_FLT-I-00017512.0002001 / 21 MAR 16
STATUS
INOP SYS
PFD BARO REF : STD ONLY
If in LAND or GA:
CAT 2 ONLY
FCU 1 + 2
AP 1 + 2
A/THR
CAT 3
(1)
(2)
(1)
CAT 2
GPWS TERR
(1)
(2)
(If not LAND or GA)
(If in LAND or GA mode)
AUTO FLT REAC W/S DET FAULT
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-N-00017473.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the reactive windshear function is lost.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← G to H →
PRO-ABN-AUTO_FLT P 12/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT REAC W/S DET FAULT (Cont'd)
Ident.: PRO-ABN-AUTO_FLT-N-00017479.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-AUTO_FLT-N-00017480.0001001 / 21 MAR 16
L12
STATUS
INOP SYS
REAC W/S DET
Note:
On ground, this warning may appear spuriously. This warning is cancelled by resetting
both FACs, one after the other.
‐ FAC 1: Pull then push AUTO FLT/FAC 1/26VAC and 28VDC circuit breakers BO3
and B04 on 49VU.
‐ FAC 2: Pull then push AUTO FLT/FAC 2/26VAC and 28VDC circuit breakers M18
and M19 on 121VU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H
PRO-ABN-AUTO_FLT P 13/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT RUD TRIM 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-C-00016921.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one rudder trim actuator is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-AUTO_FLT-C-00010449.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-AUTO_FLT-C-00017513.0001001 / 21 MAR 16
STATUS
INOP SYS
CAT 3 SINGLE ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
CAT 3 DUAL
RUD TRIM 1(2)
I
PRO-ABN-AUTO_FLT P 14/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT RUD TRIM SYS
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-D-00016928.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the rudder trim system is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-AUTO_FLT-D-00010451.0002001 / 05 AUG 10
FAC 1.......................................................................................................................... OFF THEN ON
FAC 2.......................................................................................................................... OFF THEN ON
Ident.: PRO-ABN-AUTO_FLT-D-00017464.0002001 / 21 MAR 16
STATUS
INOP SYS
RUD TRIM
AP 1 + 2
CAT 2
GLS AUTOLAND
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J
PRO-ABN-AUTO_FLT P 15/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT RUD TRV LIM 1(2)
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-E-00016922.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one rudder travel limitation actuator is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-AUTO_FLT-E-00010453.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-AUTO_FLT-E-00010454.0001001 / 05 AUG 10
STATUS
INOP SYS
RUD TRV LIM 1(2)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K
PRO-ABN-AUTO_FLT P 16/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT RUD TRV LIM SYS
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-F-00016929.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the rudder travel limitation system is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-AUTO_FLT-F-00017465.0003001 / 22 MAR 17
RUD WITH CARE ABV 160 KT
Depending on when the failure occurs, the rudder travel limiter system may not be in the correct
position for the flight speed. Therefore, to prevent damage to the aircraft structure, use the rudder
with care, when the speed is greater than 160 kt.
At slats’ extension, full rudder travel authority can be recovered.
L1 FAC 1.......................................................................................................................... OFF THEN ON
FAC 2.......................................................................................................................... OFF THEN ON
If TLU (rudder or pedals) remains locked at high speed after slat extension:
MAX X WIND FOR LDG 15 KT
AUTO BRK..............................................................................................................DO NOT USE
L2
Do not use the autobrake, so as not to delay the application of differential braking at landing
roll.
L2
L1
AT LDG ROLL:
DIFF BRAKING............................................................................................................. AS RQRD
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
L→
PRO-ABN-AUTO_FLT P 17/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT RUD TRV LIM SYS (Cont'd)
Ident.: PRO-ABN-AUTO_FLT-F-00017467.0003001 / 22 MAR 17
L12
STATUS
INOP SYS
RUD WITH CARE ABV 160 KT
If TLU (rudder or pedals) remains locked at high
speed after slat extension:
MAX X WIND FOR LDG 15 KT
AUTO BRK................................................. DO NOT USE
Do not use the autobrake, so as not to delay the
application of differential braking at landing roll.
AT LDG ROLL:
DIFF BRAKING.......................................... AS RQRD
RUD TRV LIM
CAT 3 SINGLE ONLY
Note:
An autoland must not be performed with a crosswind greater than 12 kt.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←L
PRO-ABN-AUTO_FLT P 18/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT YAW DAMPER 1(2)
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-A-00016912.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one yaw damper actuator is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-AUTO_FLT-A-00010444.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-AUTO_FLT-A-00017515.0001001 / 21 MAR 16
STATUS
INOP SYS
CAT 3 SINGLE ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
CAT 3 DUAL
YAW DAMPER 1(2)
M
PRO-ABN-AUTO_FLT P 19/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT YAW DAMPER SYS
Applicable to: ALL
Ident.: PRO-ABN-AUTO_FLT-B-00016927.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
This alert triggers when the yaw damper system is failed.
L2
Flight Phase Inhibition:
Ident.: PRO-ABN-AUTO_FLT-B-00017469.0002001 / 22 MAR 17
L2
L1
Loss of yaw dampers 1 + 2.
FAC 1.......................................................................................................................... OFF THEN ON
FAC 2.......................................................................................................................... OFF THEN ON
If fault remains:
L12
ASSOCIATED PROCEDURES
F/CTL ALTN LAW
(PROT LOST)
F/CTL normal laws are lost. All protections, except maneuver protections, are lost.
MAX SPEED...................................................................................................................... 320 KT
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
N→
PRO-ABN-AUTO_FLT P 20/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
AUTO FLT YAW DAMPER SYS (Cont'd)
Ident.: PRO-ABN-AUTO_FLT-B-00017470.0003001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320 KT
Speed is limited, due to the loss of high-speed protections.
APPR PROC
FOR LDG............................................................ USE FLAP 3
This line is replaced by "FOR LDG : USE FLAP 3" when
CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3...........................................................ON
Will be displayed, when flaps in CONF 3.
APPR SPD....................................................... VREF + 10 KT
LDG DIST PROC......................................................... APPLY
INOP SYS
F/CTL PROT
YAW DAMPER
AP 1 + 2
CAT 2
STEEP APPR
GLS AUTOLAND
ALTN LAW : PROT LOST
WHEN L/G DN : DIRECT LAW
(1)
See
(1)
At landing gear extension, control reverts to direct law in pitch,as well as in roll
Refer to PRO-ABN-F_CTL F/CTL DIRECT LAW.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←N
PRO-ABN-AUTO_FLT P 21/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AUTO FLT
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-AUTO_FLT P 22/22
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AVIONICS SMOKE
FLIGHT CREW
OPERATING MANUAL
AVIONICS SMOKE
Applicable to: ALL
Ident.: PRO-ABN-AVNCS-M-00017405.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when smoke in the ventilation extraction duct is detected.
Flight Phase Inhibition:
Ident.: PRO-ABN-AVNCS-M-00014922.0001001 / 22 MAR 17
L2
The description of this procedure is included in the SMOKE/FUMES/AVNCS SMOKE procedure
(Refer to procedure)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-AVNCS P 1/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
AVIONICS SMOKE
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-AVNCS P 2/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BLEED
FLIGHT CREW
OPERATING MANUAL
BLEED MONITORING FAULT
Applicable to: ALL
Ident.: PRO-ABN-BLEED-L-00017385.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both BMC are failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-BLEED-L-00011111.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-BLEED-L-00011112.0001001 / 05 AUG 10
STATUS
INOP SYS
BMC 1 + 2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-BLEED P 1/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BLEED
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-BLEED P 2/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
[MEM] LOSS OF BRAKING
Ident.: PRO-ABN-BRAKES-00011315.0001001 / 17 MAR 17
Applicable to: ALL
IF NO BRAKING AVAILABLE:
REV........................................................................................................................................ MAX
BRAKE PEDALS........................................................................................................... RELEASE
Brake pedals should be released when the A/SKID & N/W STRG sw is switched OFF, since
the pedal force or displacement produces more braking action in alternate mode than in normal
mode.
A/SKID OFF...................................................................................................................... ORDER
L2
The PF orders the PM to set the A/SKID & N/W STRG sw to OFF.
L1
A/SKID & N/W STRG............................................................................................................. OFF
Braking system reverts to alternate mode.
BRAKE PEDALS................................................................................................................PRESS
Apply brake with care, since initial pedal force or displacement produces more braking action in
alternate mode than in normal mode.
MAX BRK PR..................................................................................................................1000 PSI
Monitor brake pressure or BRAKES PRESS indicator. Limit brake pressure to approximately
1 000 PSI and, at low ground speed, adjust brake pressure as required.
If STILL NO BRAKING:
PARKING BRAKE...........................................SHORT AND SUCCESSIVE APPLICATIONS
Use short successive parking brake applications to stop the aircraft. Brake onset
asymmetry may be felt at each parking brake application. If possible, delay the use of the
parking brake until low speed, to reduce the risk of tire burst and lateral control difficulties.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-BRAKES P 1/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
[QRH] ASYMMETRIC BRAKING
Ident.: PRO-ABN-BRAKES-00011331.0001001 / 17 MAR 17
Applicable to: ALL
Apply this procedure when all brakes of one gear are released.
AVOID XWIND > 10 KT FROM SIDE OF AVAILABLE BRAKE
APPLY BRAKE PROGRESSIVELY ON AVAILABLE SIDE
USE RUDDER TO COUNTER LATERAL DEVIATION
If reverser inoperative on same side as inoperative brakes: DO NOT USE REVERSERS
LDG DIST PROC......................................................................................................................APPLY
[QRH] RESIDUAL BRAKING
Ident.: PRO-ABN-BRAKES-00011318.0001001 / 17 MAR 17
Applicable to: ALL
In flight:
BRAKE PEDALS..................................................................................PRESS SEVERAL TIMES
Press the brake pedals several times. This could zero a residual pressure on the alternate
system.
If residual pressure remains:
A/SKID & N/W STRG sel........................................................................................KEEP ON
For landing:
AUTO/BRK................................................................................................................ MED
Using MED mode gives immediate priority to normal braking upon landing gear
touchdown, which cancels residual alternate pressure.
If autobrake not available:
APPLY BRAKING JUST AFTER TOUCHDOWN
POSSIBLE BRAKING ASYMMETRY
Note:
If tire damage is suspected after landing, Refer to LIM-LG Taxi with Deflated or
Damaged Tires.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B to C
PRO-ABN-BRAKES P 2/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES A/SKID N/WS FAULT OR ANTI SKID N/WS OFF
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-J-00017807.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ There is a loss of normal brake system associated with Y HYD SYS LO PRESS, or
‐ Both BSCU channels are failed, or
‐ The A/SKID & N/W STRG sw is set to OFF.
Flight Phase Inhibition:
Ident.: PRO-ABN-BRAKES-J-00018571.0001001 / 21 MAR 16
L2
MAX BRK PR........................................................................................................................ 1000 PSI
Monitor brake pressure on the BRAKES PRESS indicator. Limit brake pressure to approximately
1 000 PSI and, at low ground speed, adjust brake pressure as required. Avoid landing on an icy
runway.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PRO-ABN-BRAKES P 3/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES A/SKID N/WS FAULT OR ANTI SKID N/WS OFF (Cont'd)
Ident.: PRO-ABN-BRAKES-J-00018670.0003001 / 21 MAR 16
L12
STATUS
MAX BRK PR............................................................1000 PSI
LDG DIST PROC......................................................... APPLY
If Y SYS LO PR:
BRK Y ACCU PR ONLY
CAT 3 SINGLE ONLY
(1)
See
(1)
Note:
INOP SYS
CAT 3 DUAL
ANTI SKID
N/W STRG
NORM BRK
AUTO BRK
Automatic rollout is not permitted as specified in QRH (Refer to QRH/OPS Required
Equipment for CAT2 and CAT3).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PRO-ABN-BRAKES P 4/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES ALTN BRK FAULT
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-R-00017816.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the alternate braking function is lost.
Flight Phase Inhibition:
Ident.: PRO-ABN-BRAKES-R-00018357.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-BRAKES-R-00011328.0001001 / 05 AUG 10
STATUS
INOP SYS
ALTN BRK
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-BRAKES P 5/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES ALTN L(R) RELEASED
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-S-00017817.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the brakes of one gear is released.
It is detected when the landing gear is downlocked, at least one engine is running, and
alternate braking is active.
Flight Phase Inhibition:
Ident.: PRO-ABN-BRAKES-S-00011329.0001001 / 05 AUG 10
L2
As long as the normal braking system is available, braking is normal. In alternate braking mode,
braking of all wheels on one gear is lost.
L1
If normal braking is lost:
ASYM BRK PROC............................................................................................................. APPLY
Ident.: PRO-ABN-BRAKES-S-00011330.0001001 / 11 MAY 12
STATUS
If normal braking is lost:
LDG DIST PROC...................................................APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
INOP SYS
ALTN L(R) BRK
PRO-ABN-BRAKES P 6/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES AUTO BRK FAULT
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-N-00017806.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the autobrake is failed, after being armed.
Flight Phase Inhibition:
Ident.: PRO-ABN-BRAKES-N-00018672.0004001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-BRAKES-N-00011314.0004001 / 29 MAR 12
STATUS
INOP SYS
AUTO BRK
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
PRO-ABN-BRAKES P 7/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES BRK Y ACCU LO PR
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-T-00017820.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the yellow accumulator is in low pressure.
Flight Phase Inhibition:
Ident.: PRO-ABN-BRAKES-T-00011332.0002001 / 05 AUG 10
L2
The yellow electrical pump can be used to pressurize the accumulator. If the accumulator pressure
is still low, chocks are required before Engine 1 shut down. This message is replaced on ground by
BRAKES PARK BRK LO PR if parking brake is on and yellow hydraulic system pressure is low.
L1
On ground:
BEFORE ENG SHUT DOWN:
CHOCKS CONSIDER
Ident.: PRO-ABN-BRAKES-T-00011333.0001001 / 05 AUG 10
STATUS
INOP SYS
If Y SYS LO PR
NORM BRK ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
BRK Y ACCU
H
PRO-ABN-BRAKES P 8/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES HOT
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-M-00017786.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one brake temperature is above 300 °C. The alert disappears when the
highest brake temperature is below 290 °C.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I→
PRO-ABN-BRAKES P 9/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES HOT (Cont'd)
Ident.: PRO-ABN-BRAKES-M-00018675.0008001 / 21 MAR 17
On ground:
PARK BRK: PREFER CHOCKS
L2
If the BRAKES HOT alert is still on when the aircraft is parked, the flight crew should not set the
PARKING BRK ON.
L1
BRK FAN .........................................................................................................................ON
L2
Note:
L1
DELAY T.O. FOR COOL
L2
‐ Delay takeoff, until the brake temperature is below 300 °C with the brake fans OFF, and
150 °C with the brake fans ON
‐ Refer to PRO-NOR-SOP-21 After Landing - Brake Temperature for brake temperature
limitations requiring maintenance actions.
Before they select the brake fans at the gate, the flight crew should first warn the
ground personnel in order to avoid blowing carbon brake dust on them.
L1
In flight:
IF PERF PERMITS:
MAX SPEED................................................................................................................250/.60
L/G..................................................................................................................DN FOR COOL
L2
If performance permits, the landing gear should be extended or, if already extended, it
should remain so, to improve brake cooling.
L1
L2
FOR L/G RETRACTION:
MAX SPEED................................................................................................................220/.54
Reduce speed for landing gear retraction, when the brake temperature is within limits.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
PRO-ABN-BRAKES P 10/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES HOT (Cont'd)
Ident.: PRO-ABN-BRAKES-M-00011312.0001001 / 05 AUG 10
L12
STATUS
MAX SPEED................................................................ 280/.67
(1)
See
(1)
As long as the landing gear is extended, limit the speed to 280 kt/M 0.67.
For landing gear retraction when the brake temperature is within limits, reduce the speed to
220 kt.
BRAKES NORM + ALTN FAULT
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-Q-00017819.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the normal and alternate braking functions are lost. The parking brake
is still available.
Flight Phase Inhibition:
Ident.: PRO-ABN-BRAKES-Q-00018358.0001001 / 21 MAR 16
PARK BRK ONLY
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← I to J →
PRO-ABN-BRAKES P 11/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES NORM + ALTN FAULT (Cont'd)
Ident.: PRO-ABN-BRAKES-Q-00011325.0001001 / 11 MAY 12
STATUS
INOP SYS
PARK BRK ONLY
LDG DIST PROC......................................................... APPLY
CAT 2 ONLY
CAT 3
ANTI SKID
N/W STRG
NORM BRK
AUTO BRK
ALTN BRK
BRAKES NORM BRK FAULT
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-O-00017814.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the normal braking function is lost.
Flight Phase Inhibition:
Ident.: PRO-ABN-BRAKES-O-00018679.0001001 / 21 MAR 16
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← J to K →
PRO-ABN-BRAKES P 12/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES NORM BRK FAULT (Cont'd)
Ident.: PRO-ABN-BRAKES-O-00011321.0001001 / 11 MAY 12
STATUS
LDG DIST PROC......................................................... APPLY
ALTN Y BRK WITH A/SKID
CAT 2 ONLY
INOP SYS
CAT 3
NORM BRK
AUTO BRK
BRAKES PARK BRK FAULT
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-X-00017823.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when a discrepancy between the position of the parking brake handle and
the applied parking brake pressure is detected.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← K to L →
PRO-ABN-BRAKES P 13/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES PARK BRK FAULT (Cont'd)
Ident.: PRO-ABN-BRAKES-X-00018359.0002001 / 20 MAY 16
On ground:
If PARKING BRK handle is OFF and parking brake pressure is still applied:
BRK PRESS STILL APPLIED
If PARKING BRK handle is ON and no parking brake pressure is applied:
BRK PRESS RELEASED
PARK BRK....................................................................................................................... OFF
BEFORE ENG SHUT DOWN:
CHOCKS........................................................................................................ CONSIDER
BRAKES PARK BRK LO PR
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-U-00017821.0003001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the pressure in the yellow accumulator and hydraulic system is low and
the parking brake is on.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← L to M →
PRO-ABN-BRAKES P 14/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES PARK BRK LO PR (Cont'd)
Ident.: PRO-ABN-BRAKES-U-00018572.0003001 / 21 MAR 16
L2
Chocks are required before Engine 1 shut down.
L1
On ground:
BEFORE ENG SHUT DOWN:
CHOCKS CONSIDER
Ident.: PRO-ABN-BRAKES-U-00011335.0003001 / 05 AUG 10
STATUS
INOP SYS
NORM BRK ONLY
BRK Y ACCU
BRAKES PARK BRK ON
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-Y-00017815.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the parking brake is ON in flight.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← M to N →
PRO-ABN-BRAKES P 15/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES PARK BRK ON (Cont'd)
Ident.: PRO-ABN-BRAKES-Y-00018360.0001001 / 21 MAR 16
PARK BRK.................................................................................................................................... OFF
BRAKES RELEASED
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-P-00017813.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the brake of one wheel is released. It is detected when the landing gear
is downlocked, at least one engine is running, and normal braking is active.
Flight Phase Inhibition:
Ident.: PRO-ABN-BRAKES-P-00018663.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-BRAKES-P-00011323.0001001 / 11 MAY 12
STATUS
LDG DIST PROC......................................................... APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← N to O
INOP SYS
AUTO BRK
PRO-ABN-BRAKES P 16/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
BRAKES SYS 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-BRAKES-L-00017812.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one BSCU channel is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-BRAKES-L-00011309.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-BRAKES-L-00011310.0001001 / 05 AUG 10
STATUS
INOP SYS
BRK SYS 1(2)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
P
PRO-ABN-BRAKES P 17/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-BRAKES P 18/18
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES-N/WS
FLIGHT CREW
OPERATING MANUAL
BRAKES-N/WS MINOR FAULT
Applicable to: ALL
Ident.: PRO-ABN-NWS-W-00017730.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when a minor fault of the nose wheel steering system is detected.
Flight Phase Inhibition:
Ident.: PRO-ABN-NWS-W-00011326.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-NWS P 1/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
BRAKES-N/WS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-NWS P 2/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
[QRH] CABIN OVERPRESSURE
Ident.: PRO-ABN-CAB_PR-00010761.0001001 / 17 MAR 17
Applicable to: ALL
Apply the following procedure (not displayed on ECAM) in case of total loss of cabin pressure
control leading to overpressure.
PACK 1 OR 2................................................................................................................................OFF
VENTILATION BLOWER........................................................................................................... OVRD
VENTILATION EXTRACT.......................................................................................................... OVRD
Cabin air is extracted overboard
ΔP............................................................................................................... FREQUENTLY MONITOR
If ΔP > 9 PSI:
LAND ASAP
PACK 1................................................................................................................................... OFF
PACK 2................................................................................................................................... OFF
10 min before landing:
PACK 1................................................................................................................................... OFF
PACK 2................................................................................................................................... OFF
VENTILATION BLOWER..................................................................................................... AUTO
VENTILATION EXTRACT....................................................................................................AUTO
Before door opening: CHECK ΔP ZERO
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-CAB_PR P 1/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR EXCESS CAB ALT
Applicable to: ALL
Ident.: PRO-ABN-CAB_PR-T-00017316.0005001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ In climb or descent, the cabin altitude is above the higher of:
• 9 550 ft, or
• 1 000 ft above the airfield pressure altitude.
‐ In cruise, the cabin altitude is above 9 550 ft.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-ABN-CAB_PR P 2/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR EXCESS CAB ALT (Cont'd)
Ident.: PRO-ABN-CAB_PR-T-00018066.0004001 / 20 DEC 16
Rely on the CAB PR EXCESS CAB ALT warning even if not confirmed on the CAB PRESS SD
page. The warning can be triggered by a cabin pressure sensor different from the one used to
control the pressure and display the cabin altitude on the SD.
If above FL 100:
CREW OXY MASK.................................................................................................................USE
If below FL 160:
DESCENT................................................................................................................. INITIATE
MAX FL.....................................................................................................................100/MEA
L2
L1
L2
L1
L2
L1
L2
L12
If above FL 160:
SIGNS................................................................................................................................ ON
EMER DESCENT:
DESCENT................................................................................................................. INITIATE
If A/THR is not active:
THR LEVERS............................................................................................................IDLE
If the A/THR is active, check A/THR is at IDLE on the ED.
SPD BRK........................................................................................................................ FULL
Extension of speedbrakes will significantly increase VLS.
In order to avoid autopilot disconnection and automatic retraction of speedbrakes due to
possible activation of angle of attack protection, allow the speed to increase before starting
to use speedbrakes.
SPD....................................................................................................... MAX/APPROPRIATE
Descend at maximum appropriate speed. However, if structural damage is suspected use
the flight controls with care and reduce speed as appropriate. The landing gear may be
extended. In this case, speed must be reduced to VLO/VLE.
ENG MODE SEL...............................................................................................................IGN
ATC.............................................................................................................................NOTIFY
Notify ATC of the nature of the emergency, and state intention. The flight crew can
communicate with the ATC using voice, or CPDLC when the voice contact cannot be
established or has a poor quality.
Squawk 7700 unless otherwise specified by ATC.
Note:
To save oxygen, set the oxygen diluter selector to N position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
←B→
PRO-ABN-CAB_PR P 3/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR EXCESS CAB ALT (Cont'd)
With the oxygen diluter left to 100 %, oxygen quantity may not be sufficient for the
entire descent profile.
Ensure that the flight crew can communicate wearing oxygen masks. Avoid the
continuous use of the interphone position to minimize the interference from the
noise of the oxygen mask.
L1
MAX FL.....................................................................................................................100/MEA
IF CAB ALT > 14 000 FT:
PAX OXY MASKS...........................................................................................................MAN ON
L2
This action confirms that the passenger oxygen masks are released.
Note:
When descent is established and if time permits, check that the OUTFLOW VALVE is
closed on the CAB PRESS SD page. If it is not closed and ΔP is positive, select the
other CPC. If the OUTFLOW VALVE is still not closing set the cabin pressure MODE
SEL pb to MAN and the V/S CTL sw to full down.
Notify the cabin crew when the aircraft reaches a safe flight level, and when cabin
oxygen is no longer necessary.
Ident.: PRO-ABN-CAB_PR-T-00010755.0001001 / 05 AUG 10
STATUS
MAX FL..................................................................... 100/MEA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-ABN-CAB_PR P 4/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR EXCES RESIDUAL PR
Applicable to: ALL
Ident.: PRO-ABN-CAB_PR-AE-00017328.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the differential pressure is still above 2.5 hPa (0.036 PSI) 12 s after the
last engine shutdown.
Flight Phase Inhibition:
Ident.: PRO-ABN-CAB_PR-AE-00018790.0002001 / 21 MAR 16
PACK 1..........................................................................................................................................OFF
PACK 2..........................................................................................................................................OFF
CABIN CREW........................................................................................................................... ALERT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-CAB_PR P 5/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR LDG ELEV FAULT
Applicable to: ALL
Ident.: PRO-ABN-CAB_PR-AF-00017325.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the LDG ELEV selector is set to AUTO and the landing field elevation
of the FMGS is not available.
Flight Phase Inhibition:
Ident.: PRO-ABN-CAB_PR-AF-00018936.0002001 / 21 MAR 16
L2
LDG ELEV.............................................................................................................................. ADJUST
The flight crew must select the landing field elevation manually with the LDG ELEV selector. Refer
to the LDG ELEV indication on the CRUISE page on the CAB PRESS SD page to adjust the
required landing field elevation.
Note:
If the landing is performed on QFE, set 0 ft on LDG ELEV selector.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PRO-ABN-CAB_PR P 6/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR LO DIFF PR
Applicable to: ALL
Ident.: PRO-ABN-CAB_PR-AG-00017320.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The time to reach ΔP = 0 is less than 1.5 min, and
‐ The time to reach ΔP = 0 is less than the time for CAB ALT to reach landing field elevation
+30 s, and
‐ The aircraft is at least 3 000 ft above the landing field elevation.
Note:
The alert remains, when the aircraft descends within 3 000 ft of the landing field
elevation.
Flight Phase Inhibition:
Ident.: PRO-ABN-CAB_PR-AG-00010762.0002001 / 05 AUG 10
EXPECT HI CAB RATE
A/C V/S..................................................................................................................................REDUCE
L2 This line is not displayed in case of Emergency Descent due to Excessive Cabin Altitude.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-CAB_PR P 7/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR OFV NOT OPEN
Applicable to: ALL
Ident.: PRO-ABN-CAB_PR-AH-00017323.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers, on ground, when the outflow valve is not fully open (time delay 70 s).
Flight Phase Inhibition:
Ident.: PRO-ABN-CAB_PR-AH-00018802.0001001 / 21 MAR 16
MODE SEL................................................................................................................................... MAN
MAN V/S CTL........................................................................................................................FULL UP
L2 It may take 10 s in manual mode before the crew notices a change of the outflow valve position.
L1
IF UNSUCCESSFUL :
PACK 1................................................................................................................................... OFF
PACK 2................................................................................................................................... OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-ABN-CAB_PR P 8/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR SAFETY VALVE OPEN
Applicable to: ALL
Ident.: PRO-ABN-CAB_PR-W-00017324.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers:
‐ On ground, if the safety valve is not fully closed, or
‐ In flight, if the safety valve is not fully closed for more than 1 min.
Flight Phase Inhibition:
Ident.: PRO-ABN-CAB_PR-W-00018092.0002001 / 21 MAR 16
IF DIFF PR ABV 8 PSI:
MODE SEL.............................................................................................................................MAN
MAN V/S CTL................................................................................................................AS RQRD
L2
If overpressure is confirmed, reduce cabin ΔP.
It may take 10 s in manual mode before the flight crew notices a change of the outflow valve
position.
L1
IF UNSUCCESSFUL:
A/C FL...................................................................................................................... REDUCE
IF DIFF PR BELOW 0 PSI:
EXPECT HI CAB RATE
A/C V/S........................................................................................................................... REDUCE
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G→
PRO-ABN-CAB_PR P 9/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR SAFETY VALVE OPEN (Cont'd)
Ident.: PRO-ABN-CAB_PR-W-00018093.0003001 / 21 MAR 16
STATUS
MAN CAB PR CTL
TGT V/S: CLIMB 500 FT/MIN
TGT V/S: DESC 300 FT/MIN
A/C FL
390
350
300
250
< 200
CAB ALT TGT
8 000
7 000
5 500
3 000
0
DURING FINAL APPR :
MAN V/S CTL.....................................................FULL UP
CAUTION
Check that ΔP is zero before opening the
doors.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-ABN-CAB_PR P 10/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR SYS 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-CAB_PR-U-00017326.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the cabin pressure controller is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-CAB_PR-U-00010756.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-CAB_PR-U-00010758.0001001 / 05 AUG 10
STATUS
INOP SYS
CAB PR 1 (2)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
PRO-ABN-CAB_PR P 11/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR SYS 1+2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-CAB_PR-V-00017319.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both cabin pressure controllers are failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-CAB_PR-V-00010759.0001001 / 05 AUG 10
L2
Due to the slow closure of the outflow valve in manual pressurization mode and depending on the
failure, the following procedure may not avoid the depressurization.
L1
MODE SEL................................................................................................................................... MAN
MAN V/S CTL...................................................................................................................... AS RQRD
L2
‐ It may take 10 s in manual mode before the crew notices a change of the outflow valve position.
Use the cabin V/S indication to confirm the outflow valve operation.
‐ Monitor cabin V/S and CAB ALT frequently and adjust as necessary.
Maintain aircraft altitude at or above cabin altitude.
‐ The two safety valves limit ΔP to 8.6 PSI.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I→
PRO-ABN-CAB_PR P 12/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
CAB PR SYS 1+2 FAULT (Cont'd)
Ident.: PRO-ABN-CAB_PR-V-00018107.0003001 / 21 MAR 16
L12
STATUS
INOP SYS
MAN CAB PR CTL
TGT V/S : CLIMB 500 FT/MIN
TGT V/S : DESC 300 FT/MIN
A/C FL
390
350
300
250
< 200
CAB PR 1+2
CAB ALT TGT
8 000
7 000
5 500
3 000
0
DURING FINAL APPR :
V/S CTL.............................................................. FULL UP
When on intermediate approach (below airfield pressure
altitude +2 500 ft), adjust ΔP = 0.
CAUTION
Check that ΔP is zero before opening the
doors.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I
PRO-ABN-CAB_PR P 13/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CAB PR
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-CAB_PR P 14/14
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
C/B
FLIGHT CREW
OPERATING MANUAL
C/B TRIPPED
Applicable to: ALL
Ident.: PRO-ABN-C_B-Y-00017390.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one C/B is tripped in the designated zone.
Flight Phase Inhibition:
Ident.: PRO-ABN-C_B-Y-00012551.0001001 / 25 FEB 14
Crew awareness.
If one green circuit breaker (C/B) is tripped, one of the following messages appears after
one minute, depending on the location of the affected C/B:
C/B TRIPPED ON OVHD PNL
C/B TRIPPED ON L(R) ELEC BAY
C/B TRIPPED REAR PNL J-M OR N-R OR S-V OR W-Z
L2
Note:
In flight, do not reengage a C/B that has tripped by itself, unless the Captain judges
it necessary to do so for the safe continuation of the flight. This procedure should be
adopted only as a last resort, and only one reengagement should be attempted.
On ground, do not reengage the C/B of the fuel pump(s) of any tank. For all other
C/B s, if the flight crew coordinates the action with maintenance, the flight crew may
reengage a tripped C/B , provided that the cause of the tripped C/B is identified.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-C_B P 1/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
C/B
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-C_B P 2/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COM
FLIGHT CREW
OPERATING MANUAL
COM ACARS FAULT
Applicable to: ALL
Ident.: PRO-ABN-COM-B-00016895.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a failure of ACARS.
Flight Phase Inhibition:
Ident.: PRO-ABN-COM-B-00017538.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-COM-B-00010037.0001001 / 05 AUG 10
STATUS
INOP SYS
ACARS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-COM P 1/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COM
FLIGHT CREW
OPERATING MANUAL
COM CIDS 1 + 2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-COM-A-00016887.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a total loss of CIDS.
Flight Phase Inhibition:
Ident.: PRO-ABN-COM-A-00010033.0001001 / 25 FEB 14
L2
Passenger address, cabin and service interphone, and passenger signs are inoperative.
L1
Crew awareness.
Ident.: PRO-ABN-COM-A-00010034.0001001 / 05 AUG 10
STATUS
INOP SYS
CIDS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PRO-ABN-COM P 2/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COM
FLIGHT CREW
OPERATING MANUAL
COM HF 1(2) DATA FAULT
Applicable to: ALL
Ident.: PRO-ABN-COM-F-00016896.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when data communications via HF 1(2) are inoperative.
Flight Phase Inhibition:
Ident.: PRO-ABN-COM-F-00017499.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-COM-F-00010045.0001001 / 17 MAR 11
STATUS
INOP SYS
HF 1(2) DATA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-COM P 3/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COM
FLIGHT CREW
OPERATING MANUAL
COM SATCOM DATA FAULT
Applicable to: ALL
Ident.: PRO-ABN-COM-D-00016899.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the ACARS transmissions via SATCOM are lost.
Flight Phase Inhibition:
Ident.: PRO-ABN-COM-D-00017548.0001001 / 21 MAR 16
L2
Telephone transmissions are still available. ACARS communications are inoperative.
L1
Crew awareness.
Ident.: PRO-ABN-COM-D-00010041.0001001 / 21 MAR 16
STATUS
INOP SYS
SATCOM DATA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PRO-ABN-COM P 4/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COM
FLIGHT CREW
OPERATING MANUAL
COM SATCOM FAULT
Applicable to: ALL
Ident.: PRO-ABN-COM-C-00016894.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the telephone and the ACARS transmission are lost.
Flight Phase Inhibition:
Ident.: PRO-ABN-COM-C-00017500.0001001 / 21 MAR 16
L2
ACARS and telephone communications are inoperative.
L1
Crew awareness.
Ident.: PRO-ABN-COM-C-00017502.0001001 / 21 MAR 16
STATUS
INOP SYS
SATCOM
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-COM P 5/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COM
FLIGHT CREW
OPERATING MANUAL
COM SINGLE PTT STUCK
Applicable to: ALL
Ident.: PRO-ABN-COM-G-00016902.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when any PTT transmission selector is jammed in the transmit position for
more than 40 s (VHF ) or for more than 180 s (HF).
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PRO-ABN-COM P 6/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COM
FLIGHT CREW
OPERATING MANUAL
COM SINGLE PTT STUCK (Cont'd)
Ident.: PRO-ABN-COM-G-00017503.0001001 / 21 MAR 16
ACP1 VHF 1(2)(3) TX....................................................................................................... DESELECT
ACP1 HF 1(2) TX.............................................................................................................. DESELECT
IF UNSUCCESSFUL:
ACP2 VHF 1(2)(3) TX.................................................................................................DESELECT
ACP2 HF 1(2) TX....................................................................................................... DESELECT
IF UNSUCCESSFUL:
ACP3 VHF 1(2)(3) TX.................................................................................................DESELECT
ACP3 HF 1(2) TX....................................................................................................... DESELECT
When the ACP linked to the faulty PTT is detected, the previous ECAM actions are replaced by the
following ones:
AUDIO SWTG................................................................................................................DO NOT USE
ON AFFECTED ACP:
ALL TX KEYS......................................................................................................... DO NOT USE
ON ALL OTHER ACP:
VHF 1(2)(3) TX........................................................................................................... RESELECT
HF 1(2) TX.................................................................................................................. RESELECT
Ident.: PRO-ABN-COM-G-00014765.0001001 / 26 NOV 12
STATUS
AUDIO SWTG................................................... DO NOT USE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
INOP SYS
SINGLE PTT
PRO-ABN-COM P 7/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COM
FLIGHT CREW
OPERATING MANUAL
COM VHF 1(2)(3) /HF 1(2) EMITTING
Applicable to: ALL
Ident.: PRO-ABN-COM-I-00016892.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
For VHF 1(2)(3) EMITTING, the alert triggers when the transmitter emits more than 30 s or 60 s
depending on aircraft configuration.
For HF 1(2) EMITTING, the alert triggers when the transmitter emits more than 60 s.
Flight Phase Inhibition:
Ident.: PRO-ABN-COM-I-00017549.0001001 / 21 MAR 16
L2
1. If any Push To Talk (PTT) transmission selector (sidestick PTT , hand mike PTT , or
ACP PTT switch ) is jammed in the transmit position, try to release it in order to remove the
caution.
2. If unsuccessful, deselect the identified failed VHF /HF transmission keys on the associated Audio
Control Panel (ACP ) to remove the caution. This ACP should only be used in reception mode.
The associated PTT transmission selectors must not be used.
Note:
In this case, the ACP of the unaffected side may be used to recover the deselected
VHF /HF channel.
3. If no transmission key on the ACP is found in the “transmit” position, pull the affected VHF /HF
C/B associated to the ECAM message : COM\HF1 C/B HA 14 on 49 VU , COM NAV\HF2 C/B
L13 on 121 VU , COM\VHF\1 C/B G09 on 49 VU , COM NAV\VHF\2 C/B L04 on 121 VU , COM
\VHF\3 C/B L05 on 121 VU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
PRO-ABN-COM P 8/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COM
FLIGHT CREW
OPERATING MANUAL
COM VHF 3 DATA FAULT
Applicable to: ALL
Ident.: PRO-ABN-COM-E-00016897.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when data communication via VHF 3 are inoperative.
Flight Phase Inhibition:
Ident.: PRO-ABN-COM-E-00017550.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-COM-E-00010043.0001001 / 17 MAR 11
STATUS
INOP SYS
VHF 3 DATA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
PRO-ABN-COM P 9/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COM
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-COM P 10/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COND
FLIGHT CREW
OPERATING MANUAL
COND FWD CAB/AFT CAB/CKPT DUCT OVHT
Applicable to: ALL
Ident.: PRO-ABN-COND-F-00017295.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The duct temperature rises above 88 °C, or
‐ The duct temperature rises above 80 °C four times during the same flight.
Flight Phase Inhibition:
Ident.: PRO-ABN-COND-F-00010720.0001001 / 05 AUG 10
WHEN DUCT TEMP < 70 DEG C:
HOT AIR................................................................................................................OFF THEN ON
L2
Hot air pressure regulating valve reopens.
Ident.: PRO-ABN-COND-F-00018037.0001001 / 21 MAR 16
L12
STATUS
INOP SYS
If system not recovered:
CAB TEMP BY PACK ONLY
Basic temperature regulation is by packs only (remains
automatic).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
HOT AIR
FWD CRG HEAT
PRO-ABN-COND P 1/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COND
FLIGHT CREW
OPERATING MANUAL
COND FWD(AFT) CARGO DUCT OVHT
Applicable to: ALL
Ident.: PRO-ABN-COND-G-00017339.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the duct temperature in the forward(aft) cargo compartment rises
above 88 °C.
Flight Phase Inhibition:
Ident.: PRO-ABN-COND-G-00018038.0001001 / 21 MAR 16
WHEN DUCT TEMP < 70 DEG C:
HOT AIR................................................................................................................OFF THEN ON
L2
Hot air pressure regulating valve reopens.
Ident.: PRO-ABN-COND-G-00018039.0001001 / 21 MAR 16
L12
STATUS
INOP SYS
If system not recovered:
CAB TEMP BY PACK ONLY
Basic temperature regulation is by packs only (remains
automatic).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
FWD(AFT) CRG HEAT
PRO-ABN-COND P 2/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COND
FLIGHT CREW
OPERATING MANUAL
COND FWD(AFT) CRG HEAT FAULT
Applicable to: ALL
Ident.: PRO-ABN-COND-N-00017341.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers if the heating controller of the forward(aft) cargo compartment is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-COND-N-00018040.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-COND-N-00018041.0001001 / 21 MAR 16
STATUS
INOP SYS
FWD(AFT) CRG HEAT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-COND P 3/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COND
FLIGHT CREW
OPERATING MANUAL
COND FWD(AFT) CRG ISOL VALVE
Applicable to: ALL
Ident.: PRO-ABN-COND-M-00017335.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers if the forward(aft) cargo isolation valve disagrees with the selected position.
Flight Phase Inhibition:
Ident.: PRO-ABN-COND-M-00018042.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-COND-M-00018043.0001001 / 21 MAR 16
STATUS
INOP SYS
FWD(AFT) CRG HEAT
FWD(AFT) CRG VENT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PRO-ABN-COND P 4/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COND
FLIGHT CREW
OPERATING MANUAL
COND HOT AIR FAULT
Applicable to: ALL
Ident.: PRO-ABN-COND-I-00017296.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the position of the hot air pressure regulating valve disagrees with the
commanded position.
Flight Phase Inhibition:
Ident.: PRO-ABN-COND-I-00018940.0001001 / 21 MAR 16
HOT AIR (IF NOT CLOSED)........................................................................................................ OFF
IF HOT AIR STILL OPEN and DUCT OVHT persists:
PACK 1................................................................................................................................... OFF
PACK 2................................................................................................................................... OFF
DESCENT TO FL 100/MEA
L2
Descend to FL 100, or MEA, whichever is higher.
L1
WHEN DIFF PR < 1 PSI AND FL BELOW 100:
RAM AIR...................................................................................................................................ON
MAX FL........................................................................................................................... 100/MEA
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
PRO-ABN-COND P 5/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COND
FLIGHT CREW
OPERATING MANUAL
COND HOT AIR FAULT (Cont'd)
Ident.: PRO-ABN-COND-I-00018044.0001001 / 21 MAR 16
L12
STATUS
INOP SYS
If HOT AIR closed only:
CAB TEMP BY PACK ONLY
Basic temperature regulation by packs only (remains
automatic).
PACK 1+2 (If PACKS OFF)
HOT AIR
FWD CRG HEAT
COND L+R CAB FAN FAULT
Applicable to: ALL
Ident.: PRO-ABN-COND-R-00017297.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers if both recirculation fans are failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-COND-R-00018045.0001001 / 22 MAR 17
PACK FLOW..................................................................................................................................... HI
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F →
PRO-ABN-COND P 6/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COND
FLIGHT CREW
OPERATING MANUAL
COND L+R CAB FAN FAULT (Cont'd)
Ident.: PRO-ABN-COND-R-00018046.0001001 / 21 MAR 16
STATUS
INOP SYS
L+R CAB FAN
COND LAV + GALLEY FAN FAULT
Applicable to: ALL
Ident.: PRO-ABN-COND-S-00017300.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers if the extraction fan of the lavatory and galley is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-COND-S-00010751.0002001 / 25 FEB 14
L2
Cabin zone temperature sensors are normally ventilated by the air extracted by the fan.
Therefore, cabin zone temperature regulation is lost.
L1
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G →
PRO-ABN-COND P 7/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COND
FLIGHT CREW
OPERATING MANUAL
COND LAV + GALLEY FAN FAULT (Cont'd)
Ident.: PRO-ABN-COND-S-00010752.0011001 / 05 AUG 10
L12
STATUS
INOP SYS
If ACSC 2 is operative:
CAB TEMP CKPT CTL ONLY
GALLEY FAN
‐ To adjust the cabin zone temperature, use the FWD
CABIN and AFT CABIN zone temperature selectors
(overhead panel). The selectors control the cabin duct
temperature directly.
‐ Cockpit temperature regulation is normal.
COND CTL 2
PACK 2
(1)
(1)
If ACSC 2 is inoperative:
CAB AT FIXED TEMP
‐ FWD CABIN and AFT CABIN zone temperature selectors
are inoperative.
‐ To adjust the cabin zone temperature, use the COCKPIT
zone temperature selector (overhead panel). Cabin duct
temperature is the same as cockpit duct temperature.
‐ Cockpit temperature regulation is normal.
(1)
(If ACSC 2 is inoperative)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-ABN-COND P 8/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COND
FLIGHT CREW
OPERATING MANUAL
COND TRIM AIR SYS FAULT
Applicable to: ALL
Ident.: PRO-ABN-COND-AI-00017305.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ One trim air valve is failed, or
‐ There is an overpressure downstream of the hot air valve.
Flight Phase Inhibition:
Ident.: PRO-ABN-COND-AI-00010730.0001001 / 05 AUG 10
One trim valve failed:
A message corresponding to the affected valve is displayed:
AFT CAB TRIM VALVE
FWD CAB TRIM VALVE
CKPT TRIM VALVE
High pressure detected downstream of the hot air pressure regulating valve:
TRIM AIR HI PR
L2
Note:
If the warning and the TRIM AIR HI PR message are triggered when all trim air valves
are closed (during the first 30 s after the packs are selected on, or in flight, if all zone
heating demands are fulfilled), disregard them.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
PRO-ABN-COND P 9/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
COND
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-COND P 10/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CONFIG
FLIGHT CREW
OPERATING MANUAL
CONFIG L(R) SIDESTICK FAULT
(BY TAKE OVER)
Applicable to: ALL
Ident.: PRO-ABN-CONFIG-AA-00018894.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the L or R sidestick is inoperative (takeover pb pressed more than
30 s) and when thrust levers are set at TO , or Flex TO, or when pressing T.O CONFIG pb.
Flight Phase Inhibition:
Ident.: PRO-ABN-CONFIG-AA-00018411.0001001 / 21 MAR 16
L2
L(R) TAKEOVER ................................................................................................................DEPRESS
The affected stick becomes operative.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-CONFIG P 1/6
12 APR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CONFIG
FLIGHT CREW
OPERATING MANUAL
CONFIG PARK BRK ON
Applicable to: ALL
Ident.: PRO-ABN-CONFIG-Z-00017858.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the parking brake is on and thrust levers are set at TO or FLXTO power
position.
Flight Phase Inhibition:
Ident.: PRO-ABN-CONFIG-Z-00011302.0001001 / 05 AUG 10
L2
Check that the parking brake handle is in the OFF position. If warning stays on, check that the
brake pressure is at zero on the BRAKES PRESSURE indicator.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PRO-ABN-CONFIG P 2/6
12 APR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CONFIG
FLIGHT CREW
OPERATING MANUAL
CONFIG PITCH TRIM NOT IN T.O RANGE
Applicable to: ALL
Ident.: PRO-ABN-CONFIG-AB-00018895.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
If the PITCH TRIM is not in TO configuration, this alert triggers:
- when thrust levers are set at TO , or Flex TO, or
- when pressing T.O CONFIG pb.
Flight Phase Inhibition:
Ident.: PRO-ABN-CONFIG-AB-00011773.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-CONFIG P 3/6
12 APR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CONFIG
FLIGHT CREW
OPERATING MANUAL
CONFIG RUD TRIM NOT IN T.O RANGE
Applicable to: ALL
Ident.: PRO-ABN-CONFIG-AC-00018896.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
If the RUD TRIM is not in TO configuration, this alert triggers:
- when thrust levers are set at TO , or Flex TO, or
- when pressing T.O CONFIG pb.
Flight Phase Inhibition:
Ident.: PRO-ABN-CONFIG-AC-00011776.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PRO-ABN-CONFIG P 4/6
12 APR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CONFIG
FLIGHT CREW
OPERATING MANUAL
CONFIG SLATS (FLAPS) NOT IN T.O CONFIG
Applicable to: ALL
Ident.: PRO-ABN-CONFIG-AD-00018897.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
If the slats or flaps are not in TO configuration, this alert triggers:
- when thrust levers are set at TO , or Flex TO, or
- when pressing T.O CONFIG pb.
Flight Phase Inhibition:
Ident.: PRO-ABN-CONFIG-AD-00011758.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-CONFIG P 5/6
12 APR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
CONFIG
FLIGHT CREW
OPERATING MANUAL
CONFIG SPD BRK NOT RETRACTED
Applicable to: ALL
Ident.: PRO-ABN-CONFIG-AE-00018898.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
If the speed brakes are not retracted, this alert triggers:
- when thrust levers are set at TO , or Flex TO, or
- when pressing T.O CONFIG pb.
Flight Phase Inhibition:
Ident.: PRO-ABN-CONFIG-AE-00011766.0001001 / 09 FEB 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-ABN-CONFIG P 6/6
12 APR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DATALINK
FLIGHT CREW
OPERATING MANUAL
DATALINK ATSU FAULT
Applicable to: ALL
Ident.: PRO-ABN-DATALINK-A-00017150.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a failure in ATSU initialization associated with ATSU INIT
FAULT ECAM message.
Flight Phase Inhibition:
Ident.: PRO-ABN-DATALINK-A-00018462.0001001 / 21 MAR 17
Crew awareness.
ATSU INIT FAULT
L2 Displayed, in case of failure upon ATSU initialization. Refer to DSC-46-10-50 How to Initialize.
Ident.: PRO-ABN-DATALINK-A-00018463.0001001 / 21 MAR 16
STATUS
INOP SYS
ATSU
DATA COMPANY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-DATALINK P 1/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DATALINK
FLIGHT CREW
OPERATING MANUAL
DATALINK COMPANY FAULT
Applicable to: ALL
Ident.: PRO-ABN-DATALINK-C-00017151.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a failure in the AOC datalink communications.
Flight Phase Inhibition:
Ident.: PRO-ABN-DATALINK-C-00018458.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-DATALINK-C-00018459.0001001 / 21 MAR 16
STATUS
INOP SYS
DATA COMPANY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PRO-ABN-DATALINK P 2/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DOOR
FLIGHT CREW
OPERATING MANUAL
[QRH] COCKPIT DOOR FAULT
Ident.: PRO-ABN-DOOR-00009968.0003001 / 17 MAR 17
Applicable to: ALL
CKPT DOOR CONT [OVHD PANEL] .................................................................................... CHECK
If one or more STRIKE status light on:
COCKPIT DOOR................................................................................................................. OPEN
COCKPIT DOOR sw ...................................................................... UNLOCK 10 s THEN NORM
If two or more STRIKE status lights on:
COCKPIT DOOR NOT INTRUSION PROOF.
If two CHAN status lights on:
Automatic latch release is not available, in case of cockpit decompression.
If no status light on:
TO UNLOCK THE DOOR: COCKPIT DOOR HANDLE AVAIL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-DOOR P 1/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DOOR
FLIGHT CREW
OPERATING MANUAL
DOOR L(R)(FWD)(AFT) AVIONICS
(IN FLIGHT)
Applicable to: ALL
Ident.: PRO-ABN-DOOR-A-00016888.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the L(R)(FWD)(AFT) avionics door is not detected closed by the
proximity sensors.
Flight Phase Inhibition:
Ident.: PRO-ABN-DOOR-A-00018945.0001001 / 21 MAR 16
L2
No crew action required as long as cabin pressure is normal.
L1
IF ABN CAB V/S:
MAX FL........................................................................................................................... 100/MEA
L2
Limit maximum flight level to FL 100, or MEA, or minimum obstacle clearance altitude.
Avionics doors are of plug type. Therefore full depressurization is not recommended.
Ident.: PRO-ABN-DOOR-A-00018944.0002001 / 21 MAR 16
STATUS
IF ABN CAB V/S:
MAX FL.............................................................. 100/MEA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PRO-ABN-DOOR P 2/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DOOR
FLIGHT CREW
OPERATING MANUAL
DOOR L(R)(FWD)(AFT) AVIONICS
(ON GROUND)
Applicable to: ALL
Ident.: PRO-ABN-DOOR-C-00019100.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the L(R)(FWD)(AFT) avionics door is not detected closed by the
proximity sensors.
Flight Phase Inhibition:
Ident.: PRO-ABN-DOOR-C-00019096.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-DOOR P 3/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DOOR
FLIGHT CREW
OPERATING MANUAL
DOOR L(R) FWD(AFT) CABIN
(IN FLIGHT)
Applicable to: ALL
Ident.: PRO-ABN-DOOR-D-00019103.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the L(R) FWD(AFT) cabin door is not detected closed by the proximity
sensors.
Flight Phase Inhibition:
Ident.: PRO-ABN-DOOR-D-00019101.0001001 / 21 MAR 16
No crew action required as long as cabin pressure is normal.
IF ABN CAB V/S:
MAX FL........................................................................................................................... 100/MEA
L2
Limit maximum flight level to FL 100, or MEA, or minimum obstacle clearance altitude.
If door warning is accompanied by abnormal increase of cabin altitude, flight crew must reduce
cabin ΔP and altitude by descending.
Ident.: PRO-ABN-DOOR-D-00019104.0002001 / 21 MAR 16
STATUS
IF ABN CAB V/S:
MAX FL.............................................................. 100/MEA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PRO-ABN-DOOR P 4/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DOOR
FLIGHT CREW
OPERATING MANUAL
DOOR L(R) FWD(AFT) CABIN
(ON GROUND)
Applicable to: ALL
Ident.: PRO-ABN-DOOR-E-00019106.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the L(R) FWD(AFT) cabin door is not detected closed by the proximity
sensors.
Flight Phase Inhibition:
Ident.: PRO-ABN-DOOR-E-00019102.0001001 / 21 MAR 16
L2
The crew may confirm a cabin door warning by checking the visual indicator on the door.
L1
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-DOOR P 5/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DOOR
FLIGHT CREW
OPERATING MANUAL
DOOR L(R) FWD(AFT) EMER EXIT
(IN FLIGHT)
Applicable to: ALL
Ident.: PRO-ABN-DOOR-F-00019121.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the L(R) FWD(AFT) emergency exit door is not detected closed by the
proximity sensors.
Flight Phase Inhibition:
Ident.: PRO-ABN-DOOR-F-00019120.0001001 / 21 MAR 16
No crew action required as long as cabin pressure is normal.
IF ABN CAB V/S:
MAX FL........................................................................................................................... 100/MEA
L2
Limit maximum flight level to FL 100, or MEA, or minimum obstacle clearance altitude.
If door warning is accompanied by abnormal increase of cabin altitude, flight crew must reduce
cabin ΔP and altitude by descending.
Ident.: PRO-ABN-DOOR-F-00019122.0004001 / 21 MAR 16
STATUS
IF ABN CAB V/S:
MAX FL.............................................................. 100/MEA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-ABN-DOOR P 6/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DOOR
FLIGHT CREW
OPERATING MANUAL
DOOR L(R) FWD(AFT) EMER EXIT
(ON GROUND)
Applicable to: ALL
Ident.: PRO-ABN-DOOR-G-00019125.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the L(R) FWD(AFT) emergency exit door is not detected closed by the
proximity sensors.
Flight Phase Inhibition:
Ident.: PRO-ABN-DOOR-G-00019124.0001001 / 21 MAR 16
L2
The crew may confirm an emergency exit door warning by checking the visual indicator on the door.
L1
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
PRO-ABN-DOOR P 7/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DOOR
FLIGHT CREW
OPERATING MANUAL
DOOR FWD(AFT)(BULK) CARGO
(IN FLIGHT)
Applicable to: ALL
Ident.: PRO-ABN-DOOR-B-00016890.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the FWD(AFT)(BULK) cargo door is not detected closed by the
proximity sensors.
Flight Phase Inhibition:
Ident.: PRO-ABN-DOOR-B-00019126.0001001 / 21 MAR 16
No crew action required as long as cabin pressure is normal.
IF ABN CAB V/S:
MAX FL........................................................................................................................... 100/MEA
L2
Limit maximum flight level to FL 100, or MEA, or minimum obstacle clearance altitude.
If door warning is accompanied by abnormal increase of cabin altitude, flight crew must reduce
cabin ΔP and altitude by descending.
Ident.: PRO-ABN-DOOR-B-00018946.0002001 / 21 MAR 16
STATUS
IF ABN CAB V/S:
MAX FL............................................................... 100/MEA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
PRO-ABN-DOOR P 8/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DOOR
FLIGHT CREW
OPERATING MANUAL
DOOR FWD(AFT)(BULK) CARGO
(ON GROUND)
Applicable to: ALL
Ident.: PRO-ABN-DOOR-H-00019129.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the FWD(AFT)(BULK) cargo door is not detected closed by the
proximity sensors.
Flight Phase Inhibition:
Ident.: PRO-ABN-DOOR-H-00018947.0002001 / 21 MAR 16
L2
L1
The crew may confirm a cargo door warning by checking the indication on the cargo door.
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I
PRO-ABN-DOOR P 9/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DOOR
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-DOOR P 10/10
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
EIS
FLIGHT CREW
OPERATING MANUAL
[QRH] DISPLAY UNIT FAILURE
Ident.: PRO-ABN-EIS-00021170.0002001 / 17 MAR 17
Applicable to: ALL
If DU flashes:
This phenomenon may be due to Intermittent Electrical Power Supply Interruptions. It is
evidenced by one, or a combination, of the following :
‐ Flashing of PFD , ND , ECAM DUs (blank screen or INVALID DATA message),
‐ Flashing of MCDU,
‐ Intermittent flight control law reversion.
If captain PFD, ND, ECAM DUs or MCDU 1 affected:
GEN 1...............................................................................................................................OFF
If DUs flash continues :
GEN 1..........................................................................................................................ON
If DUs flash stops :
KEEP GEN 1 OFF
Keep the generator OFF for the rest of the flight.
RUD TRIM............................................................................................... CHECK/RESET
Use the slide slip indication to reset the rudder trim if necessary. Intermittent Electrical
Power Supply Interruptions may cause offset in the rudder trim.
APU START................................................................................................... CONSIDER
If first officer PFD, ND, lower ECAM or MCDU 2 affected:
GEN 2...............................................................................................................................OFF
If DUs flash continues:
GEN 2..........................................................................................................................ON
If DUs flash stops:
KEEP GEN 2 OFF
Keep the generator OFF for the rest of the flight.
RUD TRIM............................................................................................... CHECK/RESET
Use the slide slip indication to reset the rudder trim if necessary. Intermittent Electrical
Power Supply Interruptions may cause offset in the rudder trim.
APU START................................................................................................... CONSIDER
If DU blank (with or without large amber “F”), or distorted:
DU brightness knob (affected DU)................................................................................ AS RQRD
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-ABN-EIS P 1/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
EIS
FLIGHT CREW
OPERATING MANUAL
[QRH] DISPLAY UNIT FAILURE (Cont'd)
The DU can be switched off.
CONSIDER ECAM/ND XFR
CONSIDER PFD/ND XFR
If INVALID DISPLAY UNIT message displayed:
This may be caused by a DU failure.
WAIT AT LEAST 40 s FOR AUTOMATIC DU RECOVERY
If DU not recovered:
DU brightness knob................................................................................................ AS RQRD
The DU can be switched off.
If INVALID DATA message displayed (not on all DUs):
CONSIDER EIS DMC SWITCHING
If unsuccessful:
DU brightness knob (affected DU)................................................................. OFF THEN ON
Note:
The ND display may disappear if too many waypoints and associated information
are displayed. Reduce ND range, or deselect WPT or CSTR , and the ND display
may automatically recover, after about 30 s.
If INVALID DATA message displayed on all DUs:
AP, A/THR AND MCDU NAVIGATION DATA AVAILABLE
WAIT AT LEAST 40 s FOR AUTOMATIC DU RECOVERY
If one or more DUs not recovered:
DUs brightness knob (all affected DUs).......................................................................... OFF
WAIT AT LEAST 40 s
DUs brightness knob (one by one)....................................................................................ON
If INVALID DATA message displayed on all DUs, when switching a given DU back
ON:
FAULTY DU brightness knob........................................................ OFF AND KEEP OFF
REPEAT PROCEDURE
Repeat the procedure starting at: If INVALID DATA message displayed on all DUs.
If inversion of E/WD and SD:
ECAM UPPER DISPLAY brightness knob............................................................OFF THEN ON
The same action on the EIS DMC SWITCHING selector produces the same effect.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-ABN-EIS P 2/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
EIS
FLIGHT CREW
OPERATING MANUAL
EIS DMC 1(2)(3) FAULT
Applicable to: ALL
Ident.: PRO-ABN-EIS-F-00017307.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when DMC 1, or DMC 2, or DMC 3 is failed.
Flight Phase Inhibition:
L1
Note:
(a) Inhibited only during first 15 s of Flight Phase 5.
Ident.: PRO-ABN-EIS-F-00010057.0002001 / 10 AUG 10
DMC 1
EIS DMC SWITCH .......................................................................................................... CAPT 3
L2
DMC 3 replaces DMC 1.
L1
DMC 2
EIS DMC SWITCH............................................................................................................... F/O 3
L2
DMC 3 replaces DMC 2.
L1
DMC 3
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-ABN-EIS P 3/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
EIS
FLIGHT CREW
OPERATING MANUAL
EIS DMC 1(2)(3) FAULT (Cont'd)
Ident.: PRO-ABN-EIS-F-00010058.0001001 / 10 AUG 10
STATUS
INOP SYS
DMC 1(2)(3)
EIS DMC/FWC COM FAULT
Applicable to: ALL
Ident.: PRO-ABN-EIS-I-00017317.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when at least one of the FWC detects the loss of both DMC 1/3 and DMC2/3
busses.
Flight Phase Inhibition:
Ident.: PRO-ABN-EIS-I-00014308.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C
PRO-ABN-EIS P 4/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
[QRH] C/B TRIPPED
Ident.: PRO-ABN-ELEC-00012643.0001001 / 17 MAR 17
Applicable to: ALL
On ground:
Do not reengage the circuit breaker (C/B ) of the fuel pump(s) of any tank. For all other C/B , if
the flight crew coordinates the action with maintenance, the flight crew may reengage a tripped
C/B, provided that the cause is identified.
In flight:
Do not reengage a circuit breaker (C/B), unless the captain judges it necessary to do so for the
safe continuation of the flight. Only one reengagement should be attempted.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-ELEC P 1/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
[QRH] ELEC EMER CONFIG SYS REMAINING
Applicable to: ALL
ELEC EMER CONFIG SYS REMAINING
EMER GEN RUNNING
Ident.: PRO-ABN-ELEC-S-00018562.0004001 / 17 MAR 17
AIR COND
PRESS
PRESS AUTO SYS 1
MAN PRESS CTL
RAM AIR
PACK VALVE 1
PACK VALVE 2
AVIONIC VENT
FWD CRG ISOL VALVES
Ident.: PRO-ABN-ELEC-S-00012522.0001001 / 17 MAR 17
FMGS
FMGC (NAV FUNCTION)
MCDU
FAC
FCU
Ident.: PRO-ABN-ELEC-S-00018533.0002001 / 17 MAR 17
COM
VHF 1
HF 1
RMP 1
ACP (CAPT , F/O)
CIDS
INTERPHONE
CVR
LOUDSPEAKER 1
Ident.: PRO-ABN-ELEC-S-00012524.0001001 / 17 MAR 17
EMER EQPT
CREW OXY
PAX OXY mask release
(auto + man)
SLIDES ARM/WARN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
BAT ONLY
ON THE GROUND
IN FLIGHT
NORM
INOP
NORM
NORM
Closure Inop
NORM
NORM
NORM
INOP
NORM
Closure Inop
Closure Inop
NORM
INOP
NORM
INOP(a)
NORM
Closure Inop
Closure Inop(a)
Partial
INOP
N°1 only
N°1 only
N°1 only
ch 1 only
Inop
Inop
Inop
ch 1 only
Inop
Inop
Inop
ch 1 only
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
INOP
NORM
NORM
NORM
NORM
INOP
NORM
NORM
INOP
NORM
NORM
NORM
NORM
INOP
NORM
NORM
NORM (b)
NORM (b)
NORM
INOP
INOP
NORM
NORM
B→
NORM
Continued on the following page
PRO-ABN-ELEC P 2/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC EMER CONFIG SYS REMAINING
EMER GEN RUNNING
Ident.: PRO-ABN-ELEC-S-00012525.0002001 / 17 MAR 17
FIRE
ENG 1 LOOP
ENG 2 LOOP
APU LOOP
CARGO SMOKE DET
ENG FIRE EXT.
APU FIRE EXT.
CARGO FIRE EXT.
APU AUTO EXT.
Ident.: PRO-ABN-ELEC-S-00018017.0001001 / 17 MAR 17
FLT CTL
ELAC
SEC
FCDC
SFCC
Flaps pos ind
Ident.: PRO-ABN-ELEC-S-00018018.0001001 / 17 MAR 17
FUEL
LP VALVE
FQI channel 1
X FEED VALVE
INTERTANK TRANSFER
VALVE
Ident.: PRO-ABN-ELEC-S-00012528.0001001 / 17 MAR 17
HYD
FIRE VALVES
Ident.: PRO-ABN-ELEC-S-00018539.0002001 / 17 MAR 17
ICE-RAIN
WING A.ICE
ENG A.ICE VALVE
CAPT PITOT
CAPT AOA
RAIN REPELLENT
(CAPT)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued from the previous page
BAT ONLY
IN FLIGHT
ON THE GROUND
A only
B only
INOP
ch 1 only
Bottle 1 only
Squib A only
INOP
INOP
A only
B only
INOP
INOP
Bottle 1 only
Squib A only
INOP
INOP
A only
B only
INOP(a)
INOP
Bottle 1 only
Squib A only
INOP(a)
INOP(a)
N°1 only
N°1 only
N°1 only
N°1 only
NORM
N°1 + N°2
N°1 only
INOP
N°1 only
NORM
N°1 + N°2 (d)
N°1 only
INOP
N°1 only
NORM (c)
NORM
NORM
NORM
NORM
INOP
INOP
NORM
INOP
INOP
NORM
INOP
INOP
NORM
NORM
NORM
NORM
OPEN
NORM
NORM
INOP
OPEN
NORM
INOP
INOP
OPEN
NORM(c)
INOP
NORM
NORM
NORM
Continued on the following page
←B→
PRO-ABN-ELEC P 3/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC EMER CONFIG SYS REMAINING
EMER GEN RUNNING
Ident.: PRO-ABN-ELEC-S-00018538.0002001 / 17 MAR 17
EIS
FLT INS
PFD 1
ND 1
ECAM upper disp.
DMC 1 or 3
SDAC 1, FWC 1
ECAM CONT. panel
CLOCKS
Ident.: PRO-ABN-ELEC-S-00018537.0002001 / 17 MAR 17
L/G
LGCIU SYS 1
BRK PRESS IND
PARK BRK
ABCU
Ident.: PRO-ABN-ELEC-S-00012532.0001001 / 17 MAR 17
LIGHTS
EMER CKPT
EMER CAB
Ident.: PRO-ABN-ELEC-S-00018550.0005001 / 17 MAR 17
NAV
IR
ADR
ADF
VOR
MMR
DME
DDRMI
ATC
ISIS
Ident.: PRO-ABN-ELEC-S-00018541.0002001 / 17 MAR 17
PNEU
ENG 1 BLEED
ENG 2 BLEED
APU BLEED
X BLEED (MAN CTL)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued from the previous page
BAT ONLY
IN FLIGHT
ON THE GROUND
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
INOP
NORM
NORM
NORM
NORM
NORM
NORM (c)
INOP
NORM (c)
NORM (c)
NORM (c)
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
NORM
N°1 only (e)
N°1 only
N°1 only
N°1 only
N°1 only
N°1 only
NORM
N°1 only
NORM
N°1 only (e)
N°1 only
INOP
N°1 only
N°1 only
INOP
NORM
INOP
NORM
N°1 only (e)
N°1 only
INOP
N°1 only (c)
N°1 only (c)
INOP
NORM (c)
INOP
NORM
NORM
BMC 2 INOP
INOP
NORM
←B→
BMC 1 INOP
BMC 1 INOP
BMC 2 INOP
BMC 2 INOP
INOP
INOP(a)
INOP
INOP
Continued on the following page
PRO-ABN-ELEC P 4/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC EMER CONFIG SYS REMAINING
EMER GEN RUNNING
Ident.: PRO-ABN-ELEC-S-00018019.0002001 / 17 MAR 17
APU
ECB-STARTER
FUEL LP VALVE
FUEL PUMP
Ident.: PRO-ABN-ELEC-S-00018540.0002001 / 17 MAR 17
PWR PLT
FADEC
IGNITION
HP FUEL VALVE closure
Ident.: PRO-ABN-ELEC-S-00012537.0001001 / 17 MAR 17
MISC
MECH HORN
Continued from the previous page
BAT ONLY
IN FLIGHT
ON THE GROUND
NORM(f)
NORM
NORM
NORM(g)
NORM
NORM
INOP(a)
NORM
NORM
A+B (h)
A only
NORM
A+B (h)
A only
NORM
A+B (h)
A only
NORM
NORM
NORM
NORM
(a)
Restored, when speed is below 100 kt.
(b)
Crew supply solenoid valve inoperative.
(c)
Lost, when the speed is below 50 kt.
(d)
Lost, 30 s after the last engine shutdown.
(e)
IR 2 and IR 3 are lost 5 min after failure of main generators but if IR 3 replaces IR 1 (ATT -HDG
selector at CAPT 3), IR 3 remains supplied.
(f)
For APU start only.
(g)
Not available for 45 s, after the loss of both engine generators.
(h)
Channels A and B are self powered above 10 % N2 for IAE or PW engines, 12 % N2 for CFM56
engines, or 8 % N2 for CFM LEAP-1A engines. If N2 is below these values, only Channel A is
powered.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-ABN-ELEC P 5/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC BUS 1 FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-I-00017346.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the AC 1 busbar is not supplied.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PRO-ABN-ELEC P 6/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC BUS 1 FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-I-00017853.0004001 / 21 MAR 16
L2
AC BUS 1 normally supplies the AC ESS BUS and, through TR1, the DC ESS BUS. In the case of
an AC BUS 1 FAULT, both the AC and DC ESS BUS will be lost and therefore the AC ESS BUS
FAULT and the DC ESS BUS FAULT will be displayed on the ECAM.
However, for aircraft equipped with AC ESS FEED Auto Switching , the AC ESS BUS and the
DC ESS BUS will automatically recover, due to the fact that the AC BUS 2 will automatically supply
the AC ESS BUS.
The flight crew can manually recover the AC ESS BUS and the DC ESS BUS by setting the AC
ESS FEED pb-sw to ALTN , as requested by the AC ESS BUS FAULT ECAM procedure
BLOWER.................................................................................................................................... OVRD
The avionics ventilation system is in the closed circuit configuration.
Air conditioning is added to the ventilation air.
L1 FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
L1
L2
L12
ASSOCIATED PROCEDURES
ENG 1 EPR MODE FAULT
This associated procedure is only applicable to aircraft equipped with IAE engines.
Refer to PRO-ABN-ENG ENG 1(2) EPR MODE FAULT (First Threshold).
SECONDARY FAILURES
* AVNCS VENT
* HYD
* FUEL
* F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PRO-ABN-ELEC P 7/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC BUS 1 FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-I-00017867.0028001 / 22 MAR 17
L12
STATUS
INOP SYS
LDG DIST PROC......................................................... APPLY
See below
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
SLATS SLOW
CAT 2 ONLY
INOP SYS
BLUE HYD
RA 1
L WNDW HEAT
CTR TK PUMP 1
CRG HEAT (if both FWD and aft crg
heat installed)
FWD CRG HEAT
GND COOL
BRK SYS 1/BSCU CH 1
LAV DET
STEEP APPR
SPLR 3
CAPT TAT
CAT 3
VENT BLOWER
ADR 3
L WSHLD HEAT
L+R TK PUMP 1
GALLEY FAN
CRG vent (if both FWD and aft crg
heat installed)
AFT CRG HEAT
AFT CRG VENT
MAIN GALLEY
FWD CRG VENT
B ELEC PUMP
DMC 3
REVERSER 1
GPWS
GPWS TERR
Other INOP SYS
Left cabin fan
Radar 1
Stby Pitot/AOA
HUD
EVMU eng 1 and eng 2
Hydraulic quantity indication
MCDU 3
Printer
Partial galley
COND Controller Lane A
ADF 1
TCAS
ACARS /ATSU
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Brake fans 5, 6, 7 and 8
Engine 1 ignition B
PVI
Continued on the following page
←C→
PRO-ABN-ELEC P 8/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC BUS 1 FAULT (Cont'd)
Note:
(1)
(2)
The warning may be caused by a sub BUS failure. Consequently, only a part of the
above-listed systems may be lost.
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data- Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
ELEC AC BUS 2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-J-00017348.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the AC 2 busbar is not supplied.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
PRO-ABN-ELEC P 9/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC BUS 2 FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-J-00017877.0002001 / 21 MAR 16
EXTRACT................................................................................................................................... OVRD
The avionics ventilation system is in the closed circuit configuration.
Air conditioning is added to the ventilation air.
L1 ATC/XPDR................................................................................................................................. SYS 1
L2
ASSOCIATED PROCEDURES
L/G LGCIU 2 FAULT
L12
ASSOCIATED PROCEDURES
ENG 2 EPR MODE FAULT
This associated procedure is only applicable to aircraft equipped with IAE engines.
Refer to PRO-ABN-ENG ENG 1(2) EPR MODE FAULT (First Threshold).
SECONDARY FAILURES
* AVNCS VENT
* FUEL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
PRO-ABN-ELEC P 10/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC BUS 2 FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-J-00017878.0005001 / 22 MAR 17
L12
STATUS
INOP SYS
ENG 2 APPR IDLE ONLY
FLS : F-APP+RAW ONLY
See below
INOP SYS
ADR 2
FWC 2
R WSHLD HEAT
F/O PITOT
R WNDW HEAT
REVERSER 2
Y ELEC PUMP
DMC 2
LGCIU 2
F/O AOA
L+R TK PUMP 2
VENT EXTRACT
PACK 2 REGUL
RUD TRIM 2
MAIN GALLEY
FAC 2
CTR TK PUMP 2
ILS 2 (OR LS 2 for aircraft equipped
with MLS /GLS /FLS )
GLS AUTOLAND
ACT PUMP
GPS 2
SDAC 2
RECORDER SYS (OR FDIU)
RA 2
F/O TAT
RUD TRV LIM 2
GND COOL
YAW DAMPER 2
CAT 2
BRK SYS 2 /BSCU CH 2
ATC 2 or ATC/XPDR 2
ROW/ROP
Other INOP SYS
Brake fans 1, 2, 3 and 4
Right cabin fan
DME 2
MCDU 2
F/O PFD and ND
HF 2
Note:
RADAR 2
ENG 2 ignition B
QAR
ADF 2
WXR 2
VOR 2
ECAM lower DU
The warning may be caused by a sub BUS failure. Consequently, only a part of the
above-listed systems may be lost.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PRO-ABN-ELEC P 11/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC ESS BUS ALTN
Applicable to: ALL
Ident.: PRO-ABN-ELEC-Z-00017356.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the AC ESS busbar is supplied from the AC 2 busbar although the AC
ESS FEED pb-sw is set to normal.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-Z-00017893.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-ELEC P 12/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC ESS BUS FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-K-00017357.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the AC ESS busbar is not supplied.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-K-00012502.0002001 / 24 MAR 11
AC ESS FEED............................................................................................................................ ALTN
AC BUS 2 supplies AC ESS BUS.
L1 ATC/XPDR................................................................................................................................. SYS 2
L2
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PRO-ABN-ELEC P 13/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC ESS BUS FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-K-00018552.0014001 / 01 JUN 16
L12
STATUS
INOP SYS
See below
INOP SYS
ADR 1
CAPT PITOT
SDAC 1
GPWS
RUD TRIM 1
LS 1
CAPT AOA
FWC 1
GPWS terr
RUD TRV LIM 1
ATC 1 or ATC/XPDR 1
GPS 1
CAT 2
DMC 1
YAW DAMPER 1
GLS AUTOLAND
ROW/ROP
Other INOP SYS
RMP’s lighting (RMP’s still operative)
CVR
CAPT PFD
DDRMI
Note:
VOR 1
ECAM upper display
DME 1
HF 1
MCDU 1
CAPT ND
APU fuel pump
Passenger oxygen masks (auto +
manual)
The warning may be caused by a sub BUS failure. As a result, only a part of the
above-listed systems may be lost.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
PRO-ABN-ELEC P 14/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC ESS BUS SHED
Applicable to: ALL
Ident.: PRO-ABN-ELEC-L-00017349.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the AC SHED ESS busbar is not supplied.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-L-00012504.0002001 / 03 DEC 13
ATC/XPDR................................................................................................................................. SYS 2
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G→
PRO-ABN-ELEC P 15/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC AC ESS BUS SHED (Cont'd)
Ident.: PRO-ABN-ELEC-L-00018554.0004001 / 21 MAR 16
L12
STATUS
INOP SYS
CAPT AOA
ATC 1 or ATC/XPDR 1
See below
Other INOP SYS
MCDU 1
CVR
Passenger oxygen masks (auto
+ manual)
DME 1
CAPT AOA heat
APU fuel pump
CAPT ND
HF 1
Note:
The warning may be caused by a failure in a sub BUS. Consequently only a part of the
systems listed above may be lost.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-ABN-ELEC P 16/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC APU GEN FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-E-00017362.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The protection trip is initiated by the associated GCU, or
‐ The line contactor is open with APU GEN pb-sw set to ON.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-E-00012490.0002001 / 18 MAR 11
APU GEN.................................................................................................................... OFF THEN ON
IF UNSUCCESSFUL:
APU GEN................................................................................................................................OFF
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H→
PRO-ABN-ELEC P 17/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC APU GEN FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-E-00012491.0001001 / 18 MAR 11
STATUS
INOP SYS
MAIN GALLEY
APU GEN
(1)
(1)
(When only one GEN operating)
ELEC BAT 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-F-00017367.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the charging current increases at an abnormal rate.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-F-00017894.0001001 / 21 MAR 16
L2
Battery contactor is opened automatically by the battery charge limiter.
L1
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← H to I →
PRO-ABN-ELEC P 18/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC BAT 1(2) FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-F-00017895.0001001 / 21 MAR 16
STATUS
INOP SYS
APU BAT START NOT AVAIL
BAT 1(2)
ELEC BAT 1(2) OFF
Applicable to: ALL
Ident.: PRO-ABN-ELEC-G-00017371.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the BAT 1(2) pb-sw is set to OFF and no failure is detected.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-G-00018943.0001001 / 21 MAR 16
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← I to J →
PRO-ABN-ELEC P 19/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC BAT 1(2) OFF (Cont'd)
Ident.: PRO-ABN-ELEC-G-00012495.0001001 / 19 AUG 10
STATUS
APU BAT START NOT AVAIL
ELEC BCL 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-H-00017377.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the battery charge limiter 1(2) is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-H-00012496.0001001 / 25 FEB 14
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← J to K →
PRO-ABN-ELEC P 20/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC BCL 1(2) FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-H-00012497.0001001 / 19 AUG 10
STATUS
INOP SYS
APU BAT START NOT AVAIL
BCL 1(2)
ELEC DC BAT BUS FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-W-00017358.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the DC BAT busbar is not supplied.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-W-00012545.0001001 / 22 MAR 16
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← K to L →
PRO-ABN-ELEC P 21/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC BAT BUS FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-W-00012546.0021001 / 21 MAR 16
L12
STATUS
INOP SYS
APU BAT START NOT AVAIL
ECB is no longer supplied
APU FIRE DET
Other INOP SYS
APU ECB
Stick and rudder pedals lock
(by AP)
Forward (aft) cargo fire
extinguishing
Forward (aft) cargo heat
controller
AFT Cargo isol valves
APU fuel LP valve
Manual pressure control
Note:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←L
The warning may
be caused by a
sub BUS failure.
Consequently,
only a part of
the above-listed
systems may be
lost.
PRO-ABN-ELEC P 22/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC BUS 1 FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-M-00017350.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the DC 1 busbar is not supplied.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-M-00012507.0001001 / 15 DEC 15
BLOWER.................................................................................................................................... OVRD
EXTRACT................................................................................................................................... OVRD
L2 The Air conditioning system provides ventilation to the avionics. This ventilation air is exhausted
overboard.
L1
SECONDARY FAILURES
*AVNCS VENT
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
M→
PRO-ABN-ELEC P 23/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC BUS 1 FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-M-00018555.0012001 / 22 MAR 17
L12
STATUS
INOP SYS
CAT 3 SINGLE ONLY
See below
INOP SYS
ACP 3
L. WSHLD HEAT
CAPT STAT heat
L. WNDW HEAT
AVNCS VENT
GALLEY FAN
REVERSER 1
CAT 3 DUAL
BRAKES SYS 1
STBY STAT heat
CTR TK PUMP 1
GND COOL
LAV DET
Other INOP SYS
Left cab fan
CFDIU
L CTR TK XFR valve
Eng 1 oil press and qty ind.
Note:
COND controller lane A
Sel cal
TPIS
Brake temps ind.
VHF 3
Hot air
RMP 3
Capt wiper
The warning may be caused by a sub BUS failure. Consequently, only a part of the
above-listed systems may be lost.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←M
PRO-ABN-ELEC P 24/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC BUS 2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-N-00017352.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the DC 2 busbar is not supplied.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-N-00017898.0004001 / 21 MAR 16
AIR DATA SWTG......................................................................................................................... F/O3
BARO REF...............................................................................................................................CHECK
L2 Since one FCU channel is lost, crosscheck the barometer reference settings on the FCU and PFD.
L1
If DC ESS BUS is failed:
L/G.......................................................................................................................... GRVTY EXTN
L2
Refer to PRO-ABN-LG [QRH] L/G GRAVITY EXTENSION.
L1
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
* CAB PRESS
* FUEL
* WHEEL
* F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
N→
PRO-ABN-ELEC P 25/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC BUS 2 FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-N-00017899.0013001 / 22 MAR 17
L12
STATUS
IF ABN CAB V/S:
MAX FL.............................................................. 100/MEA
If DC ESS BUS is failed:
L/G..............................................................GRVTY EXTN
INOP SYS
See below
LDG DIST PROC......................................................... APPLY
FUEL CONSUMPT INCRSD
(3)
See
FMS PRED UNRELIABLE
(4)
See
ENG 2 APPR IDLE ONLY
BOTH PFD ON SAME FAC
If DC ESS BUS is failed:
L/G CONTROL NOT AVAIL
SLATS/FLAPS SLOW
CAT 3 SINGLE ONLY
INOP SYS
SPLR 1+2+5
VHF 2
R WNDW HEAT
CAT 3 DUAL
R TK PUMP 2
REVERSER 2
Y ELEC PUMP (if selected ON)
ENG 2 LOOP A
SEC 2+3
(1)
ELAC 2
F/O STAT
AP 2
FAC 2
CTR TK PUMP 2
CAB PR 2
BRK SYS 2
FCDC 2
ROW/ROP
R WSLHD HEAT
FCU 2
L TK PUMP 2
LGCIU 2
MAIN GALLEY
ENG 1 LOOP B
LGCIU 1
(2)
Other INOP SYS
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←N→
PRO-ABN-ELEC P 26/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC BUS 2 FAULT (Cont'd)
SFCC 2
F/O rain rplnt
BMC 2
FQI channel 2
R cabin fan
Eng 1 and 2 fire ext btl 2
Bleed X feed auto control
Brake fan
rudder trim ind
Eng 2 oil low press and qty ind
Note:
(1)
(2)
(3)
(4)
CTR TK XFR valve R
FMGC 2
F/O wiper
Autobrake (due to loss of 2 SECs)
RMP 2
SDCU 2 or CIDS 2 SMOKE
DETECT
R loudspeaker
CDLS
‐ The warning may be caused by a sub BUS failure. Consequently, only a part of the
above-listed systems may be lost.
‐ The flight crew must monitor the CAB V/S, because the proximity sensor of the
bulk cargo door is no longer electrically supplied.
Lost after 30 s, but recovered at landing gear extension.
(If DC ESS BUS is failed)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←N
PRO-ABN-ELEC P 27/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC BUS 1+2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-Q-00017353.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the DC 1 and DC 2 busbars are not supplied.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
O→
PRO-ABN-ELEC P 28/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC BUS 1+2 FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-Q-00018565.0004001 / 21 MAR 16
BLOWER.................................................................................................................................... OVRD
EXTRACT................................................................................................................................... OVRD
BARO REF...............................................................................................................................CHECK
L2 Crosscheck the barometer reference settings on the FCU and PFDs.
L1 FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
MAX BRK PR.......................................................................................................................1 000 PSI
L2 Brake pressure must be limited to approximately 1 000 PSI, since antiskid is lost.
L1
ASSOCIATED PROCEDURES
ELEC DC BAT BUS FAULT
SECONDARY FAILURES
* CAB PRESS
* FUEL
* AIR COND
* BRAKES
* F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←O→
PRO-ABN-ELEC P 29/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC BUS 1+2 FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-Q-00018566.0018001 / 22 MAR 17
L12
STATUS
MAX BRK PR............................................................1000 PSI
INOP SYS
LDG DIST PROC......................................................... APPLY
See below
FUEL CONSUMPT INCRSD
(2)
See
FMS PRED UNRELIABLE
(3)
See
ENG 1 APPR IDLE ONLY
ENG 2 APPR IDLE ONLY
BOTH PFD ON SAME FAC
CTR TK FUEL UNUSABLE
APU BAT START NOT AVAIL
SLATS/FLAPS SLOW
CAT 3 SINGLE ONLY
FLS LIMITED TO F-APP+RAW
INOP SYS
SPLR 1+2+5
VHF 2
F/O STAT heat
WNDW HEAT
CAT 3 DUAL
ANTI SKID
REVERSER 1+2
L+R CAB FAN
GND COOL
Brk sys 1+2
ENG 1 LOOP B
FCDC 2
R TK PUMP 2
(1)
ELAC 2
ACP 3
STBY STAT heat
AP 2
FAC 2
N/W STRG
CAB PRESS 2
GALLEY FAN
SEC 2+3
CAPT STAT heat
WSHLD HEAT
FCU 2
SDCU
LGCIU 2
AVNCS VENT
MAIN GALLEY
CRG HEAT
Y ELEC PUMP
APU FIRE DET
ENG 2 LOOP A
CTR TK PUMPS
LAV DET
PACK 2
L TK PUMP 2
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←O→
PRO-ABN-ELEC P 30/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC BUS 1+2 FAULT (Cont'd)
Other INOP SYS
Selcal
Brake temp indication
TPIS
Capt and F/O wipers
AUTO BRK
Forward (aft) cargo isolation valves
VHF 3
CFDIU
APU ECB
RMP 2
Right loudspeakers
Forward (aft) cargo heat controller
FMGC 2
FQI channel 2
Stick and rudder pedals lock (by AP)
Note:
(1)
(2)
(3)
Rudder trim indication
Eng 1 and 2 fire ext btl 2
Forward (aft) cargo fire extinguishing
Brake fans
Eng 1 and 2 oil pressure and quantity
indication
Manual pressure control
RMP 3
SFCC 2
CDLS
BMC 2
X Bleed auto and manual control
SDCU 2 or CIDS 2 SMOKE
DETECT
The warning may be caused by a failure in a sub BUS. Consequently, only a part of
the above-listed systems may be lost.
Lost after 30 s, but is recovered at landing gear extension.
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←O
PRO-ABN-ELEC P 31/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC EMER CONFIG
Applicable to: ALL
Ident.: PRO-ABN-ELEC-X-00017359.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the DC 1, DC 2 and DC ESS busbars are not supplied.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
P→
PRO-ABN-ELEC P 32/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC EMER CONFIG (Cont'd)
Ident.: PRO-ABN-ELEC-X-00018557.0006001 / 21 MAR 16
LAND ASAP
EMER ELEC PWR.................................................................................................................MAN ON
The emergency generator supplies DC ESS BUS.
But, DC BUS 1, DC BUS 2, and DC BAT BUS are still not supplied.
L1 FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
L2
ASSOCIATED PROCEDURES
ELEC DC BUS 1 + 2 FAULT
BLOWER.................................................................................................................................... OVRD
EXTRACT................................................................................................................................... OVRD
BARO REF...............................................................................................................................CHECK
L2 Crosscheck the barometer reference settings on the FCU and PFDs.
L1 MAX BRK PR.......................................................................................................................1 000 PSI
L2 Brake pressure must be limited to approximately 1 000 PSI, since antiskid is lost.
L1 FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
ASSOCIATED PROCEDURES
ELEC DC BAT BUS FAULT
SECONDARY FAILURES
* CAB PRESS
* HYD
* FUEL
* AIR COND
* BRAKES
* WHEEL
* F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←P→
PRO-ABN-ELEC P 33/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC EMER CONFIG (Cont'd)
Ident.: PRO-ABN-ELEC-X-00018558.0003001 / 21 MAR 16
L12
STATUS
Refer to the list of INOP SYS ON
ECAM of the ELEC DC BUS 1+2
FAULT ECAM alert
LDG DIST PROC......................................................... APPLY
Note:
Refer to the list of STATUS INFO of the ELEC DC BUS 1+2
BUS FAULT ECAM alert
(1)
See
(1)
INOP SYS
MIN RAT SPEED......................................................... 140 KT
PROC: GRVTY FUEL FEEDING
MAX BRK PR.......................................................... 1 000 PSI
FUEL GRVTY FEED
Note:
To verify the other
INOP SYS not
displayed on the
ECAM,Refer to
PRO-ABN-ELEC
ELEC DC BUS
1+2 FAULT
- FWSPAGE
and Refer to
PRO-ABN-ELEC
ELEC DC BAT
BUS FAULT FWSPAGE.
DC ESS BUS is lost at landing gear extension.
Consequently, all means of communications are lost since all ACPs are lost.
To verify the list of STATUS INFO, Refer to PRO-ABN-ELEC ELEC DC BUS 1+2
FAULT - FWSPAGE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←P
PRO-ABN-ELEC P 34/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC ESS BUS FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-O-00017354.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the DC ESS busbar is not supplied.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Q→
PRO-ABN-ELEC P 35/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC ESS BUS FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-O-00012511.0005001 / 05 MAR 13
VHF 2 OR 3.................................................................................................................................. USE
AUDIO SWTG.........................................................................................................................SELECT
L2 ACP 1 and 2 are lost. Therefore, set the AUDIO SWTG rotary selector to CAPT 3 or F/O 3 to
recover communications.
L1 BARO REF...............................................................................................................................CHECK
L2 Crosscheck the barometer reference settings on the FCU and the PFD.
L1 GPWS SYS................................................................................................................................... OFF
If DC BUS 2 is failed:
L/G.......................................................................................................................... GRVTY EXTN
L2
Refer to PRO-ABN-LG [QRH] L/G GRAVITY EXTENSION.
L1
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
AVOID ICING CONDITIONS
ASSOCIATED PROCEDURES
L2
NAV GPWS FAULT
GPWS............................................................................................................................................ OFF
Note:
To shut down the engines on ground, use the ENG FIRE pb-sw.
L1
SECONDARY FAILURES
* CAB PRESS
* HYD
* F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←Q→
PRO-ABN-ELEC P 36/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC ESS BUS FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-O-00018671.0012001 / 25 JUL 17
L12
STATUS
INOP SYS
If DC BUS 2 is failed:
L/G..............................................................GRVTY EXTN
See below
LDG DIST PROC......................................................... APPLY
FUEL CONSUMPT INCRSD
(3)
See
FMS PRED UNRELIABLE
(4)
See
ENG 1 APPR IDLE ONLY
ENG 2 APPR IDLE ONLY
BOTH PFD ON SAME FAC
If DC BUS 2 is failed:
L/G CONTROL NOT AVAIL
SLATS/FLAPS SLOW
CAT 3 SINGLE ONLY
INOP SYS
B HYD
ACP 1+2
A/THR
L TK PUMP 1
ENG 2 START
SPLR 3
WING A. ICE
FCU 1
R TK PUMP 1
CAB PR 1
VENT EXTRACT
ENG 1 LOOP A
LGCIU 1
B ELEC PUMP
ENG 2 LOOP B
AUTO BRK
ROW/ROP
LGCIU 2
VHF 1
AP 1
FAC 1
REV 2
(1)
STEEP APPR
GPWS
FCDC 1
ALTN BRK
Other INOP SYS
BRK PRESS indicator
Flight interphone
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←Q→
EIU 2
(2)
Continued on the following page
PRO-ABN-ELEC P 37/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC ESS BUS FAULT (Cont'd)
Capt rain repellent
HP fuel shutoff valves
Hyd fire valves Eng 1 and 2
Left loudspeaker
Note:
(1)
(2)
(3)
(4)
Avionics air cond valve
Standby compass light
SFCC 1
Ram air inlet
DC SHED ESS BUS
RMP 1
ECAM Control Panel
1. The warning may be caused by a sub BUS failure. Consequently, only a part of the
above-listed systems may be lost.
(If DC BUS 2 is failed)
Autothrust, eng start and reverser inop.
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
ELEC DC ESS BUS SHED
Applicable to: ALL
Ident.: PRO-ABN-ELEC-P-00017355.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the DC SHED ESS busbar is not supplied.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← Q to R →
PRO-ABN-ELEC P 38/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC ESS BUS SHED (Cont'd)
Ident.: PRO-ABN-ELEC-P-00012513.0001001 / 30 MAR 12
EXTRACT................................................................................................................................... OVRD
Cooling air is supplied by the air conditioning system, without overboard extraction.
L1 AVOID ICING CONDITIONS
SECONDARY FAILURES
L2
*AVNCS VENT
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←R→
PRO-ABN-ELEC P 39/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC ESS BUS SHED (Cont'd)
Ident.: PRO-ABN-ELEC-P-00018561.0005001 / 17 MAR 17
L12
STATUS
INOP SYS
AVOID ICING CONDITIONS
IF SEVERE ICE ACCRETION
MIN SPD................................................VLS + 10/G DOT
MANEUVER WITH CARE
LDG DIST PROC...................................................APPLY
BOTH PFD ON SAME FAC
CAT 3 SINGLE ONLY
WING A. ICE
AP 1
CAT 3 DUAL
FAC 1
VENT EXTRACT
AFT CRG HEAT
FWD CRG HEAT
AFT CRG VENT
FWD CRG VENT
FCDC 1
ROW/ROP
See below
Other INOP SYS
Passenger oxygen mask (auto
drop out)
X BLEED valve man ctl
FMGC 1
STBY ALTI vib
FQ1 channel 1
BMC 1
SDCU 1 or CIDS 1 SMOKE
DETECT
Note:
The warning
may be caused
by a failure in
a sub BUS.
Consequently
only a part of the
systems listed
above may be
lost.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←R→
PRO-ABN-ELEC P 40/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC DC ESS BUS SHED (Cont'd)
ELEC EMER CONFIG
Applicable to: ALL
Ident.: PRO-ABN-ELEC-R-00018283.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the AC 1 and AC 2 busbars are not supplied.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← R to S →
PRO-ABN-ELEC P 41/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC EMER CONFIG (Cont'd)
Ident.: PRO-ABN-ELEC-R-00018642.0006001 / 22 MAR 17
LAND ASAP
MIN RAT SPEED......................................................................................................................140 KT
CAUTION
The RAT is capable of supplying the EMER GEN down to 125 kt, except during
flare.
GEN 1 + 2................................................................................................................... OFF THEN ON
IF UNSUCCESSFUL:
BUS TIE.................................................................................................................................. OFF
L2
Setting BUS TIE pb-sw to OFF segregates both generator channels.
L1
GEN 1 + 2.............................................................................................................OFF THEN ON
L2
Note:
L1
EMER ELEC PWR (IF EMER GEN NOT IN LINE)........................................................ MAN ON
ENG MODE SEL..................................................................................................................... IGN
Engines are fed by gravity only.
L2
L1
L2
If any generator reset is successful, reset both FAC’s.
VHF1/HF1 /ATC1....................................................................................................................USE
Only VHF 1, HF 1 and ATC 1 are supplied in the electrical emergency configuration.
Note:
FMGC 1, which is lost temporarily, can be regained by flight crew passing through the
MCDU MENU page.
FUEL GRVTY FEED
Engines are fed by gravity only. Avoid negative Gs.
L1 PROC: GRVTY FUEL FEEDING
L2 Apply GRVTY FUEL FEEDING procedure (Refer to PRO-ABN-FUEL [QRH] GRAVITY FUEL
FEEDING).
L1 FAC 1.......................................................................................................................... OFF THEN ON
L2 The rudder trim is recovered, although no indication is available.
L1 BUS TIE......................................................................................................................................AUTO
L2 Setting BUS TIE pb-sw to AUTO enables the APU to take an available electrical channel.
L1 APU (IF AVAIL)........................................................................................................................ START
L2 APU start is not available for 45 s after the loss of both engine generators. This 45 s delay prevents
any interference with emergency generator coupling.
L1
L2
Continued on the following page
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FCOM
←S→
PRO-ABN-ELEC P 42/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC EMER CONFIG (Cont'd)
If the APU is available, the APU may be started when below FL 250.
BLOWER + EXTRACT...............................................................................................................OVRD
L2 Cooling air is supplied by the air conditioning system and exhausted overboard through the extract
valve.
L1 FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
L1
L2
Note:
On IAE powered aircraft, the warning “EPR MODE FAULT N1 DEGRADED MODE” is
displayed.
L1
ASSOCIATED PROCEDURES
FLT CTL ALTN LAW
(PROT LOST)
MAX SPEED.............................................................................................................................320 KT
L2 Speed limited due to loss of flight control normal laws.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←S→
PRO-ABN-ELEC P 43/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC EMER CONFIG (Cont'd)
Ident.: PRO-ABN-ELEC-R-00018643.0023001 / 22 MAR 17
L12
STATUS
MIN RAT SPEED......................................................... 140 KT
MAX SPEED................................................................ 320 KT
MAX BRK PR.......................................................... 1 000 PSI
FUEL GRVTY FEED
AVOID NEGATIVE G FACTOR
Note:
If there are discrepancies between airspeed
indications on the Captain’s PFD and on the STBY
indicator, disregard the STBY indication (probe not
deiced).
APPR PROC
FOR LDG............................................................ USE FLAP 3
This line is replaced by "FOR LDG : USE FLAP 3" when
CONF 3 is selected, as a reminder.
APPR SPD................................................. VREF +10/140 KT
The approach speed must be at least minimum RAT speed
(140 kt).
LDG DIST PROC......................................................... APPLY
INOP SYS
F/CTL PROT
REVERSER 1+2
ADR 2+3
IR 2
RA 1+2
SPLR 1+2+5
ELAC 2
SEC 2+3
A/CALL OUT
AP 1+2
A/THR
FUEL PUMPS
ANTI SKID
N/W STRG
CAT 2
STEEP APPR
See
(1)
FUEL CONSUMPT INCRSD
(2)
See
FMS PRED UNRELIABLE
(3)
See
ALTN LAW: PROT LOST
WHEN L/G DN: DIRECT LAW
SLATS/FLAPS SLOW
FLS LIMITED TO F-APP + RAW
(4)
See
(1)
For other systems’ status: Refer to the “ELEC EMER CONFIG SYS REMAINING” table.
Continued on the following page
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FCOM
←S→
PRO-ABN-ELEC P 44/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC EMER CONFIG (Cont'd)
(2)
(3)
(4)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/PER-B Fuel Penalty Factors Tables in order to
find the applicable Fuel Penalty Factor.
Note:
In ELEC EMER configuration, the center tank fuel is unusable.
ELEC EMER GEN 1 LINE OFF
Applicable to: ALL
Ident.: PRO-ABN-ELEC-AB-00017382.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the GEN 1 LINE pb-sw is abnormally set to OFF position.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-AB-00012550.0001001 / 25 FEB 14
L2
With the GEN 1 LINE pb-sw (on the EMER ELEC PWR panel) in the OFF position, the GEN 1 line
contactor is open and GEN 2 supplies the AC BUS 1 channel.
L1
Crew awareness.
L2
Set the GEN 1 LINE pb-sw to ON.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← S to T
PRO-ABN-ELEC P 45/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC ESS BUSES ON BAT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-AA-00018284.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the DC ESS and AC ESS busbars are supplied by the batteries.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-AA-00018021.0002001 / 21 MAR 16
L2
AC ESS BUS is supplied via the static inverter.
LAND ASAP
L1
MIN RAT SPEED......................................................................................................................140 KT
Displayed, if the RAT is extended.
L1 EMER ELEC PWR.................................................................................................................MAN ON
L2 ESS BUSES are supplied by the emergency generator
L2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
U
PRO-ABN-ELEC P 46/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC GEN 1(2) OR APU GEN OVERLOAD
Applicable to: ALL
Ident.: PRO-ABN-ELEC-T-00017363.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the load of one generator is above 100% of rated output.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-T-00018023.0002001 / 21 MAR 16
GALY/CAB..................................................................................................................................... OFF
Ident.: PRO-ABN-ELEC-T-00018024.0002001 / 21 MAR 16
STATUS
INOP SYS
GALY/CAB
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
V
PRO-ABN-ELEC P 47/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC GEN 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-B-00017360.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:.
‐ The protection trip is initiated by the associated GCU, or
‐ The line contactor is open with the associated GEN pb-sw set to ON.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-B-00018025.0001001 / 21 MAR 16
GEN (AFFECTED).......................................................................................................OFF THEN ON
IF UNSUCCESSFUL:
GEN (AFFECTED)..................................................................................................................OFF
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
W→
PRO-ABN-ELEC P 48/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC GEN 1(2) FAULT (Cont'd)
Ident.: PRO-ABN-ELEC-B-00018026.0001001 / 21 MAR 16
L12
STATUS
Note:
If available, the APU may be started, and the APU
GEN used.
CAT 3 SINGLE ONLY
(1)
INOP SYS
MAIN GALLEY
GEN 1(2)
CAT 3 DUAL
(1)
(only if APU GEN is not online)
ELEC GEN 1(2) OFF
Applicable to: ALL
Ident.: PRO-ABN-ELEC-C-00017361.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the GEN 1(2) pb-sw is set to OFF and no failure is detected.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← W to X →
PRO-ABN-ELEC P 49/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC GEN 1(2) OFF (Cont'd)
Ident.: PRO-ABN-ELEC-C-00018027.0001001 / 21 MAR 16
L2
Turn the affected GEN ON.
L1
Crew awareness.
Ident.: PRO-ABN-ELEC-C-00018028.0001001 / 21 MAR 16
STATUS
INOP SYS
CAT 3 SINGLE ONLY
(1)
MAIN GALLEY
GEN 1(2)
CAT 3 DUAL
(1)
(only if APU GEN is not online)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←X
PRO-ABN-ELEC P 50/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC IDG 1(2) DISCONNECTED
Applicable to: ALL
Ident.: PRO-ABN-ELEC-D-00017366.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
This alert triggers when the IDG 1(2) is disconnected.
L2
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-D-00018029.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-ELEC-D-00018030.0001001 / 21 MAR 16
L12
STATUS
Note:
If available, the APU may be started, and the APU
GEN used.
CAT 3 SINGLE ONLY
(1)
INOP SYS
MAIN GALLEY
GEN 1(2)
CAT 3 DUAL
(1)
(only if APU GEN is not online)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Y
PRO-ABN-ELEC P 51/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC IDG 1(2) OIL LO PR/OVHT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-A-00018285.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
The alert ELEC IDG 1(2) OIL LO PR triggers when the IDG 1(2) oil pressure is low.
The alert ELEC IDG 1(2) OIL OVHT triggers when the IDG 1(2) outlet oil temperature rises
above 185 °C.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-A-00018031.0001001 / 21 MAR 16
L2
IDG (AFFECTED)..........................................................................................................................OFF
If the associated engine is running, the IDG (integrated drive generator) must be disconnected from
the engine at, or above, idle to prevent damage to the disconnect mechanism.
Press the IDG pb-sw until the GEN FAULT light comes on. However, do not press for more than
3 s, to avoid damage to the disengage solenoid
The IDG FAULT light goes off, when the IDG is disconnected.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Z→
PRO-ABN-ELEC P 52/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC IDG 1(2) OIL LO PR/OVHT (Cont'd)
Ident.: PRO-ABN-ELEC-A-00018032.0001001 / 21 MAR 16
L12
STATUS
Note:
If available, the APU may be started and the APU
GEN used.
CAT 3 SINGLE ONLY
(1)
INOP SYS
MAIN GALLEY
GEN 1(2)
CAT 3 DUAL
(1)
(only if APU GEN is not online)
ELEC STATIC INV FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-AC-00017380.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
The alert triggers when the static inverter is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-AC-00012549.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← Z to AA
PRO-ABN-ELEC P 53/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ELEC
FLIGHT CREW
OPERATING MANUAL
ELEC TR 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-ELEC-U-00017373.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the TR 1(2) is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-ELEC-U-00012541.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-ELEC-U-00018531.0001001 / 21 MAR 16
STATUS
INOP SYS
CAT 3 SINGLE ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
TR 1(2)
CAT 3 DUAL
AB
PRO-ABN-ELEC P 54/54
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - FUEL REMAINING
Applicable to: ALL
Ident.: PRO-ABN-ENG-X-00012309.0061001 / 17 MAR 17
As long as none of the engines recover, the flight crew must apply this paper procedure when
required by the ECAM ENG DUAL FAILURE procedure. If time permits, clear ECAM alerts, and
check the ECAM STATUS page.
LAND ASAP
OPTIMUM RELIGHT SPD......................................................................................................... 300 kt
PITCH TARGET In case of speed indication failure:
Gross Weight
Pitch (°)
At or below 50 000 kg/110 000 lb
-4.5
60 000 kg/132 000 lb
-3.5
70 000 kg/154 000 lb
-2.5
AVERAGE GLIDING DISTANCE : 2 NM / 1000 FT (300kt NO WIND)
DETERMINE LANDING STRATEGY
VHF1/HF1 /ATC1....................................................................................................................USE
ATC..........................................................................................................................................NOTIFY
TRANSPONDER.........................................................................................................SELECT A7700
Notify air traffic control of the nature of the emergency, and state intentions. If there is no contact
with air traffic control Switch to code A7700, or transmit a distress message on one of the following
frequencies: VHF frequency 121.5 MHz, HF 2 182 kHz or 8 364 kHz.
If no relight after 30 s:
ENG MASTERS....................................................................................................OFF 30 S / ON
Unassisted start attempts can be repeated until successful, or until APU bleed is available.
If unsuccessful:
CREW OXY MASKS (above FL 100)...................................................................................... ON
Cabin altitude will increase, due to the lack of engine bleed: The EXCESS CAB ALT warning
could be triggered. Depending on the situation, to gain gliding distance, the flight crew may
disregard the ECAM emergency descent requirement, because passengers will be provided
with oxygen for a sufficient period of time.
APU (IF AVAIL)..................................................................................................................START
If the APU is available, it may be started when below FL 250 and the APU BLEED may be used
for engine start below FL 200.
WING ANTI ICE......................................................................................................................OFF
Continued on the following page
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PRO-ABN-ENG P 1/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - FUEL REMAINING (Cont'd)
APU BLEED..............................................................................................................................ON
In sequence:
ENG MASTERS (all non running engines)......................................................................OFF
After 30 s
ENG MASTERS (one at a time)........................................................................................ON
Between each attempt to relight the same engine, wait at least 30 s with the associated
ENG MASTER lever set to OFF.
Continued on the following page
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PRO-ABN-ENG P 2/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - FUEL REMAINING (Cont'd)
Ident.: PRO-ABN-ENG-X-00012310.0041001 / 17 MAR 17
When APU bleed is available or if engine restart is definitively considered impossible:
OPTIMUM SPEED WITH ALL ENGINES INOPERATIVE (KNOTS)
Gross Weight (1 000 kg)
At or below FL 200
FL 300
241
251
78
76
72
68
64
60
56
52
48
44
40
237
247
221
231
229
239
213
223
205
215
197
207
189
199
181
191
173
183
165
175
FL 400
261
257
249
241
233
225
217
209
201
193
185
AVERAGE GLIDING DISTANCE: 2.5 NM / 1000 FT (NO WIND)
AVERAGE RATE OF DESCENT: 1 600 FT/MIN
PREPARE CABIN AND COCKPIT
‐ Loose equipment secured.
‐ Survival equipments prepared.
‐ Belts and shoulder harnesses locked.
SIGNS....................................................................................................................................... ON
COMMERCIAL........................................................................................................................ OFF
USE RUDDER WITH CARE
As hydraulic power is only available from the RAT, avoid large and rapid rudder deflection.
When below FL 150:
RAM AIR...................................................................................................................................ON
Ident.: PRO-ABN-ENG-X-00012311.0001001 / 17 MAR 17
BARO REF.................................................................................................................................... SET
CREW MASKS/OXY SUPPLY (below FL 100)............................................................................ OFF
ELT (when conditions permit)................................................................................................. ON
Continued on the following page
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PRO-ABN-ENG P 3/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - FUEL REMAINING (Cont'd)
Ident.: PRO-ABN-ENG-X-00012312.0065001 / 09 MAY 17
If forced landing anticipated:
AVERAGE GLIDING DISTANCE 1.2NM / 1000FT (CONF3, L/G DOWN, NO WIND)
For approach:
FOR LANDING : USE FLAP 3
SLATS AVAIL ONLY
MIN APPR SPEED : 150 kt
VAPP.................................................................................................................. DETERMINE
Gross Weight (1 000 kg)
VAPP
40
150
44
150
48
150
52
150
56
150
60
155
64
159
68
163
72
167
76
171
78
173
At a suitable altitude (not below 3 000 ft AGL):
When in CONF 3 and VAPP:
GRAVITY GEAR EXTN handcrank............................................... PULL AND TURN
FLT CTL DIRECT LAW
MAN PITCH TRIM NOT AVAILABLE
When L/G downlocked:
L/G lever..........................................................................................................DOWN
APPROACH SPEED.................................................................................... ADJUST
MAX SPEED : 200 kt
ADJUST SPEED TO REACH LANDING FIELD
SPLRs.................................................................................................................ARM
MAX BRK PR : 1 000 PSI
At 2 000 ft AGL:
CABIN CREW.................................................................................. NOTIFY FOR LANDING
At 500 ft AGL:
BRACE FOR IMPACT................................................................................................ORDER
At touchdown:
ENG MASTERS............................................................................................................... OFF
APU MASTER SW........................................................................................................... OFF
BRAKES ON ACCU ONLY
Continued on the following page
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PRO-ABN-ENG P 4/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - FUEL REMAINING (Cont'd)
When aircraft stopped:
PARKING BRK...................................................................................................................ON
ATC.............................................................................................................................NOTIFY
FIRE pb (ENGs & APU)................................................................................................PUSH
AGENT (ENGs & APU)................................................................................................DISCH
If evacuation required:
EVACUATION.................................................................................................... INITIATE
Make a short and precise announcement to order the emergency evacuation.
Press the EVAC COMMAND pb .
ELT .............................................................................................CHECK EMITTING
If not, switch on the transmitter.
If evacuation not required:
CABIN CREW and PASSENGERS (PA).............................................................NOTIFY
Continued on the following page
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←A→
PRO-ABN-ENG P 5/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - FUEL REMAINING (Cont'd)
Ident.: PRO-ABN-ENG-X-00012313.0065001 / 17 MAR 17
If ditching anticipated:
For approach:
FOR LANDING : USE FLAP 3
SLATS AVAIL ONLY
MIN APPR SPEED : 150 kt
VAPP.................................................................................................................. DETERMINE
Gross Weight (1 000
kg)
VAPP
40
44
48
52
56
60
64
68
72
76
78
150
150
150
150
150
155
159
163
167
171
173
At a suitable altitude (not below 3 000 ft AGL):
KEEP LANDING GEAR UP
FOR FLARE: TARGET PITCH 11 ° & MIN V/S
Note:
Prefer ditching parallel to the swell. If that causes a strong crosswind, ditch
into the wind.
At 2 000 ft AGL:
CABIN CREW................................................................................. NOTIFY FOR DITCHING
DITCHING pb.....................................................................................................................ON
At 500 ft AGL:
BRACE FOR IMPACT................................................................................................ORDER
At touchdown:
ENG MASTERS............................................................................................................... OFF
APU MASTER SW........................................................................................................... OFF
After ditching:
ATC (VHF 1).............................................................................................................. NOTIFY
FIRE pb (ENGs & APU)................................................................................................PUSH
AGENTs (ENGs & APU).............................................................................................. DISCH
EVACUATION...........................................................................................................INITIATE
ELT ................................................................................................... CHECK EMITTING
If not, switch on the transmitter.
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PRO-ABN-ENG P 6/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - NO FUEL REMAINING
Applicable to: ALL
Ident.: PRO-ABN-ENG-Y-00012602.0108001 / 17 MAR 17
The flight crew must apply this paper procedure when required by the ENG DUAL FAILURE
procedure. If time permits, clear ECAM alerts, and check the ECAM STATUS page.
OPTIMUM SPEED............................................................................................ 220 kt / GREEN DOT
Initially, fly 220 kt, because the PFD may not display the correct green dot speed. Then fly the
green dot speed according to the following table:
Gross Weight
(1000 kg)
68
64
60
56
52
48
44
40
GREEN DOT SPEED WITH ALL ENGINES INOPERATIVE (KNOTS)
At or below
FL 300
FL 200
221
231
213
223
205
215
197
207
189
199
181
191
173
183
165
175
FL 400
241
233
225
217
209
201
193
185
AVERAGE GLIDING DISTANCE: 2.5 NM / 1000 FT (GREEN DOT NO WIND)
AVERAGE RATE OF DESCENT: 1600 FT/MIN
DETERMINE LANDING STRATEGY
VHF1/HF1 /ATC1....................................................................................................................USE
ATC..........................................................................................................................................NOTIFY
TRANSPONDER.........................................................................................................SELECT A7700
Notify air traffic control of the nature of the emergency, and state intentions. Switch to code A7700,
or transmit a distress message on one of the following frequencies: VHF frequency 121.5 MHz, HF
2 182 kHz or 8 364 kHz.
CREW OXY MASKS (above FL 100).............................................................................................ON
Cabin altitude will increase due to the lack of engine bleed: The EXCESS CAB ALT warning could
be triggered. Depending on the situation, to gain gliding distance, the flight crew may disregard the
ECAM emergency descent requirement, because passengers will be provided with oxygen for a
sufficient period of time.
PREPARE CABIN AND COCKPIT
‐ Loose equipment secured.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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Continued on the following page
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PRO-ABN-ENG P 7/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - NO FUEL REMAINING (Cont'd)
‐ Survival equipments prepared.
‐ Belts and shoulder harnesses locked.
SIGNS..............................................................................................................................................ON
COMMERCIAL...............................................................................................................................OFF
USE RUDDER WITH CARE
As hydraulic power is only available from the RAT, avoid large and rapid rudder deflection.
When below FL 150:
RAM AIR...................................................................................................................................ON
Switch ON the RAM AIR to ensure complete depressurization.
Ident.: PRO-ABN-ENG-Y-00012317.0001001 / 17 MAR 17
BARO REF.................................................................................................................................... SET
CREW MASKS/OXY SUPPLY (below FL 100)............................................................................ OFF
ELT (when conditions permit)................................................................................................. ON
Continued on the following page
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←B→
PRO-ABN-ENG P 8/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - NO FUEL REMAINING (Cont'd)
Ident.: PRO-ABN-ENG-Y-00012318.0065001 / 09 MAY 17
If forced landing anticipated:
AVERAGE GLIDING DISTANCE 1.2NM / 1000FT (CONF3, L/G DOWN, NO WIND)
For approach:
FOR LANDING : USE FLAP 3
SLATS AVAIL ONLY
MIN APPR SPEED : 150 kt
VAPP.................................................................................................................. DETERMINE
Gross Weight (1000
kg)
VAPP
40
44
48
52
56
60
64
68
72
76
78
150
150
150
150
150
155
159
163
167
171
173
At a suitable altitude (not below 3 000 ft AGL):
When in CONF 3 and VAPP :
GRAVITY GEAR EXTN handcrank............................................... PULL AND TURN
FLT CTL DIRECT LAW
MAN PITCH TRIM NOT AVAILABLE
When L/G downlocked :
L/G lever..........................................................................................................DOWN
APPROACH SPEED.................................................................................... ADJUST
ADJUST SPEED TO REACH LANDING FIELD
MAX SPEED : 200 kt
SPLRs.................................................................................................................ARM
MAX BRK PR : 1 000 PSI
At 2 000 ft AGL:
CABIN CREW.................................................................................. NOTIFY FOR LANDING
At 500 ft AGL:
BRACE FOR IMPACT................................................................................................ORDER
At touchdown:
ENG MASTERS............................................................................................................... OFF
BRAKES ON ACCU ONLY
Continued on the following page
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←B→
PRO-ABN-ENG P 9/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - NO FUEL REMAINING (Cont'd)
When aircraft stopped:
PARKING BRK...................................................................................................................ON
ATC.............................................................................................................................NOTIFY
If evacuation required:
EVACUATION.................................................................................................... INITIATE
Make a short and precise announcement to order the emergency evacuation.
Press the EVAC COMMAND pb .
ELT .............................................................................................CHECK EMITTING
If not, switch on the transmitter
If evacuation not required:
CABIN CREW and PASSENGERS (PA).............................................................NOTIFY
Continued on the following page
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←B→
PRO-ABN-ENG P 10/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG DUAL FAILURE - NO FUEL REMAINING (Cont'd)
Ident.: PRO-ABN-ENG-Y-00012319.0065001 / 17 MAR 17
If ditching anticipated:
For approach:
FOR LANDING : USE FLAP 3
SLATS AVAIL ONLY
MIN APPR SPEED : 150 kt
VAPP.................................................................................................................. DETERMINE
Gross Weight (1 000
kg)
VAPP
40
44
48
52
56
60
64
68
72
76
78
150
150
150
150
150
155
159
163
167
171
173
At a suitable altitude (not below 3 000 ft AGL):
KEEP LANDING GEAR UP
FOR FLARE: TARGET PITCH 11 ° & MIN V/S
Note:
Prefer ditching parallel to the swell. If that causes a strong crosswind, ditch
into the wind.
At 2 000 ft AGL:
CABIN CREW................................................................................. NOTIFY FOR DITCHING
DITCHING pb.....................................................................................................................ON
At 500 ft AGL:
BRACE FOR IMPACT................................................................................................ORDER
At touchdown:
ENG MASTERS............................................................................................................... OFF
After ditching:
ATC (VHF 1).............................................................................................................. NOTIFY
EVACUATION...........................................................................................................INITIATE
ELT ................................................................................................... CHECK EMITTING
If not, switch on the transmitter.
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PRO-ABN-ENG P 11/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG RELIGHT
IN FLIGHT
Ident.: PRO-ABN-ENG-00012594.0026001 / 17 MAR 17
Applicable to: ALL
Engine Relight Envelope
ENG MASTER (affected engine).................................................................................................. OFF
THR LEVER (affected engine)..........................................................................................Check IDLE
ENG MODE sel..............................................................................................................................IGN
X BLEED.................................................................................................................................... OPEN
Continued on the following page
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PRO-ABN-ENG P 12/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENG RELIGHT (Cont'd)
IN FLIGHT
If outside the windmilling start envelope, the FADEC will open the starter valve.
WING ANTI ICE (for starter assist)...............................................................................................OFF
ENG MASTER (affected engine).................................................................................................... ON
ENG PARAMETERS (N2, EGT)......................................................................................... MONITOR
Engine light up should be achieved within 30 s after fuel flow increases.
AUTOMATIC START ABORT NOT AVAIL
Be aware that, unlike the procedure for auto start on ground, the crew must take appropriate action
in case of an abnormal start.
Monitor N2. If uncertain about successful relight, move the thrust lever forward and check engine
response.
When idle reached (ENG AVAIL):
ENG MODE sel...................................................................................................................NORM
TCAS MODE sel ........................................................................................................ TA/RA
Check that the selector is at TA /RA since, if the ENG SHUT DOWN procedure (Refer to
PRO-ABN-ENG ENG 1(2) SHUT DOWN) has been applied, the TCAS mode selector may have
been set to the TA position.
X BLEED.............................................................................................................................. AUTO
Affected SYS................................................................................................................ RESTORE
If no relight:
ENG MASTER (affected engine)............................................................................................OFF
Wait 30 s before attempting a new start (to drain the engine).
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PRO-ABN-ENG P 13/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ENGINE TAILPIPE FIRE
Ident.: PRO-ABN-ENG-00017781.0001001 / 17 MAR 17
Applicable to: ALL
Internal engine fire may be encountered during engine start or engine shutdown.
Internal engine fire may be seen by the ground crew, or the EGT may fail to decrease after the
ENG MASTER lever is set to OFF.
CAUTION
External fire agents can cause severe corrosive damage. Consider the use of
external fire agents only if the following procedure does not stop engine tailpipe
fire.
ENG MASTER (affected engine) ................................................................................................. OFF
Note:
Do not press the engine fire pushbutton, since this would cut off the FADEC power supply,
which would prevent motoring sequence.
ENG MAN START pb (affected engine)....................................................................................... OFF
ESTABLISH AIR BLEED PRESS
Select the APU, or opposite BLEED, to motor the engine.
If APU BLEED is not available, and the opposite engine is shut down, connect external pneumatic
power (if readily available).
BEACON ........................................................................................................................................ ON
ENG MODE sel...................................................................................................................... CRANK
ENG MAN START pb (affected engine).........................................................................................ON
For aircraft equipped with IAE or PW6000 engines, the start valve automatically reopens, when N2
is below 10 %.
For aircraft equipped with CFM 56-5A/5B engines, the start valve automatically reopens, when N2
is below 20 %
For aircraft equipped with CFM LEAP-1A engines, the start valve automatically reopens, when N2
is below approximately 60 %
When fire stopped:
ENG MAN START pb (affected engine).................................................................................OFF
ENG MODE sel...................................................................................................................NORM
Maintenance action is due.
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PRO-ABN-ENG P 14/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] HIGH ENGINE VIBRATION
Ident.: PRO-ABN-ENG-00012294.0006001 / 17 MAR 17
Applicable to: ALL
The VIB advisory on ECAM (N1 ≥ 6 units, N2 ≥ 4.3 units) is mainly a guideline for the flight crew to
monitor engine parameters more closely.
The ECAM vibration advisory alone does not require engine shut down.
Note:
1. High engine vibration may be accompanied by cockpit and cabin smoke and/or the
smell of burning. This may be due only to compressor blade tip contact with associated
abradable seals.
2. High N1 vibration are generally accompanied by perceivable airframe vibrations. High
N2 vibration can occur without perceivable airframe vibrations.
ENG PARAMETERS .............................................................................................................. CHECK
Check engine parameters and especially EGT; crosscheck with other engine. Report in
maintenance log.
If icing suspected:
An increase of engine vibration in icing conditions with or without engine anti-ice may be due
to fan blades and/or spinner icing. Icing may be suspected if N1 vibration occurs without other
engine parameters variation.
A/THR .................................................................................................................................... OFF
THRUST (one engine at a time)........................................... IDLE THEN INCREASE N1 > 80 %
Reduce thrust to idle if flight conditions permit.
If ENG ANTI ICE is off, switch it ON at idle fan speed, one engine after the other with
approximately 30 s interval.
To shed ice, it may be necessary to perform several thrust variations between idle and a thrust
compatible with the flight phase. For efficient ice shedding, thrust should be increased to at
least 80% N1 if flight conditions permit.
After each thrust variation, vibrations should decrease, indicating the progress of the ice
shedding.
When the ice is shed, vibrations should return to normal and the flight crew can resume normal
engine operation.
If icing not suspected:
If above vibration advisory and flight conditions permit:
THRUST (affected engine).............................. REDUCE BELOW ADVISORY THRESHOLD
After landing: SHUT DOWN ENGINE WHEN POSSIBLE
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E
PRO-ABN-ENG P 15/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ON GROUND - NON ENG SHUTDOWN AFTER ENG MASTER OFF
Ident.: PRO-ABN-ENG-00020795.0001001 / 17 MAR 17
Applicable to: ALL
The normal procedure to shut down an engine is to set the ENG MASTER lever to OFF. In the case
where the engine does not shut down as expected, use the following procedure:
ECAM FUEL PAGE................................................................................................................SELECT
LP FUEL VALVE POSITION (affected engine)....................................................................... CHECK
If LP fuel valve closed (cross line amber):
NO CREW ACTION
If LP fuel valve open:
ENG FIRE pb-sw (affected engine)...................................................................................PRESS
Using the ENG FIRE pb-sw will force the LP fuel valve to close. The engine will shut down after
a time delay.
GROUND STAFF.................................................................................................................... NOTIFY
IN BOTH CASES, ENGINE WILL SHUT DOWN AFTER A TIME DELAY UP TO 2 MIN 30 S
The engine shuts down when the remaining fuel between the LP fuel valve and the nozzles is
burned. The time delay for engine shutdown depends on airport altitude and fuel recirculation
system operation.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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F
PRO-ABN-ENG P 16/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ONE ENGINE INOPERATIVE - CIRCLING APPROACH
Ident.: PRO-ABN-ENG-00010682.0004001 / 17 MAR 17
Applicable to: ALL
MAXIMUM WEIGHT FOR CIRCLING IN CONF 3 WITH GEAR DOWN (1000 KG)
AIRPORT ELEVATION (feet)
0
2 000
4 000
6 000
8 000
10 000
12 000
77
76
69
63
58
53
48
OAT
(°C)
0
5
10
15
20
25
30
35
40
45
50
55
77
76
69
63
58
53
48
77
76
69
63
58
53
48
77
77
77
77
74
71
69
67
64
76
76
75
72
70
67
65
63
69
69
69
68
66
63
61
63
58
63
58
63
58
63
58
63
56
59
53
53
53
53
51
48
48
48
48
14 000
45
45
45
45
45
45
If aircraft weight above maximum weight for circling in CONF 3 with gear down:
DELAY GEAR EXTENSION TO MAINTAIN LEVEL FLIGHT
The aircraft cannot maintain level flight, in CONF 3 and with the landing gear down.
FOR LANDING: USE FLAP 3
CONF 3 is preferred, to minimize a configuration change in short final.
GPWS LDG FLAP 3.................................................................................................................ON
Note:
‐ If circling below 750 ft RA, “L/G GEAR NOT DOWN” alert will trigger. The pilot can
cancel the aural warning by pressing the EMER CANC pb.
‐ If the landing gear is not downlocked at 500 ft RA , GPWS "TOO LOW GEAR” aural
alert will trigger.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
PRO-ABN-ENG P 17/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
[QRH] ONE ENGINE INOPERATIVE - STRAIGHT-IN APPROACH
Ident.: PRO-ABN-ENG-00010681.0001001 / 17 MAR 17
Applicable to: ALL
If NO level off expected during final approach:
DELAY CONF FULL UNTILL ESTABLISHED ON FINAL DESCENT
If level off expected during final approach:
FOR LANDING: USE CONF 3
ENG 1(2) BLEED STATUS FAULT
(IN FLIGHT)
Applicable to: ALL
Ident.: PRO-ABN-ENG-W-00017963.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the status of one of the following valves is not received by the FADEC
active channel:
‐
‐
‐
‐
Bleed valves, or
Pack valves, or
Wing and engine anti ice valves, or
Cross-bleed valve.
Flight Phase Inhibition:
Continued on the following page
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FCOM
H to I →
PRO-ABN-ENG P 18/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) BLEED STATUS FAULT (Cont'd)
(IN FLIGHT)
Ident.: PRO-ABN-ENG-W-00018707.0001001 / 21 MAR 16
If ENG ANTI ICE on:
ENG MODE SEL..................................................................................................................... IGN
Ident.: PRO-ABN-ENG-W-00012303.0001001 / 17 AUG 10
STATUS
ENG 1(2) HI GND IDLE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I
PRO-ABN-ENG P 19/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) BLEED STATUS FAULT
(ON GROUND)
Applicable to: ALL
Ident.: PRO-ABN-ENG-V-00017965.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the status of one of the following valves is not received by the FADEC
active channel:
‐
‐
‐
‐
Bleed valves, or
Pack valves, or
Wing and engine anti ice valves, or
Cross-bleed valve.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J→
PRO-ABN-ENG P 20/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) BLEED STATUS FAULT (Cont'd)
(ON GROUND)
Ident.: PRO-ABN-ENG-V-00018708.0001001 / 21 MAR 16
L2
HI GND IDLE
FADEC increases minimum idle as if valves were opened.
L1
If ENG ANTI ICE on:
ENG MODE SEL..................................................................................................................... IGN
L2
When ENG anti ice is on, there is no automatic selection of continuous relight since FADEC
does not know position of engine anti ice valves position.
L1
BEFORE T.O.:
PACK (ASSOCIATED SIDE).................................................................................................. OFF
L2
Associated pack must be closed to reduce risk of excessive EGT.
Ident.: PRO-ABN-ENG-V-00012301.0001001 / 17 AUG 10
STATUS
ENG 1(2) HI GND IDLE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←J
PRO-ABN-ENG P 21/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG COMPRESSOR VANE
Applicable to: ALL
Ident.: PRO-ABN-ENG-CY-00017907.0001001 / 31 AUG 17
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a loss of the redundancy (i.e. one channel is detected faulty)
of the compressor vane (i.e. VBV, VSV) control system on both engines. The control of the
compressor vane is still fully operative on both engines.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CY-00017757.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K
PRO-ABN-ENG P 22/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) COMPRESSOR VANE
Applicable to: ALL
Ident.: PRO-ABN-ENG-N-00017966.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when either Variable Bleed Valve (VBV ) or Variable Stator Vane (VSV) is
failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-N-00017655.0003001 / 21 MAR 17
On ground:
THR LEVERS (AFFECTED).................................................................................................. IDLE
ENG MASTER (AFFECTED)..................................................................................................OFF
Depending on the type of failure, one of the following two messages is displayed:
AVOID RAPID THR CHANGES or
If the A/THR is engaged, adjust the thrust levers to align the thrust lever commands with actual N1
and disconnect A/THR.
ENG (AFFECTED) SLOW RESPONSE
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
L→
PRO-ABN-ENG P 23/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) COMPRESSOR VANE (Cont'd)
Ident.: PRO-ABN-ENG-N-00012155.0001001 / 17 AUG 10
STATUS
AVOID RAPID THR CHANGES
ENG (affected) SLOW RESPONSE
ENG 1(2) CTL VALVE FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-Q-00017967.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The Burner Staging Valve (BSV) is failed, or
‐ The HP Turbine Clearance (HPTC) system is failed, or
‐ The Rotor Active Clearance Control (RACC) system is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-Q-00018709.0001001 / 21 MAR 16
L2
MAX N2........................................................................................................................................96 %
Retard associated thrust lever to limit N2 to 96 %.
Continued on the following page
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FCOM
← L to M →
PRO-ABN-ENG P 24/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) CTL VALVE FAULT (Cont'd)
Ident.: PRO-ABN-ENG-Q-00012233.0001001 / 17 AUG 10
STATUS
MAX ENG (AFFECTED) N2............................................ 96 %
ENG DUAL FAILURE
Applicable to: ALL
Ident.: PRO-ABN-ENG-S-00017909.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the two engines are failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← M to N →
PRO-ABN-ENG P 25/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG DUAL FAILURE (Cont'd)
Ident.: PRO-ABN-ENG-S-00012282.0370001 / 21 MAR 17
L2
This warning inhibits the ELEC EMER CONFIG warning, and provides the flight crew with the
immediate actions to take in the case of a dual engine failure. This procedure then directs the flight
crew to apply the applicable QRH procedure, depending on if there is fuel or not.
When applying the ENG DUAL FAILURE QRH procedure:
‐ If one or more engines are recovered, apply the corresponding ECAM procedure instead
‐ If no engines are recovered, continue to apply the ENG DUAL FAILURE QRH procedure. If time
permits, clear ECAM alerts, and check the ECAM STATUS page.
LAND ASAP
L1
EMER ELEC PWR (IF EMER GEN NOT IN LINE)...............................................................MAN ON
Pressing EMER ELEC PWR MAN ON pb allows extension of RAT and emergency generator
coupling.
L1 THR LEVERS............................................................................................................................... IDLE
FAC 1.......................................................................................................................... OFF THEN ON
L2 Resetting FAC 1 enables the recovery of characteristics speed displayed on the PFD.
Resetting FAC 1 also enables rudder trim recovery, even if no indication is available.
When the hydraulic power is lost, the right aileron is lost, and is in the upfloat position.
Rudder trim may be used to compensate for this upfloating aileron.
L2
L1
IF NO FUEL:
OPT SPD.....................................................................................................220 KT/GREEN DOT
L2
If there is no fuel remaining, the optimum speed is the green dot speed.
Initially fly 220 kt then refer to the QRH procedure to get the accurate green dot speed.
L1
ENG/NO FUEL PROC........................................................................................................APPLY
L2
Refer to procedure.
L1
IF FUEL REMAINS:
ENG MODE SEL..................................................................................................................... IGN
OPT RELIGHT SPD...........................................................................................................300 KT
L2
If there is fuel remaining, the optimum speed is the optimum relight speed.
The ECAM provides reference to an envelope speed. In case of speed indication failure
(volcanic ash), pitch attitude for optimum relight is provided in the QRH procedure.
L1
ENG/FUEL PROC.............................................................................................................. APPLY
L2
Refer to procedure.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←N→
PRO-ABN-ENG P 26/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG DUAL FAILURE (Cont'd)
Ident.: PRO-ABN-ENG-S-00012283.0044001 / 21 MAR 16
L12
STATUS
MIN RAT SPEED......................................................... 140 KT
MAX SPEED ............................................................. 320/0.77
MAX BRK PR.......................................................... 1000 PSI
MANEUVER WITH CARE
FUEL GRVTY FEED
AVOID NEGATIVE G FACTOR
INOP SYS
See below
APPR PROC
IF HYD NOT RECOVERED:
FOR LDG......................................................USE FLAP 3
WHEN CONF 3 AND VAPP:
L/G .............................................................GRVTY EXTN
(Refer to PRO-ABN-LG [QRH] L/G GRAVITY
EXTENSION). Being stabilized at VAPP before selecting
the gear down enables the aircraft to be trimmed for
approach.
APPR SPD..................................................VREF +25 KT
Approach speed must be increased, due to the loss of
flaps.
LDG DIST PROC......................................................... APPLY
ALTN LAW: PROT LOST
WHEN L/G DN: DIRECT LAW
(1)
See
BRK Y ACCU PR ONLY
(2)
See
SLATS SLOW
INOP SYS
G+Y HYD
F/CTL PROT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
STABILIZER
Continued on the following page
←N→
PRO-ABN-ENG P 27/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG DUAL FAILURE (Cont'd)
R AIL
IR 2+3
ELAC 2
YAW DAMPER
A/THR
N/W. STEER
L/G RETRACT
(1)
(2)
REVERSER 1+2
RA 1+2
SEC 2+3
A/CALL OUT
FUEL PUMPS
AUTO BRK
CAB PR 1+2
ADR 2+3
SPLR 1+2+4+5
FLAPS
AP 1+2
ANTI SKID
CAT 2
PACK 1+2
At landing gear extension, control reverts to direct law in pitch as well as in roll (Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW).
7 full brake applications are available.
ENG 1(2) EIU FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-B-00017970.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the data bus between the EIU and ECU is failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← N to O →
PRO-ABN-ENG P 28/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) EIU FAULT (Cont'd)
Ident.: PRO-ABN-ENG-B-00017658.0002001 / 21 MAR 17
Crew awareness.
L2
The following consequences affect the aircraft when this alert is triggered:
‐ Affected engine start is lost
‐ Autothrust control is lost
‐ Thrust reverser on the affected engine is lost
‐ When idle is selected, only approach idle is available
‐ Bleed corrections on N1 limit are lost (Refer to PRO-ABN-ENG ENG 1(2) BLEED STATUS
FAULT (In Flight)).
Ident.: PRO-ABN-ENG-B-00017659.0001001 / 21 MAR 16
L12
STATUS
INOP SYS
ENG 1(2) APPR IDLE ONLY
Minimum idle is lost.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A/THR
REVERSER 1(2)
ENG 1(2) START
←O
PRO-ABN-ENG P 29/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FADEC A(B) FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-AZ-00017972.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the associated FADEC channel is lost.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-AZ-00017661.0001001 / 31 AUG 17
Crew awareness.
For aircraft equipped with CFM engines:
L2
Note:
Some cases of spurious FADEC fault have been experienced at engine start on
ground.
The caution can be considered as spurious, if it disappears after application of the
following procedure:
‐ Set the master sw to OFF, and wait until N2 speed goes below 5 % (If N2 indication
is not available, wait 2 minutes before going to next step).
‐ Pull and reset the C/B ’s of the affected ECU electrical supply (A04 or A05 on 49
VU or R41 or Q40 on 121 VU).
‐ Wait 10 s for the ECU power-up sequence, and restart the engine.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
P
PRO-ABN-ENG P 30/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FADEC ALTERNATOR
Applicable to: ALL
Ident.: PRO-ABN-ENG-BA-00017974.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the electrical auto supply for the FADEC system is lost.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-BA-00017662.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Q
PRO-ABN-ENG P 31/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FADEC FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-BC-00017975.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both FADEC channels are lost.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
R→
PRO-ABN-ENG P 32/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FADEC FAULT (Cont'd)
Ident.: PRO-ABN-ENG-BC-00017663.0005001 / 21 MAR 17
On ground:
THR LVR (AFFECTED) NOT ABOVE IDLE
ENG (AFFECTED) PARAMETERS...................................................................................CHECK
L2
Due to the fact that engine indications are lost, other system pages such as HYD SD page,
ELEC SD page or BLEED SD page must be used to check engine status.
L1
IF ABN ENG OPERATION:
ENG MASTER (AFFECTED)........................................................................................... OFF
In flight:
THR LEVER (AFFECTED).................................................................................................... IDLE
ENG (AFFECTED) PARAMETERS...................................................................................CHECK
L2
Due to the fact that engine indications are lost, other system pages such as HYD SD page,
ELEC SD page or BLEED SD page must be used to check engine status.
L1
IF ABN ENG OPERATION:
ENG MASTER (AFFECTED)........................................................................................... OFF
L12
ASSOCIATED PROCEDURES
ENG 1(2) SHUT DOWN
(Refer to PRO-ABN-ENG ENG 1(2) SHUT DOWN).
Ident.: PRO-ABN-ENG-BC-00019553.0001001 / 13 MAY 16
STATUS
On ground:
THR LVR 1(2) NOT ABOVE IDLE
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FCOM
←R
PRO-ABN-ENG P 33/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FADEC HI TEMP
Applicable to: ALL
Ident.: PRO-ABN-ENG-BD-00017976.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when high temperature is detected by one or both channels.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
S→
PRO-ABN-ENG P 34/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FADEC HI TEMP (Cont'd)
Ident.: PRO-ABN-ENG-BD-00017664.0004001 / 21 MAR 17
If the ECU TEMP is above 105 °C:
FADEC OVHT
L2
Reducing engine power should decrease temperature in the ECU area.
If overheating is severe enough, ECU failure could result in a significant loss of engine
functions.
L1
On the ground:
THR LEVER (AFFECTED).................................................................................................... IDLE
ENG MASTER (ASSOCIATED ENGINE)...............................................................................OFF
ENG MODE SEL.................................................................................................................NORM
FADEC GND PWR.................................................................................................. CHECK OFF
In flight:
ENG (AFFECTED) PARAMETERS...................................................................................CHECK
IF ABN ENG OPERATION:
THR LEVER (AFFECTED)..............................................................................................IDLE
ENG MASTER (ASSOCIATED ENGINE)........................................................................ OFF
L12
ASSOCIATED PROCEDURES
ENG 1(2) SHUT DOWN
(Refer to PRO-ABN-ENG ENG 1(2) SHUT DOWN).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←S
PRO-ABN-ENG P 35/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FAIL
Applicable to: ALL
Ident.: PRO-ABN-ENG-BJ-00017982.0002001 / 06 JUN 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the engine core speed is below idle, with the ENG MASTER lever set
to ON, and ENG FIRE pb not pushed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
T→
PRO-ABN-ENG P 36/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FAIL (Cont'd)
Ident.: PRO-ABN-ENG-BJ-00017667.0003001 / 21 MAR 17
L2
An engine flame-out may be recognized by a rapid decrease in EGT , N2 , FF , followed by
decrease in N1 for CFM engines, or EPR for IAE engines.
Engine damage may be accompanied by:
‐ Loud noise,
‐ Significant increase in aircraft vibrations and/or buffeting,
‐ Repeated or uncontrollable engine stalls,
‐ Associated abnormal indications such as hydraulic fluid loss, or no N2 indication.
LAND ASAP
L1
Before takeoff or after landing:
THR LEVER (AFFECTED ENGINE)..................................................................................... IDLE
ENG MASTER (AFFECTED ENGINE)...................................................................................OFF
IF DAMAGE:
ENG FIRE P/B (AFFECTED ENGINE)......................................................................... PUSH
AGENT 1...................................................................................................................... DISCH
IF NO DAMAGE:
L2
L1
L2
For CFM engines, if conditions permit, do not restart the engine. A new engine start would
erase FADEC troubleshooting data.
ENG (AFFECTED) RELIGHT...............................................................................CONSIDER
If no damage, a new start sequence may be initiated.
L12
ASSOCIATED PROCEDURES
ENG 1(2) SHUT DOWN
Apply the ENG SHUT DOWN procedure (Refer to PRO-ABN-ENG ENG 1(2) SHUT
DOWN), if damage or if engine relight is unsuccessful.
L1
In flight:
ENG MODE SEL..................................................................................................................... IGN
L2
Selection of continuous ignition confirms the immediate relight attempt made by the FADEC.
L1
THR LEVER (AFFECTED ENGINE)..................................................................................... IDLE
Continued on the following page
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←T→
PRO-ABN-ENG P 37/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FAIL (Cont'd)
L2
Note:
L1
IF NO ENG RELIGHT AFTER 30 S:
The 30 s countdown starts as soon as the ENG 1(2) FAIL alert is triggered.
L2
L1
L12
In case of GPWS (EGPWS ) alerts, reduce speed with care below VLS with flaps
extended (at light weights VMCA may be reached before αMax) when applying the
GPWS (EGPWS ) procedure.
ENG MASTER (AFFECTED ENGINE)............................................................................ OFF
IF DAMAGE:
ENG FIRE P/B (AFFECTED ENGINE)...................................................................PUSH
AGENT 1 (AFTER 10 SECONDS IN FLIGHT)..................................................... DISCH
ASSOCIATED PROCEDURES
L2
L1
L2
ENG 1(2) SHUT DOWN
Apply the ENG SHUT DOWN procedure (Refer to PRO-ABN-ENG ENG 1(2)
SHUT DOWN), if damage or if engine relight is unsuccessful.
If high vibration occurs and continues after engine shutdown, reduce airspeed and
descent to a safe altitude.
Attempt to determine and use a practical airspeed and altitude for minimum
vibrations.
IF NO DAMAGE:
ENG (AFFECTED) RELIGHT........................................................................ CONSIDER
Apply ENG RELIGHT (in flight) procedure (Refer to PRO-ABN-ENG [QRH] ENG
RELIGHT IN FLIGHT).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←T
PRO-ABN-ENG P 38/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FIRE
(IN FLIGHT)
Applicable to: ALL
Ident.: PRO-ABN-ENG-DQ-00017401.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ Fire is detected by both loops, or
‐ Fire is detected by one loop when the other loop is faulty, or
‐ A rupture occurs in both loops within 5 s.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
U→
PRO-ABN-ENG P 39/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FIRE (Cont'd)
(IN FLIGHT)
Ident.: PRO-ABN-ENG-DQ-00018190.0002001 / 21 MAR 17
LAND ASAP
THR LEVER (AFFECTED)...........................................................................................................IDLE
ENG MASTER (AFFECTED)........................................................................................................ OFF
L2 LP and HP valves close.
L1 ENG FIRE P/B (AFFECTED)..................................................................................................... PUSH
L2
When pushed:
‐ Aural warning stops
‐ The light remains on, until the fire is extinguished, regardless of the position of the ENG FIRE
pb-sw
‐ FADEC is no longer supplied.
AGENT 1 AFTER 10 S............................................................................................................. DISCH
The 10 s delay allows N1 to decrease, reducing nacelle ventilation, and thereby increasing the
effect of the agent.
Automatic countdown on the ECAM.
L1 ATC..........................................................................................................................................NOTIFY
L2 Notify ATC of the nature of the emergency, and state intentions
L1
L2
L1
IF FIRE AFTER 30 S:
AGENT 2.............................................................................................................................DISCH
L2
Discharge the second agent, if the fire warning remains 30 s after the discharge of the first
agent.
L12
ASSOCIATED PROCEDURES
ENG 1(2) SHUTDOWN
Do not attempt to restart the engine.
For the ENG SHUTDOWN procedure, see the ENG section (Refer to PRO-ABN-ENG ENG 1(2)
SHUT DOWN).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←U
PRO-ABN-ENG P 40/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FIRE
(ON GROUND)
Applicable to: ALL
Ident.: PRO-ABN-ENG-DR-00018553.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ Fire is detected by both loops, or
‐ Fire is detected by one loop when the other loop is faulty, or
‐ A rupture occurs in both loops within 5 s.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
V→
PRO-ABN-ENG P 41/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FIRE (Cont'd)
(ON GROUND)
Ident.: PRO-ABN-ENG-DR-00018192.0004001 / 14 FEB 17
L2
THR LEVERS............................................................................................................................... IDLE
Full reverse may be used to stop the aircraft.
L1
WHEN A/C IS STOPPED:
PARKING BRK......................................................................................................................... ON
ATC (VHF 1).....................................................................................................................NOTIFY
L2
Notify ATC of the nature of the emergency, and state intensions.
Only VHF 1 is available on batteries.
L1
CABIN CREW (PA)............................................................................................................ ALERT
ENG MASTER (AFFECTED)..................................................................................................OFF
L2
Associated LP and HP valves close.
L1
ENG FIRE P/B (AFFECTED)...............................................................................................PUSH
L2
When pushed:
‐ Aural warning stops
‐ The light remains on, until the fire is extinguished, regardless of the position of the ENG FIRE
pb-sw
‐ FADEC is no longer supplied.
L1
AGENT 1+2.........................................................................................................................DISCH
EMER EVAC PROC...........................................................................................................APPLY
Refer to PRO-ABN-MISC [QRH] EMER EVAC or Refer to QRH/ABN-25 EMER EVAC
L2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←V
PRO-ABN-ENG P 42/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FIRE DET FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-DO-00020838.0001001 / 17 MAR 17
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ Both loops are inoperative, or
‐ Fire Detector Unit is inoperative.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-DO-00020837.0001001 / 17 MAR 17
Crew awareness.
Ident.: PRO-ABN-ENG-DO-00020839.0001001 / 17 MAR 17
STATUS
INOP SYS
FIRE DET 1(2)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
W
PRO-ABN-ENG P 43/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FIRE LOOP A(B) FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-DP-00020841.0001001 / 17 MAR 17
ANNUNCIATIONS
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-DP-00020840.0001001 / 17 MAR 17
L2
Crew awareness.
Ident.: PRO-ABN-ENG-DP-00020842.0001001 / 17 MAR 17
STATUS
INOP SYS
ENG 1(2) LOOP A(B)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
X
PRO-ABN-ENG P 44/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FUEL CTL FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-O-00017983.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The Fuel Metering Valve (FMV) position is failed, or
‐ The FMV command is failed, or
‐ The FMV position feedback is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-O-00017679.0003001 / 21 MAR 16
On ground:
THR LEVER (AFFECTED).................................................................................................... IDLE
ENG MASTER (AFFECTED)..................................................................................................OFF
AVOID RAPID THR CHANGES, or
ENG (AFFECTED) SLOW RESPONSE
L2
Depending on the type of failure, one of the above two messages is displayed.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Y→
PRO-ABN-ENG P 45/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FUEL CTL FAULT (Cont'd)
Ident.: PRO-ABN-ENG-O-00017681.0001001 / 21 MAR 16
STATUS
AVOID RAPID THR CHANGES or
ENG (affected) SLOW RESPONSE
ENG 1(2) FUEL FILTER CLOG
Applicable to: ALL
Ident.: PRO-ABN-ENG-BK-00017984.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the fuel filter is clogged.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-BK-00012068.0001001 / 18 AUG 14
Crew awareness.
L2
Maintenance action is due.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← Y to Z
PRO-ABN-ENG P 46/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) FUEL RETURN VALVE
Applicable to: ALL
Ident.: PRO-ABN-ENG-BP-00017986.0001001 / 13 MAY 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the fuel return valve is failed in closed, or in open position.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-BP-00012277.0001001 / 25 FEB 14
L2
L1
L2
L1
VALVE NOT OPEN
The valve is failed closed.
Crew awareness.
VALVE NOT CLOSED
The valve is failed open.
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AA
PRO-ABN-ENG P 47/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) HP FUEL VALVE
Applicable to: ALL
Ident.: PRO-ABN-ENG-BY-00017955.0001001 / 13 MAY 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when HP fuel valve is failed in closed or open position.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-BY-00012096.0001001 / 13 MAY 16
HP fuel valve failed closed, and associated engine below idle:
HP FUEL VALVE NOT OPEN
On the ground:
MAN START (IF MAN START PERFORMED)................................................................OFF
ENG MASTER (AFFECTED)........................................................................................... OFF
HP fuel valve failed open, and associated engine below idle
or
HP fuel valve failed closed, and associated engine at or above idle:
HP FUEL POS SWT FAULT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AB
PRO-ABN-ENG P 48/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) IGN FAULT (IGN A OR B FAULT)
Applicable to: ALL
Ident.: PRO-ABN-ENG-J-00017956.0002001 / 20 APR 17
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when ignition circuit A or B is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-J-00012134.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-ENG-J-00012136.0001001 / 17 AUG 10
STATUS
INOP SYS
ENG 1(2) IGN A (B)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AC
PRO-ABN-ENG P 49/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) IGN FAULT (IGN A+B FAULT)
Applicable to: ALL
Ident.: PRO-ABN-ENG-K-00017957.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both ignition circuits are failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-K-00012139.0001001 / 12 JAN 11
AVOID ADVERSE CONDITIONS
Ident.: PRO-ABN-ENG-K-00012141.0001001 / 12 JAN 11
STATUS
INOP SYS
ENG 1(2) IGN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AD
PRO-ABN-ENG P 50/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) LOW N1 (ON GROUND)
Applicable to: ALL
Ident.: PRO-ABN-ENG-CA-00017958.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when N1 rotation is failed during start.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CA-00012101.0004001 / 16 NOV 11
L2
No N1 rotation during start.
L1
IF CONFIRMED:
THR LEVER (AFFECTED).................................................................................................... IDLE
ENG MASTER (AFFECTED)..................................................................................................OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AE
PRO-ABN-ENG P 51/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) N1 OR N2 OR EGT OR FF DISCREPANCY
Applicable to: ALL
Ident.: PRO-ABN-ENG-CC-00017959.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when a discrepancy between real and displayed values is detected.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CC-00017696.0001001 / 21 MAR 16
L2
The upper ECAM upper displays a CHECK (or CHK) message below the affected indication.
Normal indication may be recovered by switching from DMC 1 to DMC 3.
If unsuccessful, and if both thrust levers are at the same position, crosscheck with the opposite
parameter.
L1
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AF
PRO-ABN-ENG P 52/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) N1/N2/EGT OVER LIMIT
Applicable to: ALL
Ident.: PRO-ABN-ENG-CD-00018006.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ N1 is above 104 %, or
‐ N2 is above 105 %, or
‐ EGT is above 725 °C during start, or above 950 °C when the thrust levers are at TOGA or
FLX/MCT position, or 915 °C in the other cases.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AG →
PRO-ABN-ENG P 53/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) N1/N2/EGT OVER LIMIT (Cont'd)
Ident.: PRO-ABN-ENG-CD-00012079.0013001 / 21 MAR 17
Max pointer indication:
EGT between 915 °C and 950 °C (except during takeoff, alpha floor activation, or reverse
selected), or EGT between 950 °C and 970 °C, or
N1 between 104.0 % and 105.8 % or
N2 between 105.0 % and 105.8 %
THR LEVER (OF AFFECTED ENGINE)................................................................ BELOW LIMIT
Normal operation may be resumed and maintained until next landing. Report in maintenance
log.
L2
L1
L2
L1
Max pointer indication:
L2
L1
L2
EGT above 970 °C or
N1 above 105.8 % or
N2 above 105.8 %
THR LEVER (OF AFFECTED ENGINE)............................................................................... IDLE
ENG MASTER (OF AFFECTED ENGINE)............................................................................ OFF
If conditions do not permit engine shutdown land ASAP using the minimum thrust required to
sustain safe flight.
L12
ASSOCIATED PROCEDURES
ENG 1(2) SHUT DOWN
Apply the ENG SHUT DOWN procedure (Refer to PRO-ABN-ENG ENG 1(2) SHUT
DOWN).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AG
PRO-ABN-ENG P 54/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) OIL FILTER CLOG
Applicable to: ALL
Ident.: PRO-ABN-ENG-CF-00017964.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the oil filter is clogged.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CF-00012078.0003001 / 18 AUG 14
Crew awareness.
L2
Maintenance action is due, except if the caution is temporarily displayed during cold engine start
with engine oil temperature lower than 40 °C.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AH
PRO-ABN-ENG P 55/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) OIL HI TEMP
Applicable to: ALL
Ident.: PRO-ABN-ENG-CH-00017969.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
This alert triggers when the oil temperature is:
‐ Between 140 °C and 155 °C for more than 15 min, or
‐ Above 155 °C.
L2
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CH-00017822.0002001 / 21 MAR 17
THR LEVER (AFFECTED ENGINE)............................................................................................ IDLE
ENG MASTER (AFFECTED ENGINE)......................................................................................... OFF
L2 For aircraft equipped with IAE or PW6000 engines, operation above the maximum temperature
require engine shutdown.
L12
ASSOCIATED PROCEDURES
ENG 1 (2) SHUT DOWN
Apply the ENG SHUT DOWN procedure (Refer to PRO-ABN-ENG ENG 1(2) SHUT
DOWN).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AI
PRO-ABN-ENG P 56/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) OIL LO PR
Applicable to: ALL
Ident.: PRO-ABN-ENG-CI-00018002.0006001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
This alert triggers when oil pressure is below 13 PSI.
L2
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CI-00018796.0001001 / 21 MAR 17
L2
L1
Check oil pressure indication on ENG SD page.
THR LEVER (OF AFFECTED ENGINE)......................................................................................IDLE
ENG MASTER (OF AFFECTED ENGINE)................................................................................... OFF
L12
ASSOCIATED PROCEDURES
ENG 1(2) SHUT DOWN
Carry out ENG SHUT DOWN procedure (Refer to PRO-ABN-ENG ENG 1(2) SHUT
DOWN).
Note:
If oil pressure is low (< 13 PSI ) is indicated only on ENG SD page (red
indication) without the ENG OIL LO PR warning, it can be assumed, that the oil
pressure transducer is faulty. Flight crew may continue engine operation while
monitoring other engine parameters.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AJ
PRO-ABN-ENG P 57/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) ONE TLA FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-CM-00017977.0001001 / 21 MAR 16
ANNUNCIATIONS
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CM-00012144.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AK
PRO-ABN-ENG P 58/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) OVSPD PROT FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-CN-00017980.0003001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
This alert triggers when the overspeed protection is lost.
L2
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CN-00012166.0001001 / 25 FEB 14
Crew awareness.
L12
Note:
If the warning appears during engine start, shut down the engine. Restart the engine. If
the warning still appears, maintenance action is due.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AL
PRO-ABN-ENG P 59/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) PROBES FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-CO-00017981.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when T12, PO or PT2 data are unavailable on both channels.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CO-00018734.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AM
PRO-ABN-ENG P 60/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) REV ISOL FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-CP-00017989.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the thrust reverser shut off valve is failed in open position.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CP-00018735.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AN
PRO-ABN-ENG P 61/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) REV PRESSURIZED
Applicable to: ALL
Ident.: PRO-ABN-ENG-CR-00017992.0001001 / 13 MAY 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when thrust reverser system is pressurized while:
‐ For CFM engines: The reverser doors are stowed and locked, or
‐ For IAE and PW engines: There is no reverse deployment order.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CR-00017702.0002001 / 21 MAR 16
In flight:
THR LEVER 1(2)................................................................................................................... IDLE
L2
If flight conditions permit, reduce the thrust of the affected engine to IDLE as a precautionary
measure.
L1
On ground:
THR LVR 1(2) NOT ABOVE IDLE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AO
PRO-ABN-ENG P 62/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG REV SET
Applicable to: ALL
Ident.: PRO-ABN-ENG-DA-00017905.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the reverse thrust is selected in flight.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-DA-00017776.0001001 / 21 MAR 16
THR LEVER (AFFECTED ENGINE)................................................................................... FWD THR
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AP
PRO-ABN-ENG P 63/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) REV SWITCH FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-CS-00017870.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the reverser permission switch is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CS-00012098.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AQ
PRO-ABN-ENG P 64/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) REVERSE UNLOCKED
Applicable to: ALL
Ident.: PRO-ABN-ENG-CT-00017871.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one or more reverser doors are not locked in stowed position in flight,
or on ground with no deploy order.
Flight Phase Inhibition:
Note:
(a) Alert not inhibited in the flight phases 4 and 5, if the engine thrust is automatically set
to idle.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AR →
PRO-ABN-ENG P 65/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) REVERSE UNLOCKED (Cont'd)
Ident.: PRO-ABN-ENG-CT-00012084.0007001 / 21 MAR 17
L2
One or more reverser doors are not stowed.
If N1 is above 70 %, the auto-restow function is inhibited in flight and on ground.
L1
On ground:
ENG 1(2) AT IDLE
L2
Only displayed, if the FADEC automatically sets the engine at idle (i.e. when 4 reverser doors
are not stowed, or 1, 2, or 3 reverser doors are not stowed with the reverser pressurized).
L1
THR LEVER (AFFECTED ENGINE)..................................................................................... IDLE
ENG MASTER (AFFECTED ENGINE)...................................................................................OFF
In flight:
L2
L1
L2
L1
LAND ASAP
ENG 1(2) AT IDLE
Only displayed, if the engine is automatically set at idle.
THR LEVER (AFFECTED ENGINE)..................................................................................... IDLE
MAX SPEED...................................................................................................................... 300/.78
IF BUFFET:
The warning alone, without buffet or vibration, may be a false warning.
MAX SPEED .............................................................................................................. 240 KT
ENG MASTER (AFFECTED ENGINE)............................................................................ OFF
If reverser is actually deployed:
RUD TRIM .....................................................................................................FULL R (L)
CONTROL HDG WITH ROLL
L12
ASSOCIATED PROCEDURES
ENG 1(2) SHUT DOWN
Apply the ENG SHUT DOWN procedure (Refer to PRO-ABN-ENG ENG 1(2) SHUT
DOWN).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AR
PRO-ABN-ENG P 66/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) REVERSER FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-A-00017872.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the thrust reverser on one engine is failed (due to system components
or inputs).
Flight Phase Inhibition:
Note:
(a) Alert not inhibited in the flight phases 3, 4, 5, if engine thrust is automatically set to
idle.
Ident.: PRO-ABN-ENG-A-00017703.0003001 / 21 MAR 16
If reverser position fault with reverser pressurized:
L2
L1
L2
LAND ASAP
ENG 1(2) AT IDLE
Thrust of the affected engine is locked at idle.
THR LEVER 1(2)................................................................................................................... IDLE
Set thrust lever of affected engine at idle.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AS →
PRO-ABN-ENG P 67/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) REVERSER FAULT (Cont'd)
Ident.: PRO-ABN-ENG-A-00012070.0001001 / 17 AUG 10
STATUS
INOP SYS
REVERSER 1(2)
ENG 1(2) SENSOR FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-R-00017873.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when PS3 or T25 or T3 or N1 or N2 data is unavailable on both channels.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AS to AT →
PRO-ABN-ENG P 68/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) SENSOR FAULT (Cont'd)
Ident.: PRO-ABN-ENG-R-00012235.0003001 / 16 NOV 11
L2
PS3, T25, T3, N1 , N2 data not available on both ECU channels.
L1
On ground:
THR LEVER (AFFECTED).................................................................................................... IDLE
ENG MASTER (AFFECTED)..................................................................................................OFF
In flight:
AVOID RAPID THR CHANGES.
Ident.: PRO-ABN-ENG-R-00017707.0001001 / 21 MAR 16
STATUS
AVOID RAPID THR CHANGES.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AT
PRO-ABN-ENG P 69/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) SHUT DOWN
Applicable to: ALL
Ident.: PRO-ABN-ENG-I-00017874.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when ENG master is at off in phases 3 to 8, or ENG FIRE pb is pushed in
phases 1, 2, 9 and 10.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AU →
PRO-ABN-ENG P 70/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) SHUT DOWN (Cont'd)
Ident.: PRO-ABN-ENG-I-00017837.0006001 / 20 MAR 17
LAND ASAP
If wing anti-ice ON:
If Elec Emer Config:
PACK 1.............................................................................................................................OFF
L2
In Elec Emer config, only Pack 1 pb-sw can be set to off.
L1
L2
L1
L2
L1
L2
L1
If not Elec Emer Config:
PACK (AFFECTED SIDE) .............................................................................................. OFF
One pack must be closed when wing anti-ice is in use due to precooler performance.
If ENG FIRE pb not pushed:
X BLEED (IF ENG FIRE PB NOT PUSHED)............................................................... OPEN
X BLEED selector must be opened to have symmetrical wing anti-icing.
ENG MODE SEL............................................................................................................................IGN
Continuous ignition is selected, in order to protect the remaining engine.
IF NO FUEL LEAK:
IMBALANCE..................................................................................................................MONITOR
TCAS MODE SEL ....................................................................................................................TA
If REV unlocked:
IF BUFFET:
MAX SPEED .............................................................................................................. 240 KT
If ENG FIRE pb-sw pushed:
X BLEED ........................................................................................................................... SHUT
WING ANTI ICE......................................................................................................................OFF
AVOID ICING CONDITIONS
SECONDARY FAILURES
* HYD
* ELEC
* AIR BLEED
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AU →
PRO-ABN-ENG P 71/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) SHUT DOWN (Cont'd)
L2
Note:
In some conditions, with full asymmetric power, the aircraft may be control-limited before
reaching the protection system limit. Therefore, in extreme conditions, where low speed
may be advantageous (GPWS , WINDSHEAR, etc.), reduce speed with care below VLS
and respect the minimum control speed.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AU →
PRO-ABN-ENG P 72/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) SHUT DOWN (Cont'd)
Ident.: PRO-ABN-ENG-I-00017852.0005001 / 22 MAR 17
L12
STATUS
If ENG 1(2) FIRE pb-sw pushed:
AVOID ICING CONDITIONS
IF SEVERE ICE ACCRETION:
MIN SPD......................................... VLS + 10/G DOT
MANEUVER WITH CARE
LDG DIST PROC............................................ APPLY
If REV unlocked:
MAX SPEED........................................................300/0.78
APPR PROC
INOP SYS
CAT 3 DUAL
ENG 1(2) BLEED
PACK 1(2)
MAIN GALLEY
GEN 1(2)
G ENG 1 PUMP or
Y ENG 2 PUMP
(1)
WING A. ICE
AFT CRG HEAT
STEEP APPR
If REV unlocked:
4 doors not stowed (CFM) or reverser deployed
(IAE/PW):
IF BUFFET:
FOR LDG.........................................USE FLAP 1
This line is replaced by "FOR LDG : USE FLAP
1" when CONF 1 is selected, as a reminder.
APPR SPD....................................VREF + 55 KT
RUD TRIM.........................................5 DEG R(L)
When committed to land, set 5 ° rudder trim
towards live engine.
A/THR............................................................ OFF
GPWS FLAP MODE..................................... OFF
WHEN LDG ASSURED:
L/G.............................................................DOWN
AT 800 FT AGL:
TARGET SPD...............................VREF + 40 KT
LDG DIST PROC......................................APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AU →
Continued on the following page
PRO-ABN-ENG P 73/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) SHUT DOWN (Cont'd)
1, 2, or 3 doors not stowed (CFM), or reverse
detected unlocked (IAE/PW):
IF BUFFET:
FOR LDG.........................................USE FLAP 3
This line is replaced by "FOR LDG : USE FLAP
3" when CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3....................................... ON
APPR SPD....................................VREF + 10 KT
LDG DIST PROC......................................APPLY
If WING A/ICE off and ENG 1(2) FIRE pb-sw not
pressed:
IF PERF PERMITS:
X BLEED...........................................................OPEN
If no obstacle constraint exists, open the XBLEED.
To determine the single engine gross ceiling,
decrease by1 200 ft the result provided by the QRH
table (Refer to QRH/PER-L Ceilings (Paper Only))
or by the performance application of FlySmart with
Airbus.
For A321 aircraft:
ECON FLOW......................................................... ON
AFT CRG HOT AIR .................................... OFF
The ECON FLOW must be selected ON, and the
aft cargo heat must be selected OFF, due to
precooler performance.
IF NO ENG 1(2) DAMAGE:
CONSIDER ENG 1(2) RELIGHT
CAT 3 SINGLE ONLY
ONE PACK ONLY IF WAI ON
(2)
See
(1)
(2)
(if affected ENG FIRE pb-sw pushed)
Note:
‐ If available, the APU may be started and the APU GEN used
‐ If the ENG 1 FIRE pb-sw is pushed, APU bleed must not be used.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AU →
PRO-ABN-ENG P 74/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) SHUT DOWN (Cont'd)
If ENG 2 FIRE pb-sw is pushed, APU bleed may be used, provided the X BLEED
rotary selector is set at SHUT.
‐ After landing, the Fuel Used value of the engine, shutdown in flight, becomes
incorrect.
ENG 1(2) STALL
Applicable to: ALL
Ident.: PRO-ABN-ENG-Z-00017876.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when an engine stall is detected.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AU to AV →
PRO-ABN-ENG P 75/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) STALL (Cont'd)
Ident.: PRO-ABN-ENG-Z-00017749.0003001 / 17 MAR 17
L2
A stall may be indicated by varying degrees of abnormal engine noises, accompanied by
flame from the engine exhaust (and possibly from the engine inlet in severe case), fluctuating
performance parameters, sluggish or no thrust lever response, high EGT and/or a rapid EGT rise
when thrust lever is advanced. Engine stalls must be reported for maintenance action.
L1
THR LEVER (AFFECTED ENGINE)............................................................................................ IDLE
ENG MASTER (AFFECTED ENGINE)......................................................................................... OFF
ASSOCIATED PROCEDURES
L2
ENG 1(2) SHUT DOWN
If N2 is above IDLE:
L1
L12
This caution is not displayed on the ECAM.
Consequently, if the crew detects a stall, it must apply the following procedure:
On ground:
THR LEVER (AFFECTED ENGINE)...............................................................................IDLE
ENG MASTER (AFFECTED ENGINE)............................................................................ OFF
In flight:
THR LEVER (AFFECTED ENGINE)...............................................................................IDLE
ENG PARAMETERS (AFFECTED ENGINE)............................................................. CHECK
If abnormal ENG parameters:
ENG MASTER (AFFECTED ENGINE)......................................................................OFF
ASSOCIATED PROCEDURES
ENG 1(2) SHUT DOWN
Apply the ENG SHUT DOWN procedure (Refer to PRO-ABN-ENG ENG 1(2)
SHUT DOWN).
L2
L1
If normal ENG parameters:
ENG ANTI ICE (AFFECTED ENGINE)....................................................................... ON
WING ANTI ICE.......................................................................................................... ON
Operation of ENG and WING ANTI ICE will increase the stall margin but EGT
increases accordingly.
THR LEVER (AFFECTED ENGINE).................................. SLOWLY MOVE FORWARD
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AV →
PRO-ABN-ENG P 76/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) STALL (Cont'd)
L2
L1
L2
If stall recurs:
THR LEVER (AFFECTED ENGINE)..........................................MOVE BACKWARD
Reduce thrust and operate below the stall threshold where stall recurs.
If stall does not recur:
CONTINUE NORMAL ENGINE OPERATION
Ident.: PRO-ABN-ENG-Z-00017748.0001001 / 21 MAR 16
STATUS
CONSIDER ENG 1(2) RELIGHT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AV
PRO-ABN-ENG P 77/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) START FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-AD-00017995.0001001 / 13 MAY 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when start fault due to:
‐ No light up, or
‐ Engine stall, or
‐ Engine overtemperature (above 725 °C), or
‐ Starter time exceeded, or
‐ Low start air pressure, or
‐ Thrust lever not at idle.
Flight Phase Inhibition:
Note:
Alert inhibited in the flight phase 6, only if it is due to thrust lever not at idle.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AW →
PRO-ABN-ENG P 78/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) START FAULT (Cont'd)
Ident.: PRO-ABN-ENG-AD-00012100.0005001 / 13 MAY 16
ENG 1(2) IGNITION FAULT:
L2
The engine does not start within the 18 s that follow the ignition start.
L1
In flight:
ENG MASTER (AFFECTED)........................................................................................... OFF
Wait 30 s before attempting a new start (to drain the engine).
L2
L1
L2
L1
L2
L1
L2
On the ground (auto start) :
If the engine does not start, the FADEC can attempt an additional engine restart. After any
start attempt that is not successful, a dry crank phase automatically occurs. The ECAM
displays the following messages:
AUTO CRANK IN PROGRESS
NEW START IN PROGRESS
When the final dry cranking process is finished:
ENG MASTER (AFFECTED).....................................................................................OFF
Following starter cooldown, the pilot must decide whether to attempt auto or manual
start, or to report the no start condition for appropriate maintenance action.
On the ground (manual start):
ENG MASTER (AFFECTED)........................................................................................... OFF
MAN START (AFFECTED).............................................................................................. OFF
MODE SEL..................................................................................................................CRANK
MAN START (AFFECTED)................................................................................................ON
Note:
ECAM does not display the last two lines of the above procedure.
Dry crank the engine for 30 s. The start valve automatically reopens when N2 is
below 20 %.
After the starter cools, and for any subsequent attempt to start the engine, the
flight crew must perform a manual start, or must report the “no start condition” to
maintenance for appropriate action.
L1
ENG 1(2) STALL, ENG 1(2) EGT OVERLIMIT:
In flight:
ENG MASTER (AFFECTED)........................................................................................... OFF
L2
Wait 30 s before attempting a new start (to drain the engine).
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AW →
PRO-ABN-ENG P 79/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) START FAULT (Cont'd)
L1
L2
L1
L2
L1
L2
L1
L2
L1
On ground (auto start):
If the FADEC detects a stall or a potential EGT overheat, the FADEC will reduce the fuel
schedule in stages, if necessary, to achieve a normal condition. The following message will
be displayed on the ECAM:
NEW START IN PROGRESS
If restart not possible:
If normal conditions cannot be achieved, the FADEC shuts off fuel and turn off ignition.
Then a dry crank phase automatically occurs. The ECAM displays the following
message:
AUTO CRANK IN PROGRESS
ENG MASTER (AFFECTED).....................................................................................OFF
‐ The fuel metering valve and starter air valve are automatically closed. Both igniters
are turned off
‐ Setting ENG MASTER to OFF confirms automatic start abort
‐ In case of ENG STALL, consider making a XBLEED start, if pressure is low.
On ground (manual start):
ENG MASTER (AFFECTED)........................................................................................... OFF
MAN START (AFFECTED).............................................................................................. OFF
MODE SEL..................................................................................................................CRANK
MAN START (AFFECTED)................................................................................................ON
Note:
ECAM does not display the last two lines of the above procedure.
Dry crank the engine for 30 s. The start valve automatically reopens when N2 is
below 20 %.
After the starter cools, and for any subsequent attempt to start the engine, the
flight crew must perform a manual start, or must report the “no start condition” to
maintenance for appropriate action.
STARTER TIME EXCEEDED:
MAN START (IF MANUAL START IS PERFORMED)...........................................................OFF
ENG MASTER (AFFECTED)..................................................................................................OFF
LO START AIR PRESS:
BLEED AIR SUPPLY........................................................................................................ CHECK
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AW →
PRO-ABN-ENG P 80/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) START FAULT (Cont'd)
THR LEVER NOT AT IDLE:
THR LEVER........................................................................................................................... IDLE
ENG 1(2) START VALVE FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-D-00017932.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the start valve is stuck in closed or open position.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AW to AX →
PRO-ABN-ENG P 81/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) START VALVE FAULT (Cont'd)
Ident.: PRO-ABN-ENG-D-00018010.0002001 / 21 MAR 17
L2
L1
L2
L1
START VALVE NOT CLOSED
Remove all bleed sources supplying the faulty start valve.
APU BLEED (IF ENG 1 AFFECTED).................................................................................... OFF
X BLEED.............................................................................................................................. SHUT
In flight:
ENG BLEED (AFFECTED SIDE).....................................................................................OFF
On the ground:
MAN START (IF MAN START PERFORMED)................................................................OFF
ENG MASTER (AFFECTED SIDE)................................................................................. OFF
On the ground, consider application of “START VALVE MANUAL OPERATION” procedure.
START VALVE NOT OPEN
If opposite engine running:
X BLEED....................................................................................................................... OPEN
If APU AVAIL below FL 200:
APU BLEED....................................................................................................................... ON
L2
If UNSUCCESSFUL:
MAN START (IF MAN START PERFORMED)................................................................OFF
ENG MASTER (AFFECTED) (IF AUTO START PERFORMED).....................................OFF
MAN START procedure is useless since in both cases, the start valve is controlled by
FADEC.
On the ground, consider application of “START VALVE MANUAL OPERATION” procedure.
L1
EEC control of start valve failed (for IAE or PW 6000 engines):
On the ground:
START VALVE MAN ONLY
L2
Start valve must be manually opened (Refer to PRO-NOR-SUP-ENG Engine Start Valve
Manual Operation).
L1
L2
In flight:
WINDMILL START ONLY.
Windmilling start only is available since EEC cannot control the start valve.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AX
PRO-ABN-ENG P 82/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) THR LEVER ABV IDLE
Applicable to: ALL
Ident.: PRO-ABN-ENG-CW-00017922.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ One thrust lever is above idle while the other thrust lever is in the reverse detent at landing.
‐ One thrust lever is above idle while the other thrust lever is at idle, at reverser deselection
during landing roll.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-CW-00018748.0002001 / 21 MAR 16
L2
L1
The repetitive "RETARD-RETARD" synthetic voice is triggered at landing.
THR LEVER (AFFECTED ENGINE)............................................................................................ IDLE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AY
PRO-ABN-ENG P 83/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) THR LEVER DISAGREE
Applicable to: ALL
Ident.: PRO-ABN-ENG-L-00017999.0004001 / 06 SEP 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when a discrepancy between both resolvers of a thrust lever is detected.
Flight Phase Inhibition:
Note:
(a) Alert not inhibited in the flight phases 4 and 5, if the FADEC automatically selects IDLE
thrust.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AZ →
PRO-ABN-ENG P 84/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) THR LEVER DISAGREE (Cont'd)
Ident.: PRO-ABN-ENG-L-00012146.0017001 / 02 MAY 17
L2
Both Thrust Lever Angle (TLA) sensors not in agreement on one engine.
LAND ASAP
L1
On ground (if both TLA not at TOGA or FLX/MCT or if only one TLA is at TOGA or
FLX/MCT and the other is below IDLE):
ENG (AFFECTED) IDLE POWER ONLY.
L2
In that situation, the FADEC automatically selects IDLE.
L1
THR LEVER (AFFECTED)................................................................................................... IDLE
During take-off (if both TLA are above IDLE):
ENG (AFFECTED) TO, FLX, OR DRT TO
L2
If both TLA are above IDLE, the FADEC automatically selects TO , FLX TO, or DRT TO
thrust until thrust reduction, after which the maximum available thrust is CLB.
L1
In cruise (with slats retracted):
AVAIL MAX POWER : CLB
L2
In flight, if the failure occurs while the thrust lever is between idle and MCT , and if the slats are
not extended, (or when MN > 0.55, if the onside EIU is failed) the FADEC selects the larger
TLA power limited to CLB.
L1
A/THR (IF ENGAGED) ................................................................................................. KEEP ON
A/THR (IF NOT ENGAGED AND IF SLATS ARE NOT EXTENDED) .................................... ON
L2
With A/THR engaged, thrust is automatically managed between IDLE and higher TLA position.
L1
In approach (with slats extended):
ENG (AFFECTED) AT IDLE (WHEN SLATS ARE EXTENDED FOR APPROACH)..
L2
If TLA at, or below, MCT and if the slats are extended for approach, (or when MN < 0.47, if the
onside EIU is failed).
L1
THR LEVER (AFFECTED)................................................................................................... IDLE
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AZ →
PRO-ABN-ENG P 85/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) THR LEVER DISAGREE (Cont'd)
Ident.: PRO-ABN-ENG-L-00018067.0013001 / 21 MAR 16
L12
STATUS
INOP SYS
If TLA at, or below, MCT
WHEN SLATS OUT:
ENG 1(2) THR
(Displayed, if slats not extended), or
WHEN MN < 0.47:
(Displayed, if the onside EIU is failed)
ENG (AFFECTED) AT IDLE
For any case of thrust lever disagree (TO, FLEX, or
between Idle and MCT ), the FADEC will command
idle thrust for the approach when slats are extended
(or when the Mach number is less than 0.47, if
associated EIU is failed). It is independent of the
autothrust condition. The affected engine’s thrust
remains definitively at idle, even for go-around.
ENG (affected) AVAIL MAX PWR: CLB
ON GND ENG (affected) MAX PWR: IDLE.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AZ
PRO-ABN-ENG P 86/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) THR LEVER FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-M-00018000.0003001 / 01 JUN 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both resolvers on one thrust lever are failed.
Flight Phase Inhibition:
Note:
(a) Alert not inhibited in flight phases 4 and 5 if the FADEC automatically selects IDLE
thrust.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
BA →
PRO-ABN-ENG P 87/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) THR LEVER FAULT (Cont'd)
Ident.: PRO-ABN-ENG-M-00018069.0009001 / 21 MAR 16
LAND ASAP
On the ground:
ENG (AFFECTED) IDLE POWER ONLY.
L2
Idle power is automatically selected by FADEC.
If associated thrust reverser is already deployed, FADEC commands restow.
L1
THR LEVER (AFFECTED).................................................................................................... IDLE
L2
L1
L2
L1
L2
L1
L2
L1
L2
In flight:
If the selected thrust lever position at the time of fault detection is:
TO or FLEX: FADEC freezes TO or FLEX TO thrust until slat retraction. At slat retraction it
selects CLB thrust.
Between IDLE and MCT: in manual thrust setting mode, engine rating freezes at CLB , or
IDLE with slats extended (or MN < 0.47 if the FADEC no longer receives the slats position
due to EIU failure). It is possible to activate autothrust. If selected, autothrust mode manages
thrust between idle and CLB.
ENG (AFFECTED) AT IDLE
For any case of thrust lever fault (TO, FLEX or between IDLE and MCT) the FADEC will
command idle thrust for the approach when slats are extended (or when MN < 0.47 if
associated EIU is failed). It is independant of the autothrust condition. Thrust of affected engine
remains definitively at idle even for go around.
THR LEVER (AFFECTED) ................................................................................................... IDLE
When slats are extended or MN < 0.47, if on side EIU is failed.
A/THR engaged:
A/THR......................................................................................................................KEEP ON
A/THR not engaged:
ENG (AFFECTED) HI PWR IN MAN THR.
Inhibited when the FADEC commands the affected engine at IDLE.
BEFORE SLATS IN:
A/THR .........................................................................................................................ON
HI PWR ONLY
If thrust lever angle failed in TO or flex position.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← BA →
PRO-ABN-ENG P 88/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG 1(2) THR LEVER FAULT (Cont'd)
Ident.: PRO-ABN-ENG-M-00012152.0002001 / 14 NOV 11
L12
STATUS
INOP SYS
WHEN SLATS OUT:
(Displayed if slats not extended) or,
WHEN MN < 0.47:
REVERSER 1(2)
ENG 1(2) THR
(Displayed if the onside EIU is failed).
ENG 1(2) AT IDLE
ENG THR LEVERS NOT SET
Applicable to: ALL
Ident.: PRO-ABN-ENG-DD-00017892.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the levers position does not correspond to TO power mode.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← BA to BB →
PRO-ABN-ENG P 89/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG THR LEVERS NOT SET (Cont'd)
Ident.: PRO-ABN-ENG-DD-00017863.0003001 / 21 MAR 16
L2
At least one FADEC engaged a takeoff thrust mode that is not in accordance with the position of
the thrust levers.
Note:
L1
1. The takeoff thrust mode is engaged when the flight crew sets the thrust levers above
the CL position.
2. The flex takeoff thrust mode is armed only if the flight crew entered a FLEX TO TEMP
on the MCDU that is above the OAT.
If the flex mode is not armed, and the flight crew sets the thrust levers below or at the
MCT/FLX position:
THR LEVERS..................................................................................................................... TO/GA
If the flex mode is armed, and the flight crew sets the thrust levers below the MCT/FLX
position:
THR LEVERS ............................................................................................................... MCT/FLX
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← BB
PRO-ABN-ENG P 90/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG THRUST LOCKED
Applicable to: ALL
Ident.: PRO-ABN-ENG-DE-00017888.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when thrust levers are not moved within 5 s, following an unvoluntary
disconnection of the A/THR (or disconnection through the FCU pb).
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-DE-00017865.0002001 / 21 MAR 16
THR LEVERS.............................................................................................................................MOVE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
BC
PRO-ABN-ENG P 91/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG TYPE DISAGREE
Applicable to: ALL
Ident.: PRO-ABN-ENG-DF-00017881.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when a rating discrepancy between two engines is detected.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-DF-00017868.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
BD
PRO-ABN-ENG P 92/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
ENG VIB SYS FAULT
Applicable to: ALL
Ident.: PRO-ABN-ENG-DG-00017879.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the vibration detection system is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-ENG-DG-00012074.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
BE
PRO-ABN-ENG P 93/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
ENG
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-ENG P 94/94
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
[QRH] LANDING WITH SLATS OR FLAPS JAMMED
Ident.: PRO-ABN-F_CTL-00010683.0001001 / 17 MAR 17
Applicable to: ALL
LDG DIST PROC......................................................................................................................APPLY
Determine flap lever position for landing
Repeat the following until landing configuration is reached:
SPD SEL............................................................................................................ VFE NEXT - 5 kt
AT VFE NEXT: SELECT FLAPS LEVER ONE STEP DOWN
Note:
‐ OVERSPEED alert, and VLS displayed on the PFD, are computed according to the
actual flaps/slats position
‐ VFE and VFE NEXT are displayed on the PFD according to the FLAPS lever
position. If not displayed, use the placard speeds
‐ If VLS is greater than VFE NEXT (overweight landing case), the FLAPS lever
can be set in the required next position, while the speed is reduced to follow VLS
reduction as surfaces extend. The VFE warning threshold should not be triggered.
In this case, disconnect the A/THR . A/THR can be re-engaged when the landing
configuration is established.
When in landing CONF and in final approach:
DECELERATE TO CALCULATED VAPP
AP BELOW 500 ft AGL : DO NOT USE
For Go-around:
Slats
Flaps
S=0
03
MAX SPEED
F=0
03
215 kt
200 kt
185 kt
177 kt
(Not allowed)
200 kt
185 kt
NO LIMITATION
230 kt
200 kt
177 kt
177 kt
If SLATS FAULT:
For circuit:
MAINTAIN SLATS/FLAPS CONFIGURATION
Recommended speed: MAX SPEED - 10 kt
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
177 kt
177 kt
177 kt
Continued on the following page
PRO-ABN-F_CTL P 1/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
[QRH] LANDING WITH SLATS OR FLAPS JAMMED (Cont'd)
For diversion:
SELECT CLEAN CONFIGURATION
Recommended speed for flaps retraction: between MAX SPEED - 10 kt and MAX
SPEED.
Recommended diversion speed: MAX SPEED - 10 kt.
INCREASED FUEL CONSUMPTION
If FLAPS FAULT:
For circuit:
MAINTAIN SLATS/FLAPS CONFIGURATION
Recommended speed: MAX SPEED - 10 kt
For diversion:
If FLAPS jammed at 0:
SELECT CLEAN CONFIGURATION
Recommended speed for slats retraction: between MAX SPEED - 10 kt and MAX
SPEED
USE NORMAL OPERATING SPEEDS
If FLAPS jammed > 0:
MAINTAIN SLAT/FLAP CONFIGURATION
Recommended speed for diversion: MAX SPEED - 10 kt
Note:
In case of a go-around with CONF FULL selected, the L/G NOT DOWN
warning is triggered at landing gear retraction.
INCREASED FUEL CONSUMPTION
CAUTION
For flight with SLATS or FLAPS extended, fuel consumption is increased.
Refer to the fuel flow indication. As a guideline, determine the fuel
consumption in clean configuration at the same altitude without airspeed
limitation (e.g. From ALTERNATE FLIGHT PLANNING tables) and multiply this
result by the applicable Fuel Penalty Factor provided in the QRH, to obtain the
fuel penalty required to reach the destination in the current configuration. Refer
to QRH/OPS Fuel Penalty Factors/ECAM Alert Table.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-ABN-F_CTL P 2/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
[QRH] RUDDER JAM
Ident.: PRO-ABN-F_CTL-00011807.0001001 / 17 MAR 17
Applicable to: ALL
L2
Rudder jamming may be detected by undue (and adverse) pedal movement during rolling
maneuvers.
This is because the yaw damper orders can no longer be sent to the rudder, but are fed back to the
pedals.
Use F/CTL SD page for a visual check of the rudder position.
L1
For approach:
AVOID LANDING WITH CROSSWIND FROM THE SIDE WHERE THE RUDDER IS
DEFLECTED
MAX CROSSWIND FOR LDG: 15 kt
AUTO BRK..............................................................................................................DO NOT USE
L2
Do not use the autobrake, so as not to delay the application of differential braking at landing
roll.
L1
FOR LANDING........................................................................................... USE NORMAL CONF
SPEED AND TRAJECTORY.............................................................................STABILIZE ASAP
LDG DIST PROC............................................................................................................... APPLY
For landing:
DIFFERENTIAL BRAKING.......................................................................................... USE ASAP
REVERSER: SYMMETRIC USE ONLY
L2
Use nosewheel steering handle below 70 kt.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PRO-ABN-F_CTL P 3/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
[QRH] STABILIZER JAM
Ident.: PRO-ABN-F_CTL-00011806.0001001 / 17 MAR 17
Applicable to: ALL
L2
The ELACs may not detect a stabilizer jam when the pitch trim wheel is jammed.
The flight control normal law remains active in this case and there is no ECAM warning.
Apply the following procedure.
AP.................................................................................................................................................. OFF
MAN PITCH TRIM................................................................................................................... CHECK
L2 The pitch trim wheel may not be fully jammed, the force needed may be higher than pre-takeoff
manual setting.
L1
L1
If MAN PITCH TRIM available:
TRIM FOR NEUTRAL ELEV
L2
If manual pitch trim is available, trim to maintain the elevator at the zero position (indications on
F/CTL SD page).
L1
If MAN PITCH TRIM not available:
FOR LANDING: USE FLAP 3
L2
Do not select configuration full so as not to degrade the handling qualities.
L1
GPWS LDG FLAP 3.................................................................................................................ON
CAT 1 ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-F_CTL P 4/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
ACTIVE CONTROL LAW
Ident.: PRO-ABN-F_CTL-00018549.0001001 / 21 MAR 16
Applicable to: ALL
ACTIVE LAW ▸
SYS FAILED▾
ELAC 1 or 2
or SEC 1 or 2
ELAC 1 and 2
or both ailerons
2 SEC
3 SEC
2 FAC
Yaw damper
2 SFCC (slat channel)
2 ADR or 2 IR
(2nd self detected)
2 ADR (2nd
not self detec.)
2 IR (2nd not
self detec.)
3 ADR
3 IR
2 RADIO ALT
SPOILER 4 or
5 or (4 and 5)
All SPOILERS
1 AIL SERVO
or 1 AILERON
1 ELEV SERVO
1 ELEVATOR
THS (jammed) (5)
HYD G or Y or B
HYD G + Y
HYD G + B
HYD Y + B
on BATTERIES
on EMER GEN
LAW
PITCH
PROTEC
ROLL
YAW
NORM
NORM
NORM
NORM
ALTN
REDUCED
DIRECT
ALTN
NORM
ALTN
ALTN
ALTN
ALTN
NORM
REDUCED
REDUCED
REDUCED
NO
NORM
DIRECT
DIRECT
DIRECT
DIRECT
NORM
ALTN
MECH
MECH
ALTN
ALTN
REDUCED
DIRECT
ALTN
DIRECT
ALTN
DIRECT
–––––
ALTN (2)
ALTN
DIRECT
NORM
–––––
DIRECT (4)
NO
–––––
REDUCED (1)
NO
–––––
REDUCED (2)
NO
NO
NORM
–––––
NO (4)
DIRECT
DIRECT
NORM
–––––
DIRECT (4)
MECH
–––––
ALTN (2)
MECH
MECH
NORM
–––––
MECH (4)
NORM
NORM
NORM
NORM
ALTN
REDUCED
DIRECT
ALTN
NORM
NORM
NORM
NORM
NORM
ALTN
NORM
ALTN
NORM
ALTN
ALTN
NORM
ALTN
ALTN
NORM
REDUCED
NORM
REDUCED
NORM
REDUCED
NO
NORM
REDUCED
REDUCED
NORM
DIRECT
NORM
DIRECT
NORM
DIRECT
DIRECT
NORM
DIRECT
DIRECT
ALTN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
DIRECT
NORM
ALTN
NORM
ALTN
NORM
MECH
ALTN
NORM
MECH
MECH
Continued on the following page
PRO-ABN-F_CTL P 5/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
ACTIVE CONTROL LAW (Cont'd)
ACTIVE LAW ▸
SYS FAILED▾
LAW
PITCH
PROTEC
ROLL
(1)
In case of AOA disagree
(2)
After the faulty IR is selected OFF
(3)
After FAC 1 is reset
(4)
When landing gear down (or CONF 2, if both LGCIUs faulty)
(5)
Depending where the failure is, control law may revert to alternate law
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
YAW
–––––
ALTN (3)
PRO-ABN-F_CTL P 6/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
ELEVATORS AND STABILIZER CONTROL AFTER FAILURE
Ident.: PRO-ABN-F_CTL-00018591.0001001 / 09 FEB 16
Applicable to: ALL
NORM OPERATION
SINGLE FAILURE
ELAC 2
ELAC 1
SEC 2
SEC 1
G
Y
B
DOUBLE FAILURE
ELAC + ELAC 1
2
+ SEC 2
+ SEC 1
+G
+Y
+B
ELAC + SEC 2
1
+ SEC 1
+G
+Y
+B
SEC 2 + SEC 1
+G
+Y
+B
SEC 1 + G
+Y
+B
G+Y
B+G
B+Y
TRIPLE FAILURE
ELAC 2
ELAC + SEC 2
1
+ SEC 1
+G
LEFT ELEVATOR
BLUE
GREEN
ELAC 2
ELAC 1
ELAC 1
ELAC 1
ELAC 1
ELAC 1
ELAC 1
ELAC 1
SEC 1
ELAC 1
ELAC 1
ELAC 1
ELAC 1
ELAC 1
THS
GREEN AND YELLOW
ELAC 2
ELAC 2
ELAC 1
ELAC 2
ELAC 2
ELAC 2
ELAC 1
ELAC 1
ELAC 2
SEC 2
SEC 2
SEC 2
ELAC 2
ELAC 1
ELAC 1
ELAC 1
ELAC 1
SEC 2
ELAC 2
ELAC 2
ELAC 2
ELAC 2
ELAC 2
ELAC 2
SEC 2
SEC 2
ELAC 2
ELAC 2
ELAC 1
ELAC 1
ELAC 2
ELAC 1
ELAC 1
ELAC 2
INOP
ELAC 2
ELAC 2
SEC 2
ELAC 2
ELAC 2
ELAC 2
ELAC 2
Damped
ELAC 2
SEC 1
SEC 1
SEC 1
SEC 2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
SEC 2
SEC 2
E→
RIGHT ELEVATOR
YELLOW
BLUE
ELAC 2
ELAC 1
ELAC 2
ELAC 2
ELAC 2
ELAC 1
ELAC 1
ELAC 2
SEC 2
ELAC 1
ELAC 1
ELAC 1
ELAC 1
SEC 2
ELAC 2
ELAC 2
SEC 2
SEC 1
ELAC 2
ELAC 2
ELAC 1
ELAC 1
ELAC 2
ELAC 1
ELAC 1
ELAC 2
ELAC 2
ELAC 1
Damped
SEC 1
SEC 2
SEC 2
Continued on the following page
PRO-ABN-F_CTL P 7/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
ELEVATORS AND STABILIZER CONTROL AFTER FAILURE (Cont'd)
+Y
+B
SEC 2 + SEC 1
+G
+Y
+B
SEC 1 + G
+Y
+B
G+Y
B+G
B+Y
ELAC 1
SEC 2 + SEC 1
+G
+Y
+B
SEC 1 + G
+Y
+B
G+Y
B+G
B+Y
SEC 2
SEC 1 + G
+Y
+B
G+Y
B+G
B+Y
SEC 1
G+Y
B+G
B+Y
SEC 2
SEC 2
SEC 2
SEC 2
ELAC 1
ELAC 1
ELAC 1
Mechanical
ELAC 1
ELAC 1
SEC 2
INOP
SEC 2
SEC 2
ELAC 1
ELAC 1
ELAC 1
Centered
ELAC 1
ELAC 1
SEC 2
ELAC 1
Damped
SEC 2
SEC 1
SEC 1
SEC 1
ELAC 1
ELAC 1
ELAC 1
ELAC 1
ELAC 2
ELAC 2
SEC 1
SEC 1
ELAC 2
SEC 2
SEC 2
ELAC 2
INOP
ELAC 2
ELAC 2
ELAC 2
Damped
SEC 2
ELAC 2
Damped
ELAC 2
Damped
ELAC 2
ELAC 1
ELAC 1
ELAC 2
INOP
ELAC 2
ELAC 2
Damped
ELAC 2
INOP
ELAC 2
ELAC 2
ELAC 2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
SEC 1
SEC 2
Centered
SEC 2
SEC 2
ELAC 2
ELAC 2
Damped
SEC 1
SEC 1
Damped
SEC 1
Damped
ELAC 1
ELAC 1
ELAC 2
ELAC 2
ELAC 2
ELAC 1
ELAC 1
ELAC 1
ELAC 2
ELAC 2
SEC 2
ELAC 1
ELAC 1
ELAC 1
ELAC 1
Damped
ELAC 1
Damped
PRO-ABN-F_CTL P 8/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL AIL SERVO FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-AF-00016986.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a loss of one servojack on one aileron, or loss of one or both
ELAC 1 rudder pedal transducers.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-AF-00018412.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-ABN-F_CTL P 9/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL ALTN LAW
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-K-00016965.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when alternate laws are active.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-K-00018413.0001001 / 22 MAR 17
Refer to DSC-27-20-20 General for flight characteristics.
With autopilot engaged the FMGC (AP mode) controls the aircraft.
L1 (PROT LOST)
L2 All protections, except maneuver protections, are lost. Depending on the failure, static stability may
be introduced.
L2
L1
Note:
In case of GPWS (EGPWS ) alerts, since protections are lost, respect stall warnings
when applying the GPWS (EGPWS ) procedure.
MAX SPEED.............................................................................................................................320 KT
(320/.77 if dual hydraulic system low pressure). Speed is limited to 320 /.82 or 320/.77 for dual
hydraulic failure, due to the loss of high-speed protection.
L1 SPD BRK (IF L OR R ELEVATOR FAULT) .................................................................DO NOT USE
L2
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G→
PRO-ABN-F_CTL P 10/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL ALTN LAW (Cont'd)
Ident.: PRO-ABN-F_CTL-K-00018414.0003001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320 KT
(320/.77, if dual hydraulic system low pressure).
SPD BRK (IF L OR R ELEVATOR FAULT)....... DO NOT USE
INOP SYS
F/CTL PROT
STEEP APPR
APPR PROC
FOR LDG............................................................ USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3 ..........................................................ON
APPR SPD .............................................................. VREF+10
LDG DIST PROC ........................................................ APPLY
If no AP engaged:
WHEN L/G DN: DIRECT LAW
At landing gear extension, control reverts to direct law in
pitch, as well as in roll. Refer to PRO-ABN-F_CTL F/CTL
DIRECT LAW.
If AP engaged:
WHEN L/G DN AND AP OFF: DIRECT LAW
If the autopilot is disengaged:
‐ Before landing gear extension, flight control alternate law
is active.
‐ After landing gear extension, flight control direct law is
active. Refer to PRO-ABN-F_CTL F/CTL DIRECT LAW.
ALTN LAW: PROT LOST
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-ABN-F_CTL P 11/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL DIRECT LAW
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-J-00016964.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when direct law is active.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H→
PRO-ABN-F_CTL P 12/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL DIRECT LAW (Cont'd)
Ident.: PRO-ABN-F_CTL-J-00018420.0001001 / 22 MAR 17
L2
L1
L2
PFD displays « USE MAN PITCH TRIM » in amber. Refer to DSC-27-20-10-70 Aircraft Trimming
(PROT LOST)
Note:
In case of GPWS ( EGPWS ) alerts, since protections are lost, respect stall warning
when applying the GPWS (EGPWS ) procedure.
MAX SPEED.............................................................................................................................320/.77
Speed is limited, due to the loss of high-speed protection. Do not exceed M 0.77, so as not to
degrade handling qualities.
L1 MAN PITCH TRIM (EXCEPT IF HYD Y + G SYS LO PR).......................................................... USE
L2 Automatic trim is inoperative in direct law.
L1 MANEUVER WITH CARE
L2 Use small control inputs at high speed, since in direct law the controls are powerful. Use of manual
thrust is recommended. Avoid large thrust changes.
L1 USE SPD BRK WITH CARE
L2 At high Mach numbers, use speed brakes with care to avoid too strong nose up changes.
L1
L2
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H→
PRO-ABN-F_CTL P 13/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL DIRECT LAW (Cont'd)
Ident.: PRO-ABN-F_CTL-J-00018422.0003001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320/.77
MANEUVER WITH CARE
USE SPD BRK WITH CARE
APPR PROC
INOP SYS
F/CTL PROT
STEEP APPR
FOR LDG..........................................................USE FLAPS 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3...........................................................ON
MAN PITCH TRIM............................................................ USE
APPR SPD............................................................... VREF+10
LDG DIST PROC......................................................... APPLY
DIRECT LAW
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H
PRO-ABN-F_CTL P 14/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL ELAC 1(2) FAULT
(ONE COMPUTER FAILED)
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-F-00016960.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a failure of ELAC (FAULT lt on ELAC pb), or when one
sidestick transducer is faulty.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-F-00018425.0006001 / 21 MAR 16
ELAC (AFFECTED)..................................................................................................... OFF THEN ON
L2
Note:
1. In some sidestick transducer failure cases, ELAC 1(2) FAULT is triggered without the
procedure, and FAULT It on associated pb does not come on.
2. If the ELAC 1 computer is reset on ground the pitch trim returns to the ground setting
position (0 °).
L1
IF UNSUCCESSFUL:
ELAC (AFFECTED)................................................................................................................ OFF
L2
Functions are performed by other ELAC.
L1
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I→
PRO-ABN-F_CTL P 15/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL ELAC 1(2) FAULT (Cont'd)
(ONE COMPUTER FAILED)
Ident.: PRO-ABN-F_CTL-F-00018426.0003001 / 21 MAR 17
L12
STATUS
INOP SYS
(1)
(2)
CAT 3 SINGLE ONLY
ELAC 1(2)
CAT 3 DUAL
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS chapter in order to find the applicable Fuel
Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I
PRO-ABN-F_CTL P 16/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL ELAC 1(2) FAULT
(BOTH COMPUTERS FAILED)
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-G-00018899.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a failure of ELAC (FAULT lt on ELAC pb), or when one
sidestick transducer is faulty.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J→
PRO-ABN-F_CTL P 17/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL ELAC 1(2) FAULT (Cont'd)
(BOTH COMPUTERS FAILED)
Ident.: PRO-ABN-F_CTL-G-00018433.0009001 / 22 MAR 17
ELAC 1........................................................................................................................ OFF THEN ON
L2
Note:
L1
ELAC 2........................................................................................................................ OFF THEN ON
If both ELAC FAULT remain:
ELAC 1....................................................................................................................................OFF
ELAC 2....................................................................................................................................OFF
If the ELAC 1 computer is reset on ground, the pitch trim returns to the ground setting
position (0 °).
ASSOCIATED PROCEDURES
F/CTL ALTN LAW
(PROT LOST)
L2
L1
Pitch and roll normal laws are lost: Refer to PRO-ABN-F_CTL F/CTL ALTN LAW. THS motor 1
and both ailerons are lost. LAF is degraded and uses spoilers only.
MAX SPEED...................................................................................................................... 320 KT
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←J→
PRO-ABN-F_CTL P 18/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL ELAC 1(2) FAULT (Cont'd)
(BOTH COMPUTERS FAILED)
Ident.: PRO-ABN-F_CTL-G-00018434.0004001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320 KT
APPR PROC
FOR LDG............................................................ USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3...........................................................ON
Will be displayed when flaps in CONF 3
APPR SPD..........................................................VREF+10 KT
LDG DIST PROC......................................................... APPLY
INOP SYS
F/CTL PROT
L+R AIL
ELAC 1+2
AP 1+2
CAT 2
STEEP APPR
ALTN LAW: PROT LOST
WHEN L/G DOWN: DIRECT LAW
(1)
See
FUEL CONSUMPT INCRSD
(2)
See
FMS PRED UNRELIABLE
(3)
See
(1)
(2)
(3)
At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW).
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS chapter in order to find the applicable Fuel
Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←J
PRO-ABN-F_CTL P 19/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL ELAC 1(2) PITCH FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-H-00016977.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a failure of pitch channel in ELAC 1(2).
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-H-00018447.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-F_CTL-H-00018448.0001001 / 21 MAR 16
STATUS
INOP SYS
CAT 3 SINGLE ONLY
(1)
ELAC PITCH
CAT 3 DUAL
(1)
(If ELAC 1 and 2 PITCH FAULT)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K
PRO-ABN-F_CTL P 20/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL ELEV SERVO FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-P-00016979.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a loss of one servojack on one elevator.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-P-00018449.0001001 / 21 MAR 16
Crew awareness.
CAUTION
Do not use speedbrakes above 350 kt/M 0.82 (VMO /MMO).
Ident.: PRO-ABN-F_CTL-P-00018450.0001001 / 21 MAR 16
STATUS
INOP SYS
CAT 3 SINGLE ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
CAT 3 DUAL
L
PRO-ABN-F_CTL P 21/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL FCDC 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-L-00016981.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a failure of one FCDC.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-L-00011777.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-F_CTL-L-00011778.0001001 / 18 AUG 10
STATUS
INOP SYS
FCDC 1(2)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
M
PRO-ABN-F_CTL P 22/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL FCDC 1+2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-M-00016963.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a failure of both FCDCs.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-M-00011779.0001001 / 18 AUG 10
L2
MONITOR F/CTL OVHD PNL
F/CTL data on ECAM is lost.
Control laws remains normal.
Note:
When both FCDCs fails:
‐ F/CTL warning are not available on the ECAM.
‐ Stall warning may be triggered as in alternate or direct law (it may occur at speeds
greater than Vα max).
‐ Bank and pitch limits are no longer displayed on the PFD.
‐ Vα prot, Vα max are lost on the PFD.
‐ Vsw, displayed on the PFD, corresponds to the stall warning of the alternate or direct
law.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
N→
PRO-ABN-F_CTL P 23/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL FCDC 1+2 FAULT (Cont'd)
Ident.: PRO-ABN-F_CTL-M-00018451.0001001 / 21 MAR 16
STATUS
INOP SYS
F/CTL INDICATIONS LOST
FCDC 1 + 2
STEEP APPR
F/CTL FLAP ATTACH SENSOR
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-AH-00016989.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is failure of flap attachment's failure detection sensor.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-AH-00018453.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← N to O
PRO-ABN-F_CTL P 24/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL FLAPS FAULT/LOCKED
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-A-00011744.0002001 / 21 MAR 16
If flaps locked:
WING TIP BRK ON OR ALIGNMENT FAULT
L2
MAX SPEED........................ REFER TO PRO-ABN-F_CTL F/CTL FLAPS/SLATS FAULT/LOCKED
Limit speed to the VFE corresponding to the next flap position
L1
If flaps not locked:
FLAPS LEVER.............................................................................................................. RECYCLE
L2
Return to the previous selection, then back to the desired position.
L1
If flaps extended:
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
L2
If unsuccessful:
Refer to PRO-ABN-F_CTL [QRH] Landing with Slats or Flaps Jammed .
The autopilot may be used down to 500 ft AGL. As it is not tuned for abnormal configurations,
its behavior can be less than optimum and must be monitored.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
P→
PRO-ABN-F_CTL P 25/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL FLAPS FAULT/LOCKED (Cont'd)
Ident.: PRO-ABN-F_CTL-A-00018456.0004001 / 21 MAR 17
L12
STATUS
INOP SYS
APPR PROC
FLAPS
FOR LDG (IF FLAPS ≤ 3)...................................USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder
FLAPS (IF FLAPS>3)................................KEEP CONF FULL
GPWS FLAP MODE (IF FLAPS < 3)................................OFF
GPWS LDG FLAP 3 (IF FLAPS ≥ 3)..................................ON
APPR SPD.................................................................. REFER
TO PRO-ABN-F_CTL F/CTL FLAPS/SLATS FAULT/LOCKED
LDG DIST PROC......................................................... APPLY
AP 1+2
A/THR
(1)
(1)
Moreover, both FDs are lost
(1)
(1)
CAT 2
GLS AUTOLAND
STEEP APPR
ENG 1 APPR IDLE ONLY (Only in case of FLAPS FAULT)
ENG 2 APPR IDLE ONLY (Only in case of FLAPS FAULT)
FUEL CONSUMPT INCRSD
(2)
See
FMS PRED UNRELIABLE
(3)
See
(1)
(2)
(3)
(If both flap channels fault.)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS chapter in order to find the applicable Fuel
Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←P
PRO-ABN-F_CTL P 26/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL FLAP LVR NOT ZERO
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-AI-00018902.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the FLAP lever is not in the zero position, and the aircraft is above
22 000 ft.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-AI-00018454.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Q
PRO-ABN-F_CTL P 27/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL FLAP SYS 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-E-00016990.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
This alert triggers when there is failure of flap channel in one SFCC.
L2
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-E-00011753.0002001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-F_CTL-E-00011754.0002001 / 30 MAR 12
L12
STATUS
APPR PROC
In case of FLAP SYS 1 FAULT:
GPWS FLAP MODE...................................................OFF
Flap position signal to GPWS is lost.
ENG 1(2) APPR IDLE ONLY
FLAPS SLOW
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
R
PRO-ABN-F_CTL P 28/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL FLAPS/SLATS FAULT/LOCKED
Ident.: PRO-ABN-F_CTL-00018457.0001001 / 17 MAR 17
Applicable to: ALL
MAX SPEED
Flaps(1)
Slats(1)
S=0
0 < S <1
S=1
13
(1)
03
Not allowed
(177 kt)
200 kt
177 kt
Slats/Flaps position displayed on the upper ECAM display.
Slats(1)
Flaps(1)
S=0
03
(1)
F=0
APPR SPD
F=0
0 3
not allowed)
VREF +25
VREF +10
VREF +5
Slats/Flaps position displayed on the upper ECAM display.
CAUTION
For flight with SLATS or FLAPS extended, fuel consumption is increased.
Refer to the fuel flow indication.
As a guideline, determine the fuel consumption in clean configuration, at the same
altitude without airspeed limitation (e.g. from ALTERNATE FLIGHT PLANNING
tables, Refer to PER-FPL-FLP-ALN-20 ALTERNATE PLANNING ISA), and
multiply this result by the applicable Fuel Penalty Factor provided in the QRH
(Refer to QRH/OPS Fuel Penalty Factors/ECAM Alert Table) to obtain the fuel
penalty required to reach the destination in the current configuration.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
S
PRO-ABN-F_CTL P 29/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL GND SPLR 5 FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-Z-00016967.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
This alert triggers when there is a loss of ground spoiler function in SEC 2.
L2
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-Z-00018903.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-F_CTL-Z-00014253.0001001 / 23 MAY 12
L12
STATUS
LDG DIST PROC......................................................... APPLY
.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
T
INOP SYS
GND SPLR 5
PRO-ABN-F_CTL P 30/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL GND SPLR / 1+2 / 3+4 / FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-S-00016968.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
‐ GND SPLR FAULT :
Loss of ground spoiler function in SEC 1+3, or 1+2, or 2+3, or 1+2+3.
If ground spoiler function is lost in SEC (1+2) or (1+3), one reverser is inoperative.
If ground spoiler function is lost in SEC (1+2+3), both reversers are inoperative.
In any case, the autobrake function is lost.
‐ GND SPLR 1+2(3+4) FAULT:
Loss of ground spoiler function in SEC 3 (or 1).
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-S-00018466.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-F_CTL-S-00011793.0001001 / 11 MAY 12
STATUS
LDG DIST PROC......................................................... APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
U
INOP SYS
GND SPLR (affected)
PRO-ABN-F_CTL P 31/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL GND SPLR NOT ARMED
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-AJ-00016966.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when ground spoilers are not armed before landing.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-AJ-00018905.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
V
PRO-ABN-F_CTL P 32/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL L(R) AIL FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-N-00016975.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a loss of both servojacks on one aileron.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-N-00018474.0002001 / 21 MAR 16
Crew awareness.
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
W→
PRO-ABN-F_CTL P 33/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL L(R) AIL FAULT (Cont'd)
Ident.: PRO-ABN-F_CTL-N-00011783.0003001 / 21 MAR 17
L12
STATUS
INOP SYS
(1)
(2)
FUEL CONSUMPT INCRSD
L (R) AIL
(1)
See
FMS PRED UNRELIABLE
(2)
See
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS chapter in order to find the applicable Fuel
Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←W
PRO-ABN-F_CTL P 34/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL L(R) ELEV FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-Q-00016974.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a loss of both servojacks on one elevator, or activation of
elevator flutter protection in ELAC.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-Q-00018484.0001001 / 22 MAR 17
ASSOCIATED PROCEDURES
F/CTL ALTN LAW
(PROT LOST)
L2
Note:
If the L(R) elevator fails, the ELAC s loose pitch control through the elevator. Therefore,
the SEC s control pitch in alternate law. This is not the case, if the right elevator is lost,
due to the failure of B+Y hydraulic circuits. Pitch normal law remains active in ELAC.
MAX SPEED.............................................................................................................................320 KT
Speed is limited, due to the loss of high-speed protection.
L1 SPD BRK.......................................................................................................................DO NOT USE
L1
L2
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
X→
PRO-ABN-F_CTL P 35/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL L(R) ELEV FAULT (Cont'd)
Ident.: PRO-ABN-F_CTL-Q-00018490.0003001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320 KT
SPD BRK...........................................................DO NOT USE
APPR PROC
FOR LDG............................................................ USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3...........................................................ON
Will be displayed, when flaps in CONF 3.
APPR SPD..........................................................VREF+10 KT
LDG DIST PROC......................................................... APPLY
INOP SYS
F/CTL PROT
L (R) ELEV
ELAC PITCH
AP 1+2
CAT 2
GLS AUTOLAND
STEEP APPR
ALTN LAW: PROT LOST
WHEN L/G DN: DIRECT LAW
(1)
See
(1)
At landing gear extension, control reverts to direct law in pitch, as well as in roll.Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←X
PRO-ABN-F_CTL P 36/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL L+R ELEV FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-O-00016958.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both elevators are lost.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-O-00018491.0001001 / 22 MAR 17
MAX SPEED.............................................................................................................................320/.77
Due to loss of high speed protections.
L1 MAN PITCH TRIM........................................................................................................................ USE
L2 Only manual trim is available for pitch control.
L1 SPD BRK.......................................................................................................................DO NOT USE
L2 Do not use speed brakes, because it is difficult to control the induced pitch moment with manual
pitch trim only.
L2
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Y→
PRO-ABN-F_CTL P 37/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL L+R ELEV FAULT (Cont'd)
Ident.: PRO-ABN-F_CTL-O-00018492.0009001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320/.77
SPD BRK...........................................................DO NOT USE
APPR PROC
FOR LDG............................................................ USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder
GPWS LDG FLAP 3...........................................................ON
Will be displayed when flaps in CONF 3.
MAN PITCH TRIM............................................................ USE
APPR SPD............................................................... VREF+10
LDG DIST PROC......................................................... APPLY
INOP SYS
L+R ELEV
ELAC PITCH
AP 1+2
CAT 2
GLS AUTOLAND
STEEP APPR
PITCH MECH BACK UP
ROLL DIRECT LAW
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←Y
PRO-ABN-F_CTL P 38/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL L(R) SIDESTICK FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-Y-00016959.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when transducers, on pitch or roll axis, are failed on one sidestick.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-Y-00011756.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-F_CTL-Y-00014250.0001001 / 30 MAR 12
STATUS
INOP SYS
L(R) SIDESTICK
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Z
PRO-ABN-F_CTL P 39/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SEC 1(2)(3) FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-I-00016961.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a failure of one SEC.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-I-00018502.0002001 / 21 MAR 16
SEC (AFFECTED)....................................................................................................... OFF THEN ON
IF UNSUCCESSFUL:
SEC (AFFECTED).................................................................................................................. OFF
L2
Associated spoilers are lost.
If all spoilers are inoperative (3 SECs failed), roll direct law and pitch alternate law become
active.
L1
SPD BRK (IF SEC 1 AFFECTED)..........................................................................DO NOT USE
L2
VLS would not be corrected, if speed brakes 2 extend (no speed brake position sent to FACs).
L1
If SEC 1 + 2 + 3 fail
ASSOCIATED PROCEDURES
F/CTL ALTN LAW
PROT LOST
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AA →
PRO-ABN-F_CTL P 40/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SEC 1(2)(3) FAULT (Cont'd)
Ident.: PRO-ABN-F_CTL-I-00018504.0004001 / 01 JUN 16
L12
STATUS
SPD BRK...........................................................DO NOT USE
(If SEC 1 is affected.)
If SEC 1 + 2 + 3 fail:
FOR LDG......................................................USE FLAP 3
APPR SPD..................................................VREF + 10KT
LDG DIST PROC......................................................... APPLY
(If SEC 1 + 2 + 3 fail).
ALTN LAW: PROT LOST
If no AP engaged
and
SEC 1 + 2 + 3 fail.
WHEN L/G DN: DIRECT LAW
If SEC 1 + 2 + 3 fail. In such a case, the LGCIU
information can no longer be sent to the ELAC . For the
activation of DIRECT law, the ELAC uses the condition
“slats and flaps in CONF 2”, instead of “landing gear
down”.
If AP engaged
and
SEC 1 + 2 + 3 fail.
WHEN L/G DN AND AP OFF: DIRECT LAW
If SEC 1 + 2 + 3 fail. In such a case, the LGCIU
information can no longer be sent to the ELAC . For the
activation of DIRECT law, the ELAC uses the condition
“slats and flaps in CONF 2”, instead of “landing gear
down”.
(1)
(2)
(3)
INOP SYS
(1)
F/CTL PROT
SPLR (associated)
SEC (affected)
REVERSER 1(2)
AUTO BRK
(2)
(3)
STEEP APPR
ROW/ROP
(4)
(If SEC 1 + 2 + 3 fail)
(If SEC 1 + 2 fail, reverser 1 is not available for landing. If SEC 1 + 3 fail, reverser 2 is not
available for landing)
(If at least 2 SECs fail)
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AA →
PRO-ABN-F_CTL P 41/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SEC 1(2)(3) FAULT (Cont'd)
(4)
(If at least SEC 1 fails.)
F/CTL SIDESTICK PRIORITY
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-AM-00016983.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is failure in a sidestick priority logic circuit.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AA to AB →
PRO-ABN-F_CTL P 42/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SIDESTICK PRIORITY (Cont'd)
Ident.: PRO-ABN-F_CTL-AM-00018509.0001001 / 21 MAR 16
CHECK PRIORITY LOGIC
L2
L1
Check the integrity of flight control priority, as follows (not displayed on ECAM) :
ELAC 1........................................................................................................................ OFF THEN ON
L2
Note:
L1
ELAC 2........................................................................................................................ OFF THEN ON
If the warning disappears:
CAPT TAKE OVER pb..................................................................... PRESS (at least 3 seconds)
L2
When the ELAC 1 computer is reset on ground, the pitch trim returns to the ground setting
position (0 °).
Check that the :
‐ Aural “priority left” message is activated.
‐ F/O red arrow light is on.
CAPT TAKE OVER pb..................................................................................................RELEASE
F/O TAKE OVER pb.........................................................................PRESS (at least 3 seconds)
Check that the:
‐ Aural “priority right” message is activated
‐ CAPT red arrow light is on.
F/O TAKE OVER pb..................................................................................................... RELEASE
Check that the warning does not reappear.
Note:
There is no need to move the sidestick for the check.
If the warning does not disappear, or if the warning reappears after the above check:
Maintenance action is due.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AB
PRO-ABN-F_CTL P 43/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SLAT(FLAP) TIP BRK FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-AN-00016996.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is failure of one wing tip brake on slats or flaps, or failure of one
wing tip brake solenoid on slats, or flaps.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-AN-00018510.0001001 / 21 MAR 16
Crew awareness.
F/CTL SLATS AND FLAPS FAULT IN CONF 0
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-C-00018511.0001001 / 22 MAR 17
FLAPS LEVER.....................................................................................................................RECYCLE
If both slat channels fail:
ASSOCIATED PROCEDURES
F/CTL ALTN LAW
(PROT LOST)
MAX SPEED...................................................................................................................... 320 KT
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AC to AD →
PRO-ABN-F_CTL P 44/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SLATS AND FLAPS FAULT IN CONF 0 (Cont'd)
Ident.: PRO-ABN-F_CTL-C-00018512.0002001 / 22 MAR 17
L12
STATUS
INOP SYS
MAX SPEED................................................................ 320 KT
ALTN LAW: PROT LOST
F/CTL PROT
SLATS
FLAPS
APPR PROC
FOR LDG............................................................ USE FLAP 1
With FLAPS lever set at 1, AP /FD GO AROUND mode is
available.
CTR TK PUMPS............................................................... OFF
GPWS FLAP MODE......................................................... OFF
AP 1+2
A/THR
(1)
(2)
(2)
Moreover, both FDs are lost
(2)
(2)
CAT 2
STEEP APPR
APPR SPD........................................................ VREF +60 KT
Approach with A/THR in selected mode is recommended.
If both slat channels fail:
WHEN L/G DN: DIRECT LAW
AT 300 FT AGL:
TARGET SPD............................................. VREF +50 KT
Reduce speed between 500 ft and 300 ft to reach VREF
+50 kt at runway threshold, and disconnect A/THR , as
the target speed may be below VLS.
LDG DIST PROC...................................................APPLY
Only in case of FLAPS FAULT:
ENG 1 APPR IDLE ONLY
ENG 2 APPR IDLE ONLY
(1)
(2)
(If both slat channels fail.)
(If both slat or flap channels fail.)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AD
PRO-ABN-F_CTL P 45/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SLATS FAULT/LOCKED
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-B-00018517.0006001 / 22 MAR 17
If slats locked:
WING TIP BRK ON
L2
MAX SPEED........................ REFER TO PRO-ABN-F_CTL F/CTL FLAPS/SLATS FAULT/LOCKED
Speed is limited to the VFE corresponding to the next slat position.
L1
If slats not locked:
FLAPS LEVER.............................................................................................................. RECYCLE
L2
Return to the previous selection, then back to the desired position.
L1
L2
If slats extended:
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
If unsuccessful:
L1
L12
L2
L1
L2
Refer to PRO-ABN-F_CTL [QRH] Landing with Slats or Flaps Jammed.
The autopilot may be used down to 500 ft AGL. As it is not tuned for the abnormal
configurations, its behavior could be less than optimum and must be monitored.
Note:
If there is a SLATS FAULT after both slat channels fail, alternate law becomes active
(Refer to PRO-ABN-F_CTL F/CTL ALTN LAW).
If slats not at zero:
FUEL MODE SEL............................................................................................................MAN
To allow CTR TK feeding.
CTR TK PUMPS.....................................................................................................AS RQRD
Set CTR TK PUMPS pb to OFF when CTR TK is empty or during approach.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AE →
PRO-ABN-F_CTL P 46/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SLATS FAULT/LOCKED (Cont'd)
Ident.: PRO-ABN-F_CTL-B-00018518.0004001 / 22 MAR 17
L12
STATUS
INOP SYS
APPR PROC
FOR LDG............................................................ USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder.
CTR TK PUMPS............................................................... OFF
GPWS LDG FLAP 3...........................................................ON
APPR SPD.................................................................. REFER
TO PRO-ABN-F_CTL F/CTL FLAPS/SLATS FAULT/LOCKED
LDG DIST PROC......................................................... APPLY
F/CTL PROT
SLATS
AP 1+2
(1)
(1)
A/THR
(1)
CAT 2
(1)
Moreover, both FDs are lost
(1)
STEEP APPR
GLS AUTOLAND
(1)
CTR TK FEED: MAN ONLY
If both slat channels fail, or slats are locked in clean
configuration and flaps are at, or above, CONF 2:
ALTN LAW: PROT LOST
WHEN L/G DN: DIRECT LAW
FUEL CONSUMPT INCRSD
(2)
See
FMS PRED UNRELIABLE
(3)
See
(1)
(2)
(3)
(If both slat channels fail.)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS chapter in order to find the applicable Fuel
Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AE
PRO-ABN-F_CTL P 47/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SLAT SYS 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-D-00016995.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is failure of slat channel in one SFCC.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-D-00011751.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-F_CTL-D-00011752.0001001 / 18 AUG 10
STATUS
SLATS SLOW
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AF
PRO-ABN-F_CTL P 48/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SPD BRK 2 (3+4) FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-W-00016980.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when speedbrake lever transducers to SEC 3 (1) failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-W-00018519.0001001 / 21 MAR 16
If SPD BRK 3+4 affected:
SPD BRK................................................................................................................ DO NOT USE
L2
Do not use speedbrakes since it is not efficient to use only surfaces n° 2, and would active the
SPD BRK DISAGREE caution.
Ident.: PRO-ABN-F_CTL-W-00018520.0001001 / 21 MAR 16
STATUS
If SPD BRK 3+4 affected:
SPD BRK.................................................... DO NOT USE
LDG DIST PROC......................................................... APPLY
(1)
INOP SYS
SPD BRK (affected)
STEEP APPR
(1)
(if SPD BRK 3 and 4 are affected)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AG
PRO-ABN-F_CTL P 49/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SPD BRK DISAGREE
(SURFACES 3+4 AFFECTED)
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-T-00016970.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a position disagree between surfaces and lever position.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-T-00018521.0001001 / 21 MAR 16
SPD BRK LEVER................................................................................................................RETRACT
SPD BRK.......................................................................................................................DO NOT USE
Ident.: PRO-ABN-F_CTL-T-00018522.0001001 / 21 MAR 16
STATUS
SPD BRK...........................................................DO NOT USE
INOP SYS
SPD BRK 3+4
STEEP APPR
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AH
PRO-ABN-F_CTL P 50/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SPD BRK DISAGREE
(SURFACES 2+3+4 AFFECTED)
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-U-00018907.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a position disagree between surfaces and lever position.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-U-00018523.0001001 / 21 MAR 16
SPD BRK LEVER................................................................................................................RETRACT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AI
PRO-ABN-F_CTL P 51/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SPD BRK FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-V-00016971.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when speedbrake lever transducers to SEC 1 and 3 failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-V-00018534.0001001 / 21 MAR 16
L2
L1
In addition, associated ground spoilers are available only through reverse selection.
Crew awareness.
Ident.: PRO-ABN-F_CTL-V-00018535.0002001 / 22 MAR 17
STATUS
SPD BRK...........................................................DO NOT USE
(1)
INOP SYS
STEEP APPR
(1)
(if SPD BRK 3 or 4 are affected)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AJ
PRO-ABN-F_CTL P 52/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SPD BRK STILL OUT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-AO-00016972.0002001 / 21 MAR 16
ANNUNCIATIONS
Flight Phase Inhibition:
Ident.: PRO-ABN-F_CTL-AO-00011810.0014001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AK
PRO-ABN-F_CTL P 53/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SPLR FAULT
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-R-00016976.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a loss of one or more spoilers.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AL →
PRO-ABN-F_CTL P 54/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SPLR FAULT (Cont'd)
Ident.: PRO-ABN-F_CTL-R-00018536.0003001 / 22 MAR 17
L2
Note:
L1
If one or more spoilers are fully extended:
L2
L1
L2
L1
L2
L1
If heavy vibrations are felt, CONF 3 may be used for landing in order to reduce the
buffeting.
Current Flight Level (FL) may not be maintained due to increased drag. Maintain a cruise FL as
high as possible.
OPT SPD................................................................................................................. G DOT+10KT
Whenever possible, target green dot speed +10 kt to minimize fuel consumption. However, if
buffet is encountered at GDOT speed +10 kt, increase speed to fly out of buffet condition.
AP............................................................................................................................DO NOT USE
Depending on the failed spoiler position, the AP may not have enough authority to counteract
the roll induced by spoiler runaway.
SPD BRK (IF SPOILERS 3+4 AFFECTED).................................................................. DO NOT USE
Do not use speedbrakes, since using only surfaces N° 2 is not efficient and would activate the SPD
BRK DISAGREE caution.
If one or more spoilers are extended:
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AL →
PRO-ABN-F_CTL P 55/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL SPLR FAULT (Cont'd)
Ident.: PRO-ABN-F_CTL-R-00018544.0004001 / 21 MAR 17
L12
STATUS
If one or more spoilers are fully extended:
AP............................................................... DO NOT USE
If spoilers 3+4 affected:
SPD BRK.................................................... DO NOT USE
APPR PROC
INOP SYS
SPLR (affected)
SPD BRK
(1)
STEEP APPR
(2)
If one or more spoilers are fully extended:
In clean configuration, if VLS is above VFENEXT, the flight
crew should deselect A/THR, decelerate to VFENEXT, and
select CONF 1 when below VFENEXT. When established
at CONF 1, the flight crew can reengage the A/THR and
use managed speed again.
FOR LDG......................................................USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3 ................................................... ON
APPR SPD : VREF + 10 KT
LDG DIST PROC......................................................... APPLY
FUEL CONSUMPT INCRSD
(3)
See
FMS PRED UNRELIABLE
(4)
See
(1)
(2)
(3)
(4)
(If spoilers 2+3+4 affected)
(if spoilers 3 and/or 4 affected)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS chapter in order to find the applicable Fuel
Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AL
PRO-ABN-F_CTL P 56/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL STABILIZER JAM
Applicable to: ALL
Ident.: PRO-ABN-F_CTL-X-00016973.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a loss of the electrical control of the stabilizer (with or without
jamming of the stabilizer).
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AM →
PRO-ABN-F_CTL P 57/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL STABILIZER JAM (Cont'd)
Ident.: PRO-ABN-F_CTL-X-00018545.0001001 / 22 MAR 17
L2
When the Flight Control Computers detect a loss of electrical control of the stabilizer, pitch control
law reverts to alternate law. Depending on the type of failure, the MAN PITCH TRIM may still be
available.
L1
MAN PITCH TRIM................................................................................................................... CHECK
The force needed on the PITCH TRIM wheel may be higher than during pre-takeoff manual setting.
L2
L1
IF MAN TRIM AVAIL:
TRIM FOR NEUTRAL ELEV
L2
If manual pitch trim is available, trim to maintain the elevator at the zero position (indications on
F/CTL SD page).
L1
ASSOCIATED PROCEDURES
F/CTL ALTN LAW
(PROT LOST)
MAX SPEED.............................................................................................................................320 KT
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AM →
PRO-ABN-F_CTL P 58/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
F/CTL STABILIZER JAM (Cont'd)
Ident.: PRO-ABN-F_CTL-X-00018546.0003001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320 KT
APPR PROC:
FOR LDG............................................................ USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3...........................................................ON
Will be displayed when flaps in CONF 3
IF MAN TRIM NOT AVAIL:
WHEN CONF 3 AND VAPP:
L/G......................................................................... DN
Landing gear extension is delayed, in order to delay
the switching to direct law.
INOP SYS
F/CTL PROT
STABILIZER
ELAC PITCH
AP 1 + 2
CAT 2
GLS AUTOLAND
STEEP APPR
APPR SPD:...................................................... VREF + 10 KT
LDG DIST PROC......................................................... APPLY
ALTN LAW: PROT LOST
WHEN L/G DN: DIRECT LAW
At landing gear extension, control reverts to direct law in
pitch, as well as in roll. Refer to PRO-ABN-F_CTL F/CTL
DIRECT LAW.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AM
PRO-ABN-F_CTL P 59/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
F/CTL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-F_CTL P 60/60
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
[QRH] FUEL IMBALANCE
Ident.: PRO-ABN-FUEL-00011257.0002001 / 17 MAR 17
Applicable to: ALL
FOB.......................................................................................................................................... CHECK
Compare the FOB + FU , with the FOB at departure.
If the difference is significant, or if the FOB + FU decreases, suspect a fuel leak.
CAUTION
A fuel imbalance may indicate a fuel leak.
Do not apply this procedure, if a fuel leak is suspected.
Refer to PRO-ABN-FUEL [QRH] FUEL LEAK.
FUEL X FEED.................................................................................................................................ON
On lighter side and in center tank:
FUEL PUMPS......................................................................................................................... OFF
When fuel balanced:
FUEL PUMPS...........................................................................................................................ON
FUEL X FEED........................................................................................................................ OFF
Note:
There is no requirement to correct an imbalance, until the ECAM fuel advisory is
displayed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-FUEL P 1/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
[QRH] FUEL LEAK
Ident.: PRO-ABN-FUEL-00018665.0003001 / 17 MAR 17
Applicable to: ALL
A fuel leak may be detected, if:
‐ The sum of FOB and FU significantly less than FOB at engine start or is decreasing, or
‐ A passenger observes fuel spray from engine/pylon or wingtip/sharklet, or
‐ The total fuel quantity is decreasing at an abnormal rate, or
‐ A fuel imbalance is developing, or
‐ Fuel quantity in a tank is decreasing too fast (leak from engine/pylon, or hole in a tank), or
‐ The Fuel flow is excessive (leak from engine), or
‐ Fuel is smelt in the cabin.
‐ The destination EFOB turns to amber on the F-PLN (or on the FUEL PRED) page, or
‐ ”DEST EFOB BELOW MIN” appears on the MCDU scratchpad.
If visibility permits, leak source may be identified by a visual check from the cabin.
WHEN A LEAK IS CONFIRMED
LAND ASAP
Leak from engine/pylon confirmed by excessive fuel flow or visual check:
THR LEVER (affected engine)...........................................................................................IDLE
ENG MASTER (affected engine)........................................................................................OFF
FUEL X FEED........................................................................................................... AS RQRD
If the leak stops, the crossfeed valve can now be opened to re-balance fuel quantity, or to
enable use of fuel from both wings.
DO NOT RESTART AFFECTED ENGINE
Leak from engine/pylon not confirmed or leak not located:
Stop any fuel transfer, and then monitor the depletion rate of each inner tank, to determine if
the leak is from an engine or a wing, or from the Center tank, or the APU feeding line.
FUEL X FEED...........................................................................................MAINTAIN CLOSED
The crossfeed valve must remain closed to prevent the leak from affecting both sides.
CTR TK PUMP 1................................................................................................................ OFF
CTR TK PUMP 2................................................................................................................ OFF
Each engine is fed via its associated inner tank only.
INNER TANK FUEL QUANTITIES........................................................................... MONITOR
Monitor the depletion rate of each inner tank.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-ABN-FUEL P 2/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
[QRH] FUEL LEAK (Cont'd)
If one inner tank depletes faster than other by at least 300 kg (660 lb) in less than
30 min:
An engine leak may still be suspected. Therefore:
THR LEVER (engine on leaking side)........................................................................ IDLE
ENG MASTER (engine on leaking side)......................................................................OFF
CTR TK PUMP 1........................................................................................................... ON
CTR TK PUMP 2........................................................................................................... ON
FUEL LEAK........................................................................................................ MONITOR
If leak stops:
ENGINE LEAK CONFIRMED
FUEL X FEED.............................................................................................. AS RQRD
DO NOT RESTART AFFECTED ENGINE
If leak continues (after engine shutdown):
WING LEAK SUSPECTED
ENGINE RESTART....................................................................................CONSIDER
CAUTION
Do not apply the FUEL IMBALANCE procedure. Approach and
landing can be done, even with one full wing/one empty wing.
If both inner tanks deplete at a similar rate:
LEAK FROM CENTER TANK OR APU FEEDING LINE SUSPECTED
If fuel smell in cabin:
APU........................................................................................................................ OFF
This prevents additional fuel loss through the APU feeding line.
When fuel quantity in one inner tank less than 3 000 kg (6 600 lb):
CTR TK PUMP 1.....................................................................................................ON
CTR TK PUMP 2.....................................................................................................ON
For landing: DO NOT USE REVERSERS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-ABN-FUEL P 3/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
[QRH] GRAVITY FUEL FEEDING
Ident.: PRO-ABN-FUEL-00011261.0001001 / 17 MAR 17
Applicable to: ALL
ENG MODE SEL............................................................................................................................IGN
AVOID NEGATIVE G FACTOR
MAX FL: GRAVITY FEED CEILING
‐
‐
‐
‐
Current FL if flight time above FL 300 > 30 min.
FL 300 if flight time above FL 300 < 30 min.
Highest of FL 150 or 7 000 ft above takeoff airport if FL 300 never exceeded.
FL 100 for JET B.
When reaching gravity feed ceiling:
FUEL X FEED........................................................................................................................ OFF
If no fuel leak and with one engine running (fed by gravity):
FUEL X FEED.......................................................................................................................... ON
BANK ANGLE................................................................... 1° WING DOWN ON LIVE ENG SIDE
The fuel from the wing tank on the engine running side is used.
RUDDER TRIM.......................................................................................................................USE
Use rudder trim to maintain constant course and neutral stick.
When fuel imbalance reaches 1 000 kg (2 200 lb):
BANK ANGLE....................................................2° or 3° WING DOWN ON LIVE ENG SIDE
Use fuel from the opposite wing tank, until fuel imbalance is reduced to 0.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-FUEL P 4/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL ACT XFR FAULT
Applicable to: ALL
Ident.: PRO-ABN-FUEL-R-00016820.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The ACT quantity > 250 kg (550 lb) and
‐ The CTR TK quantity < 3 000 kg (6 600 lb).
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PRO-ABN-FUEL P 5/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL ACT XFR FAULT (Cont'd)
Ident.: PRO-ABN-FUEL-R-00017614.0001001 / 21 MAR 16
ACT...............................................................................................................................................FWD
IF NECESSARY:
DESCEND TO FL270
L2
L1
Note:
‐ ACT transfer rate depends on altitude and on remaining ACT fuel quantity.
‐ If ACT transfer is uncertain, set the ACT pb to AUTO to avoid pump dry running.
‐ ACT pb can be set back to FWD at lower Flight Level to recover remaining ACT
fuel.
WHEN ACT EMPTY:
ACT...................................................................................................................................... AUTO
For A321 aircraft equipped with 1 ACT :
ACT UNUSABLE (IF AUTOMATIC AND MANUAL MODES ARE FAILED)
For aircraft equipped with 2 ACTs :
IF NO XFR:
ACT UNUSABLE
PROC........................................................................................................................... APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PRO-ABN-FUEL P 6/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL ACT PUMP LO PR
Applicable to: ALL
Ident.: PRO-ABN-FUEL-BB-00016811.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the ACT pump is in low pressure.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-BB-00018877.0001001 / 21 MAR 16
ACT LO LVL
L2
Note:
L1
ACT................................................................................................................................................OFF
Displayed if ACT is empty.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-FUEL P 7/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL APU LP VALVE FAULT
Applicable to: ALL
Ident.: PRO-ABN-FUEL-BC-00016826.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the valve position disagrees with the selected position.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-BC-00017633.0002001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-ABN-FUEL P 8/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL AUTO FEED FAULT
Applicable to: ALL
Ident.: PRO-ABN-FUEL-Q-00016698.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ CTR TK quantity > 250 kg (550 lb) and left or right wing tanks quantity < 5 000 kg (11 000
lb), or
‐ CTR TK pumps do not stop after slat extension or CTR TK level is low.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G→
PRO-ABN-FUEL P 9/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL AUTO FEED FAULT (Cont'd)
Ident.: PRO-ABN-FUEL-Q-00017666.0001001 / 21 MAR 16
L2
FUEL MODE SEL.........................................................................................................................MAN
The center tank pumps will run and feed the engines.
L1
Fuel in one wing tank < 5 000 kg (11 000 lb ) and in center tank > 250 kg (550 lb ):
CTR TK PUMP 1......................................................................................................................ON
CTR TK PUMP 2......................................................................................................................ON
L2
When the center tank is empty, CTR TK PUMP LO PR alert will come on.
For aircraft equipped with CFM engines only : If the center tank is not empty at slat extension,
CTR TK PUMPs should be switched OFF. This action will prevent a possible wing tank overflow
on ground, due to IDG fuel recirculation.
L1
CTR TK PUMPS running after slat extension, or LO LVL in center tank:
CTR TK PUMP 1....................................................................................................................OFF
CTR TK PUMP 2....................................................................................................................OFF
Ident.: PRO-ABN-FUEL-Q-00018882.0001001 / 21 MAR 16
STATUS
CTR TK FEED : MAN ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-ABN-FUEL P 10/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL CTR TK PUMP 1(2) LO PR
Applicable to: ALL
Ident.: PRO-ABN-FUEL-M-00016843.0001001 / 21 MAR 16
ANNUNCIATIONS
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-M-00018914.0003001 / 21 MAR 16
IF NO FUEL LEAK:
FUEL X FEED.......................................................................................................................... ON
CTR TK PUMP (AFFECTED)....................................................................................................... OFF
L2
A fuel imbalance may occur, if the performance of the pumps of one wing is different from that of
the other wing, and the CTR TK PUMP that is not affected stops automatically because:
‐ The L(R) INR TK is full, or
‐ The CTR TK is empty.
In this case, apply the FUEL IMBALANCE procedure, as required.
L1
WHEN CTR TK EMPTY:
FUEL X FEED........................................................................................................................ OFF
L2
When the CTR TK is empty, the X FEED pb-sw must be turned off, to avoid a possible fuel
imbalance.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H→
PRO-ABN-FUEL P 11/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL CTR TK PUMP 1(2) LO PR (Cont'd)
Ident.: PRO-ABN-FUEL-M-00018918.0002001 / 21 MAR 16
STATUS
WHEN CTR TK EMPTY:
FUEL X FEED............................................................ OFF
INOP SYS
CTR TK PUMP 1(2)
FUEL CTR TK PUMPS LO PR
Applicable to: ALL
Ident.: PRO-ABN-FUEL-N-00016845.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the pressure of the CTR TK pumps is low.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← H to I →
PRO-ABN-FUEL P 12/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL CTR TK PUMPS LO PR (Cont'd)
Ident.: PRO-ABN-FUEL-N-00011221.0003001 / 30 MAR 12
L2
Set FUEL MODE SEL pb-sw to MAN, to avoid the possible triggering of the FUEL CTR TK PUMPS
OFF ECAM caution.
CTR TK PUMP 1.......................................................................................................................... OFF
CTR TK PUMP 2.......................................................................................................................... OFF
FUEL X FEED............................................................................................................................... OFF
CTR TK UNUSABLE
L2 Gravity feeding from the center tank is not possible (no by-pass valve fitted on the center tank
pumps).
L1
Ident.: PRO-ABN-FUEL-N-00011222.0001001 / 13 AUG 10
STATUS
INOP SYS
CTR TK FUEL UNUSABLE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
CTR TK PUMPS
←I
PRO-ABN-FUEL P 13/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL CTR TK PUMPS OFF
Applicable to: ALL
Ident.: PRO-ABN-FUEL-BE-00016846.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both CTR TK PUMP 1 pb-sw and CTR TK PUMP 2 pb-sw are at OFF
with no failure.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-BE-00011260.0002001 / 10 JAN 11
L2
L1
The center tank pumps pushbuttons are OFF, with slats retracted.
CTR TK PUMP 1............................................................................................................................ ON
CTR TK PUMP 2............................................................................................................................ ON
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J
PRO-ABN-FUEL P 14/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL ENG 1(2) LP VALVE OPEN
Applicable to: ALL
Ident.: PRO-ABN-FUEL-BG-00016814.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the valve remains in the open position.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-BG-00011217.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K
PRO-ABN-FUEL P 15/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL FQI CH 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-FUEL-BI-00016817.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when a FQI channel is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-BI-00011216.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
L
PRO-ABN-FUEL P 16/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) OUTER (INNER) TK HI TEMP
Applicable to: ALL
Ident.: PRO-ABN-FUEL-BL-00016825.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the fuel temperature:
‐
‐
‐
‐
In outer cell, is above 55 °C on ground
In outer cell, is above 60 °C in flight
In inner cell, is above 45 °C on ground
In inner cell, is above 54 °C in flight.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
M→
PRO-ABN-FUEL P 17/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) OUTER (INNER) TK HI TEMP (Cont'd)
Ident.: PRO-ABN-FUEL-BL-00011214.0001001 / 13 AUG 10
L2
This caution may spuriously trigger due to interference from communication equipment.
Therefore, the flight crew should wait 2 min while the fuel temperature measurement is updated.
After 2 min, if the ECAM caution has not disappeared, the flight crew must apply the following
procedure:
L1
GALLEY......................................................................................................................................... OFF
Reducing electrical loads reduce heat emitted by IDG.
L2
L1
On the ground:
LIMITED TAXI TIME
If temp reaches 60° C in outer cell or 54° C in inner cell:
DELAY T.O.
ENG MASTER (AFFECTED SIDE)................................................................................. OFF
In flight:
ENG F. FLOW (AFFECTED SIDE)............................................................................. INCREASE
L2
Disconnect autothrust. Adjust the thrust lever to increase fuel flow through the IDG oil heat
exchanger and decrease the temperature of the fuel returning to the outer cell.
L1
L2
L1
IF TEMP ABV 65 DEG C in outer cell or 57 DEG C in inner cell:
APU.........................................................................................................................AS RQRD
APU if available may be started and APU GEN used to allow IDG disconnection.
If opposite GEN avail:
IDG (AFFECTED SIDE).............................................................................................OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←M
PRO-ABN-FUEL P 18/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) OUTER (INNER) TK LO TEMP
Applicable to: ALL
Ident.: PRO-ABN-FUEL-BM-00016827.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the fuel temperature is approximately below -43 °C.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-BM-00011208.0001001 / 25 FEB 14
On the ground before takeoff:
DELAY T.O
L2
Do not takeoff until temperatures are within limits.
L1
In flight:
Crew awareness.
L2
Consider descending to a lower altitude and/or increasing Mach to increase TAT.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
N
PRO-ABN-FUEL P 19/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) OUTER XFR CLOSED
Applicable to: ALL
Ident.: PRO-ABN-FUEL-V-00016829.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both transfer valves remain closed after inner tank reaches the low
level.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-V-00014879.0006001 / 07 MAR 13
Note:
When fuel quantity in affected wing reaches low level, corresponding FUEL WING TK LO
LVL warning is triggered.
L (R) OUTER TK UNUSABLE
Ident.: PRO-ABN-FUEL-V-00014881.0006001 / 07 MAR 13
STATUS
L (R) OUTER TK UNUSABLE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
O
PRO-ABN-FUEL P 20/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) OUTER XFR OPEN
Applicable to: ALL
Ident.: PRO-ABN-FUEL-W-00016831.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when either transfer valve opens before inner tank reaches low level.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-W-00014882.0006001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-FUEL-W-00014883.0006001 / 07 MAR 13
STATUS
INOP SYS
L (R) CELL VALVE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
P
PRO-ABN-FUEL P 21/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) TK PUMP 1(2) LO PR
Applicable to: ALL
Ident.: PRO-ABN-FUEL-D-00016832.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the pressure of one tank pump is low.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-D-00011177.0002001 / 13 AUG 10
TK PUMP (AFFECTED)................................................................................................................OFF
L2
Note:
Aircraft altitude must be limited to 35 000 ft if a single fuel pump feeds both engines with
hot JET B (JP4) fuel (fuel temperature above 30 °C).
Ident.: PRO-ABN-FUEL-D-00011178.0001001 / 13 AUG 10
STATUS
INOP SYS
TK PUMP (affected)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Q
PRO-ABN-FUEL P 22/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) TK PUMP 1 + 2 LO PR
(CENTER TANK EMPTY)
Applicable to: ALL
Ident.: PRO-ABN-FUEL-C-00018184.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the pressure of the tank pumps is low.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
R→
PRO-ABN-FUEL P 23/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) TK PUMP 1 + 2 LO PR (Cont'd)
(CENTER TANK EMPTY)
Ident.: PRO-ABN-FUEL-C-00017648.0004001 / 21 MAR 16
IF NO FUEL LEAK:
FUEL X FEED (IF ABOVE FL150).......................................................................................... ON
ENG MODE SEL............................................................................................................................IGN
The selection of continuous relight protects against flame-out, caused by possible fuel supply
surging.
L1 TK PUMP 1 (AFFECTED).............................................................................................................OFF
TK PUMP 2 (AFFECTED).............................................................................................................OFF
WHEN TK (affected) FUEL RQRD:
TK (AFFECTED) FEED.......................................................................................... GRVTY ONLY
L2
Apply GRVTY FUEL FEED procedure, (Refer to PRO-ABN-FUEL [QRH] GRAVITY FUEL
FEEDING).
Fuel from the affected tank may be used immediately if there is no ceiling limitation for gravity
fuel feeding.
L2
L1
L2
L1
L2
L1
L2
FUEL X FEED (IF BELOW FL150)...............................................................................................OFF
If FUEL X FEED off:
As long as fuel X feed is closed, associated engine is fed by gravity only.
PROC: GRVTY FUEL FEEDING
Apply GRVTY FUEL FEED procedure, (Refer to PRO-ABN-FUEL [QRH] GRAVITY FUEL
FEEDING).
AVOID NEGATIVE G FACTOR
Avoiding negative g will prevent fuel surging and therefore reduce the risk of engine
malfunction.
Ident.: PRO-ABN-FUEL-C-00011175.0001001 / 13 AUG 10
STATUS
If FUEL X FEED off:
PROC:GRVTY FUEL FEEDING
AVOID NEGATIVE G FACTOR
INOP SYS
TK PUMPS (affected)
TK (AFFECTED) GRVTY FEED ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←R
PRO-ABN-FUEL P 24/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) TK PUMP 1 + 2 LO PR
(CENTER TANK NOT EMPTY)
Applicable to: ALL
Ident.: PRO-ABN-FUEL-B-00018196.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the pressure of the tank pumps is low.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-B-00011170.0003001 / 26 JUL 12
FUEL MODE SEL (IF CTR TK NOT FEEDING)..........................................................................MAN
Setting FUEL MODE SEL pb-sw to MAN will allow center tank pumps to run.
If the center tank is not empty at slat extension, CTR TK PUMPs should be switched OFF. This
action will prevent a possible wing tank overflow on ground, due to IDG fuel recirculation.
L1 TK PUMP 1 (AFFECTED).............................................................................................................OFF
TK PUMP 2 (AFFECTED).............................................................................................................OFF
WHEN TK (affected) FUEL RQRD:
L2
Apply the GRVTY FUEL FEEDING procedure, (Refer to PRO-ABN-FUEL [QRH] GRAVITY
FUEL FEEDING).
L2
L1
TK (AFFECTED) FEED.......................................................................................... GRVTY ONLY
PROC: GRVTY FUEL FEEDING
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
S→
PRO-ABN-FUEL P 25/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) TK PUMP 1 + 2 LO PR (Cont'd)
(CENTER TANK NOT EMPTY)
Ident.: PRO-ABN-FUEL-B-00011171.0001001 / 13 AUG 10
STATUS
INOP SYS
PROC:GRVTY FUEL FEEDING
TK (AFFECTED) GRVTY FEED ONLY
TK PUMPS (affected)
CTR TK FEED: MAN ONLY
FUEL L (R) WING TK LO LVL
Applicable to: ALL
Ident.: PRO-ABN-FUEL-E-00016837.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when left or right wing tanks quantity is below 750 kg (1 650 lb). This alert is
triggered by sensors getting dry and is independent from the fuel quantity indications.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← S to T →
PRO-ABN-FUEL P 26/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L (R) WING TK LO LVL (Cont'd)
Ident.: PRO-ABN-FUEL-E-00018927.0002001 / 21 MAR 16
If center tank not empty:
FUEL MODE SEL.................................................................................................................. MAN
IF NO FUEL LEAK AND FUEL IMBALANCE:
FUEL X FEED.......................................................................................................................... ON
TK PUMP 1 (ON SIDE WITH LO LVL).................................................................................. OFF
TK PUMP 2 (ON SIDE WITH LO LVL).................................................................................. OFF
L2
Note:
TK PUMP 1+2 (on side with LO LVL) LO PR warning will be triggered.
Ident.: PRO-ABN-FUEL-E-00018928.0001001 / 21 MAR 16
STATUS
INOP SYS
If center tank not empty:
CTR TK FEED: MAN ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
TK PUMPS
←T
PRO-ABN-FUEL P 27/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL L + R WING TK LO LVL
Applicable to: ALL
Ident.: PRO-ABN-FUEL-BO-00016810.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the low level is detected in both wing inner tanks. The alert is triggered
by sensors getting dry and is independent from the fuel quantity indications.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-BO-00018673.0003001 / 21 MAR 16
LAND ASAP
FUEL MODE SEL (IF CENTER TANK NOT EMPTY)................................................................. MAN
ALL TK PUMPS.............................................................................................................................. ON
L2 All pumps in center tank and in wing tanks will run.
L1
IF NO FUEL LEAK:
FUEL X FEED.......................................................................................................................... ON
IF GRVTY FEED:
FUEL X FEED........................................................................................................................ OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
U
PRO-ABN-FUEL P 28/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
FUEL X FEED VALVE FAULT
Applicable to: ALL
Ident.: PRO-ABN-FUEL-J-00016842.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the valve position disagrees with the selected position.
Flight Phase Inhibition:
Ident.: PRO-ABN-FUEL-J-00011206.0001001 / 25 FEB 14
L2
If valve failed open, maintain fuel balance with selective use of pumps.
If valve failed closed and if unable to maintain an acceptable balance, land as soon as possible.
L1
Crew awareness.
Ident.: PRO-ABN-FUEL-J-00011207.0001001 / 13 AUG 10
STATUS
INOP SYS
FUEL X FEED
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
V
PRO-ABN-FUEL P 29/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-FUEL P 30/30
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FWS
FLIGHT CREW
OPERATING MANUAL
[QRH] MULTIPLE UNDUE ECAM ALERTS
Ident.: TDU / PRO-ABN-FWS-00012928.0001001 / 17 MAR 17
Applicable to: ALL
Impacted DU: NONE
In the case of multiple undue ECAM alerts:
‐
‐
‐
‐
‐
ENG 1(2) N1 (N2 ) (EGT) OVER LIMIT, or
ENG 1(2) N1 (N2 ) (EGT )(EPR ) (FF) DISCREPANCY, or
NAV ATT (ALTI ) (HDG) DISCREPANCY, or
NAV FM /GPS POS DISAGREE, or
MINIMUM or HUNDRED ABOVE callouts.
Possibly associated with EFIS red flags, apply the procedure below:
AFFECTED PARAMETERS........................................................................................CROSSCHECK
Crosscheck the affected parameters on the E/WD , PFD , ND or on the related SD page to confirm
that the alerts are spurious.
If spurious alerts:
SWITCHING EIS DMC..................................................................................................... CAPT 3
DMC 3 replaces DMC 1. If the undue alerts stop, DMC 1 is the faulty DMC.
If unsuccessful :
SWITCHING EIS DMC...................................................................................................F/O 3
DMC 3 replaces DMC 2. If the undue alerts stop, DMC 2 is the faulty DMC.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-FWS P 1/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FWS
FLIGHT CREW
OPERATING MANUAL
FWS FWC 1 + 2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-FWS-H-00017311.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both FWC 1 and FWC 2 are failed, or when the communication
between the FWC and the EIS is lost.
Flight Phase Inhibition:
Ident.: PRO-ABN-FWS-H-00010055.0001001 / 14 FEB 13
MONITOR SYS
MONITOR OVERHEAD PANEL
NOT AVAIL
ECAM WARN
ALTI ALERT
STATUS
A/CALL OUT
MEMO
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-ABN-FWS P 2/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FWS
FLIGHT CREW
OPERATING MANUAL
FWS FWC 1 + 2 FAULT (Cont'd)
Ident.: PRO-ABN-FWS-H-00010056.0001001 / 14 FEB 13
L2
Other INOP SYS
CAT2
ECAM Cautions and Warnings, aural warnings, master caution and warning lights are lost.
ECAM system pages are still available. therefore check regularly (more often than usual)
cockpit panels for local warnings and ECAM system pages for system checks.
Check the general status of the systems for the DES /APPR preparation.
FWS FWC 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-FWS-G-00017310.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when either FWC 1 or, FWC 2 is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-FWS-G-00010059.0001001 / 10 AUG 10
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-ABN-FWS P 3/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FWS
FLIGHT CREW
OPERATING MANUAL
FWS FWC 1(2) FAULT (Cont'd)
Ident.: PRO-ABN-FWS-G-00010060.0001001 / 10 AUG 10
STATUS
INOP SYS
CAT 3 SINGLE ONLY
CAT 3 DUAL
FWC 1(2)
FWS OEB/FWC DISCREPANCY
Applicable to: ALL
Ident.: PRO-ABN-FWS-J-00017314.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when FWC 1 and FWC 2 do not have the same OEB s listed in their OEB
reminder database.
Flight Phase Inhibition:
Ident.: PRO-ABN-FWS-J-00010050.0001001 / 10 AUG 10
L2
OEB DATABASE................................................................................................................... XCHECK
This action is normally performed by maintenance.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
PRO-ABN-FWS P 4/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FWS
FLIGHT CREW
OPERATING MANUAL
FWS SDAC 1 + 2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-FWS-E-00017306.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both SDAC 1 and SDAC 2 are failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-FWS-E-00010053.0001001 / 10 AUG 10
MONITOR OVERHEAD PANEL
Amber cautions are lost. Aircraft status on the ECAM STATUS page is lost.
Only red warnings, engine and fuel parameters, and slat/flap positions are available on the upper
ECAM DU.
L1 ECAM ENG FUEL F/CTL WHEEL (L/G POS IND) SYS PAGES AVAIL.
L2
Ident.: PRO-ABN-FWS-E-00010054.0002001 / 10 AUG 10
STATUS
INOP SYS
SDAC 1 + 2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-FWS P 5/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FWS
FLIGHT CREW
OPERATING MANUAL
FWS SDAC 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-FWS-D-00017308.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
This alerts triggers when either SDAC 1 or, SDAC 2 is failed.
L2
Flight Phase Inhibition:
Ident.: PRO-ABN-FWS-D-00010051.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-FWS-D-00010052.0001001 / 10 AUG 10
L12
STATUS
INOP SYS
SDAC 1(2)
Note:
Although the ECAM may display some symbols and/or parameters in amber, this does
not always signify that additional systems are failed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-ABN-FWS P 6/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B ELEC PUMP LO PR OR OVHT
Applicable to: ALL
Ident.: PRO-ABN-HYD-T-00017137.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
LO PR: This alert triggers when the pump outlet pressure ≤1 450 PSI (the alert resets if
pressure ≥1 750 PSI).
OVHT: This alert triggers when the blue electric pump overheats.
Flight Phase Inhibition:
Note:
(a) The Flight Phase Inhibition 3 is only available for HYD B ELEC PUMP OVHT.
Ident.: PRO-ABN-HYD-T-00011661.0002001 / 27 NOV 12
BLUE ELEC PUMP....................................................................................................................... OFF
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
ASSOCIATED PROCEDURES
B SYS LO PR
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-ABN-HYD P 1/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B ELEC PUMP LO PR OR OVHT (Cont'd)
Ident.: PRO-ABN-HYD-T-00018313.0003001 / 21 MAR 17
L12
STATUS
INOP SYS
APPR PROC
HYD LO PR
IF BLUE OVHT OUT:
BLUE ELEC PUMP................................................. AUTO
BLUE HYD
SPLR 3
CAT 3 DUAL
B ELEC PUMP
STEEP APPR
LDG DIST PROC......................................................... APPLY
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
SLATS SLOW
CAT 3 SINGLE ONLY
(1)
(2)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-ABN-HYD P 2/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B RSVR LO AIR PR
Applicable to: ALL
Ident.: PRO-ABN-HYD-A-00017106.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the reservoir air pressure ≤ 22 PSI (the alert resets if pressure ≥
25 PSI).
This alert triggers when the reservoir air pressure ≤ 30 PSI (detected in flight but only displayed
on ground after landing).
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-A-00011602.0002001 / 05 MAR 13
IF PRESS FLUCTUATES:
BLUE ELEC PUMP.................................................................................................................OFF
ASSOCIATED PROCEDURES
B SYS LO PR
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-ABN-HYD P 3/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B RSVR LO AIR PR (Cont'd)
Ident.: PRO-ABN-HYD-A-00018312.0003001 / 21 MAR 17
L12
STATUS
INOP SYS
APPR PROC
The probability of cavitation increases with altitude.
Therefore, it may be possible to restore the system after
descending to a lower altitude.
HYD LO PR
BLUE ELEC PUMP........................................................AUTO
If sys not recovered:
LDG DIST PROC...................................................APPLY
BLUE HYD
SPLR 3
CAT 3 DUAL
B ELEC PUMP
STEEP APPR
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
SLATS SLOW
CAT 3 SINGLE ONLY
(1)
(2)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-ABN-HYD P 4/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B RSVR LO LVL
Applicable to: ALL
Ident.: PRO-ABN-HYD-C-00017144.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
The alert triggers when the fluid quantity < 2.4 l (0.63 US Gal).
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-C-00011606.0002001 / 05 MAR 13
BLUE ELEC PUMP....................................................................................................................... OFF
ASSOCIATED PROCEDURES
B SYS LO PR
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PRO-ABN-HYD P 5/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B RSVR LO LVL (Cont'd)
Ident.: PRO-ABN-HYD-C-00018314.0003001 / 21 MAR 17
L12
STATUS
LDG DIST PROC......................................................... APPLY
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
SLATS SLOW
CAT 3 SINGLE ONLY
(1)
(2)
INOP SYS
BLUE HYD
SPLR 3
CAT 3 DUAL
EMER GEN
B ELEC PUMP
STEEP APPR
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PRO-ABN-HYD P 6/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B RSVR OVHT
Applicable to: ALL
Ident.: PRO-ABN-HYD-B-00017108.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the fluid temperature ≥93 °C (the alert resets if temperature ≤88 °C).
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-B-00011604.0002001 / 05 MAR 13
BLUE ELEC PUMP....................................................................................................................... OFF
ASSOCIATED PROCEDURES
B SYS LO PR
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PRO-ABN-HYD P 7/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B RSVR OVHT (Cont'd)
Ident.: PRO-ABN-HYD-B-00018315.0003001 / 21 MAR 17
L12
STATUS
INOP SYS
APPR PROC
HYD LO PR
IF BLUE OVHT OUT:
BLUE ELEC PUMP................................................. AUTO
BLUE HYD
SPLR 3
CAT 3 DUAL
B ELEC PUMP
STEEP APPR
If sys not recovered:
LDG DIST PROC...................................................APPLY
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
SLATS SLOW
CAT 3 SINGLE ONLY
(1)
(2)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PRO-ABN-HYD P 8/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G ENG 1 PUMP LO PR
(PTU OPERATIVE)
Applicable to: ALL
Ident.: PRO-ABN-HYD-N-00017136.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the pump outlet pressure ≤1 750 PSI (the alert resets if pressure
≥2 200 PSI).
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-N-00011648.0001001 / 18 AUG 10
GREEN ENG 1 PUMP..................................................................................................................OFF
Ident.: PRO-ABN-HYD-N-00011649.0001001 / 17 MAR 11
STATUS
INOP SYS
G ENG 1 PUMP
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-HYD P 9/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G ENG 1 PUMP LO PR
(PTU INOPERATIVE)
Applicable to: ALL
Ident.: PRO-ABN-HYD-P-00018805.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the pump outlet pressure ≤1 750 PSI (the alert resets if pressure
≥2 200 PSI).
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-P-00011652.0001001 / 18 AUG 10
GREEN ENG 1 PUMP..................................................................................................................OFF
ASSOCIATED PROCEDURES
G SYS LO PR
SECONDARY FAILURES
*WHEEL
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PRO-ABN-HYD P 10/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G ENG 1 PUMP LO PR (Cont'd)
(PTU INOPERATIVE)
Ident.: PRO-ABN-HYD-P-00018316.0002001 / 21 MAR 16
STATUS
L/G.................................................................... GRVTY EXTN
LDG DIST PROC......................................................... APPLY
SLATS/FLAPS SLOW
CAT 3 SINGLE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
INOP SYS
GREEN HYD
SPLR 1+5
CAT 3 DUAL
AUTO BRK
NORM BRK
L/G RETRACT
REVERSER 1
PTU
G ENG 1 PUMP
YAW DAMPER 1
PRO-ABN-HYD P 11/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G RSVR LO AIR PR
Applicable to: ALL
Ident.: PRO-ABN-HYD-D-00017104.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the reservoir air pressure ≤22 PSI (the alert resets if air pressure
≥25 PSI).
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-D-00011609.0002001 / 05 MAR 13
IF PRESS FLUCTUATES:
PTU......................................................................................................................................... OFF
GREEN ENG 1 PUMP........................................................................................................... OFF
G ENG 1 PUMP LO PR
ASSOCIATED PROCEDURES
G SYS LO PR
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*WHEEL
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G→
PRO-ABN-HYD P 12/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G RSVR LO AIR PR (Cont'd)
Ident.: PRO-ABN-HYD-D-00018317.0007001 / 21 MAR 17
L12
STATUS
INOP SYS
APPR PROC
HYD LO PR
The probability of cavitation increases with altitude.
Therefore, it may be possible to restore the system after
descending to a lower altitude.
GREEN ENG 1 PUMP....................................................... ON
IF HYD NOT RECOVERED:
L/G..............................................................GRVTY EXTN
Refer to PRO-ABN-LG [QRH] L/G GRAVITY
EXTENSION
LDG DIST PROC...................................................APPLY
GREEN HYD
SPLR 1 + 5
CAT 3 DUAL
AUTO BRK
NORM BRK
L/G RETRACT
REVERSER 1
YAW DAMPER 1
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
ALTN Y BRK WITH A/SKID
SLATS/FLAPS SLOW
CAT 3 SINGLE ONLY
(1)
(2)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-ABN-HYD P 13/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G RSVR LO LVL
Applicable to: ALL
Ident.: PRO-ABN-HYD-F-00017142.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the fluid quantity < 3.5 l (0.92 US Gal).
Flight Phase Inhibition:
L1
Note:
The HYD G RSVR LO LVL alert is inhibited for the first 15 s of flight phase 5.
Ident.: PRO-ABN-HYD-F-00011614.0002001 / 05 MAR 13
PTU................................................................................................................................................OFF
GREEN ENG 1 PUMP..................................................................................................................OFF
G ENG 1 PUMP LO PR
ASSOCIATED PROCEDURES
G SYS LO PR
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*WHEEL
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H→
PRO-ABN-HYD P 14/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G RSVR LO LVL (Cont'd)
Ident.: PRO-ABN-HYD-F-00018320.0007001 / 21 MAR 17
L12
STATUS
L/G.................................................................... GRVTY EXTN
Refer to PRO-ABN-LG [QRH] L/G GRAVITY EXTENSION
LDG DIST PROC......................................................... APPLY
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
ALTN Y BRK WITH A/SKID
SLATS/FLAPS SLOW
CAT 3 SINGLE ONLY
(1)
(2)
INOP SYS
GREEN HYD
SPLR 1 + 5
CAT 3 DUAL
AUTO BRK
NORM BRK
L/G RETRACT
REVERSER 1
YAW DAMPER 1
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←H
PRO-ABN-HYD P 15/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G RSVR OVHT
Applicable to: ALL
Ident.: PRO-ABN-HYD-E-00017107.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the fluid temperature ≥93 °C (the alert resets if temperature ≤88 °C).
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-E-00011612.0002001 / 05 MAR 13
PTU................................................................................................................................................OFF
GREEN ENG 1 PUMP..................................................................................................................OFF
G ENG 1 PUMP LO PR
ASSOCIATED PROCEDURES
G SYS LO PR
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*WHEEL
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I→
PRO-ABN-HYD P 16/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G RSVR OVHT (Cont'd)
Ident.: PRO-ABN-HYD-E-00018321.0007001 / 02 MAY 17
L12
STATUS
INOP SYS
APPR PROC
HYD LO PR
IF GREEN OVHT OUT:
GREEN ENG 1 PUMP.................................................ON
IF HYD NOT RECOVERED:
L/G..............................................................GRVTY EXTN
Refer to PRO-ABN-LG [QRH] L/G GRAVITY
EXTENSION
LDG DIST PROC...................................................APPLY
GREEN HYD
SPLR 1 + 5
CAT 3 DUAL
AUTO BRK
NORM BRK
L/G RETRACT
REVERSER 1
YAW DAMPER 1
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
ALTN Y BRK WITH A/SKID
SLATS/FLAPS SLOW
CAT 3 SINGLE ONLY
(1)
(2)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I
PRO-ABN-HYD P 17/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y ELEC PUMP LO PR OR OVHT
Applicable to: ALL
Ident.: PRO-ABN-HYD-M-00017133.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
LO PR: This alert triggers when the yellow system pressure ≤1 450 PSI (the alert resets if
pressure ≥1 750 PSI) with:
‐ Y ELEC PUMP pb at ON
‐ Y ENG PUMP and PTU not available.
OVHT: This alert triggers when the yellow electric pump overheats.
Flight Phase Inhibition:
Note:
(a) The Flight Phase Inhibition 3 is only available for HYD Y ELEC PUMP OVHT.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J→
PRO-ABN-HYD P 18/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y ELEC PUMP LO PR OR OVHT (Cont'd)
Ident.: PRO-ABN-HYD-M-00019032.0003001 / 21 MAR 16
YELLOW ELEC PUMP................................................................................................................. OFF
ASSOCIATED PROCEDURES
Y SYS LO PR
BRK Y ACCU PR MONITOR
L2 This check is recommended to cover the case of a pipe rupture, which could lead to the
simultaneous loss of the hydraulic system and the accumulator fluid. If this occurs, the loss of the
accumulator should be observed on the indicator within 10 min. In that case: The only remaining
braking means is the normal braking using green pressure, the parking brake should not be used
since it is not available and the chocks should be in place before engine 1 shutdown.
L1 FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←J→
PRO-ABN-HYD P 19/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y ELEC PUMP LO PR OR OVHT (Cont'd)
Ident.: PRO-ABN-HYD-M-00018322.0004001 / 21 MAR 17
L12
STATUS
INOP SYS
APPR PROC
HYD LO PR
IF YELLOW OVHT OUT:
YELLOW ENG 2 PUMP...............................................ON
PTU..........................................................................AUTO
The above two lines are only displayed, in case of an
electrical pump overheat.
YELLOW HYD
SPLR 2+4
CAT 3 DUAL
N/W STRG
REVERSER 2
Y ELEC PUMP
YAW DAMPER 2
STEEP APPR
LDG DIST PROC......................................................... APPLY
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
FLAPS SLOW
CAT 3 SINGLE ONLY
(1)
(2)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←J
PRO-ABN-HYD P 20/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y ENG 2 PUMP LO PR
(PTU OPERATIVE)
Applicable to: ALL
Ident.: PRO-ABN-HYD-O-00017135.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the pump outlet pressure ≤1 750 PSI (the alert resets if pressure
≥2 200 PSI).
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-O-00011650.0001001 / 18 AUG 10
YELLOW ENG 2 PUMP................................................................................................................OFF
Ident.: PRO-ABN-HYD-O-00011651.0001001 / 18 AUG 10
STATUS
INOP SYS
Y ENG 2 PUMP
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K
PRO-ABN-HYD P 21/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y ENG 2 PUMP LO PR
(PTU INOPERATIVE)
Applicable to: ALL
Ident.: PRO-ABN-HYD-Q-00018806.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the pump outlet pressure ≤1 750 PSI (the alert resets if pressure
≥2 200 PSI).
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-Q-00011654.0001001 / 18 AUG 10
YELLOW ENG 2 PUMP................................................................................................................OFF
ASSOCIATED PROCEDURES
Y SYS LO PR
L2
Note:
If yellow system is affected, the yellow electrical pump may be used.
L1
SECONDARY FAILURES
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
L→
PRO-ABN-HYD P 22/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y ENG 2 PUMP LO PR (Cont'd)
(PTU INOPERATIVE)
Ident.: PRO-ABN-HYD-Q-00018323.0002001 / 21 MAR 16
L12
STATUS
LDG DIST PROC......................................................... APPLY
FLAPS SLOW
CAT 3 SINGLE
(1)
See
(1)
Note:
INOP SYS
YELLOW HYD
SPLR 2+4
CAT 3 DUAL
N/W STRG
REVERSER 2
PTU
Y ENG 2 PUMP
YAW DAMPER 2
STEEP APPR
Following a yellow hydraulic system failure, the parking brake may be inoperative due to
a yellow accumulator low pressure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←L
PRO-ABN-HYD P 23/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y RSVR LO AIR PR
Applicable to: ALL
Ident.: PRO-ABN-HYD-G-00017105.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the reservoir air pressure ≤ 22 PSI (the alert resets if pressure ≥
25 PSI).
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
M→
PRO-ABN-HYD P 24/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y RSVR LO AIR PR (Cont'd)
Ident.: PRO-ABN-HYD-G-00011626.0003001 / 27 NOV 12
IF PRESS FLUCTUATES:
PTU......................................................................................................................................... OFF
YELLOW ENG 2 PUMP......................................................................................................... OFF
YELLOW ELEC PUMP........................................................................................................... OFF
BRK Y ACCU PR MONITOR
This check is recommended to cover the case of a pipe rupture, which could lead to the
simultaneous loss of the hydraulic system and the accumulator fluid. If this occurs, the loss of the
accumulator should be observed on the indicator within 10 min. In that case : The only remaining
braking means is normal braking, using green pressure. The parking brake should not be used
since, it is not available. And, the chocks should be in place before Engine 1 shutdown.
L1 Y ENG 2 PUMP LO PR
L2
ASSOCIATED PROCEDURES
Y SYS LO PR
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←M→
PRO-ABN-HYD P 25/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y RSVR LO AIR PR (Cont'd)
Ident.: PRO-ABN-HYD-G-00018324.0007001 / 21 MAR 17
L2
The probability of cavitation increases with altitude.
Therefore, it may be possible to restore the system after descending to a lower altitude.
L12
STATUS
INOP SYS
APPR PROC
HYD LO PR
YELLOW ENG 2 PUMP..................................................... ON
If sys not recovered:
LDG DIST PROC...................................................APPLY
YELLOW HYD
SPLR 2 + 4
CAT 3 DUAL
N/W STRG
REVERSER 2
YAW DAMPER 2
STEEP APPR
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
FLAPS SLOW
CAT 3 SINGLE
(1)
(2)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←M
PRO-ABN-HYD P 26/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y RSVR LO LVL
Applicable to: ALL
Ident.: PRO-ABN-HYD-I-00017143.0002001 / 06 SEP 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the fluid quantity < 3.5 l (0.92 US Gal).
Flight Phase Inhibition:
L1
Note:
(a) The HYD Y RSVR LO LVL alert is inhibited for the first 15 s of flight phase 5.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
N→
PRO-ABN-HYD P 27/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y RSVR LO LVL (Cont'd)
Ident.: PRO-ABN-HYD-I-00011631.0003001 / 05 MAR 13
PTU................................................................................................................................................OFF
YELLOW ENG 2 PUMP................................................................................................................OFF
YELLOW ELEC PUMP................................................................................................................. OFF
BRK Y ACCU PR MONITOR
L2 This check is recommended to cover the case of a pipe rupture, which could lead to the
simultaneous loss of the hydraulic system and the accumulator fluid. If this occurs, the loss of the
accumulator should be observed on the indicator within 10 min. In that case: The only remaining
braking means is normal braking, using green pressure. The parking brake should not be used
since, it is not available. And, the chocks should be in place before Engine 1 shutdown.
L1 Y ENG 2 PUMP LO PR
ASSOCIATED PROCEDURES
Y SYS LO PR
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←N→
PRO-ABN-HYD P 28/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y RSVR LO LVL (Cont'd)
Ident.: PRO-ABN-HYD-I-00018326.0006001 / 21 MAR 17
L12
STATUS
LDG DIST PROC......................................................... APPLY
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
FLAPS SLOW
CAT 3 SINGLE
(3)
See
(1)
(2)
(3)
INOP SYS
YELLOW HYD
SPLR 2 + 4
CAT 3 DUAL
N/W STRG
REVERSER 2
CARGO DOOR
YAW DAMPER 2
STEEP APPR
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
Note:
Following a yellow hydraulic system failure, the parking brake may be inoperative due to
a yellow accumulator low pressure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←N
PRO-ABN-HYD P 29/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y RSVR OVHT
Applicable to: ALL
Ident.: PRO-ABN-HYD-H-00017109.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the fluid temperature ≥93 °C (the alert resets if temperature ≤88 °C).
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
O→
PRO-ABN-HYD P 30/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y RSVR OVHT (Cont'd)
Ident.: PRO-ABN-HYD-H-00011629.0003001 / 05 MAR 13
PTU................................................................................................................................................OFF
YELLOW ENG 2 PUMP................................................................................................................OFF
YELLOW ELEC PUMP................................................................................................................. OFF
BRK Y ACCU PR MONITOR
L2 This check is recommended to cover the case of a pipe rupture, which could lead to the
simultaneous loss of the hydraulic system and the accumulator fluid. If this occurs, the loss of the
accumulator should be observed on the indicator within 10 min. In that case: The only remaining
braking means is normal braking, using green pressure. The parking brake should not be used
since, it is not available. And, the chocks should be in place before Engine 1 shutdown.
L1 Y ENG 2 PUMP LO PR
ASSOCIATED PROCEDURES
Y SYS LO PR
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
SECONDARY FAILURES
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←O→
PRO-ABN-HYD P 31/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD Y RSVR OVHT (Cont'd)
Ident.: PRO-ABN-HYD-H-00018327.0007001 / 21 MAR 17
L12
STATUS
INOP SYS
APPR PROC
HYD LO PR
IF YELLOW OVHT OUT:
YELLOW ENG 2 PUMP...............................................ON
If not recovered:
LDG DIST PROC...................................................APPLY
YELLOW HYD
SPLR 2 + 4
CAT 3 DUAL
N/W STRG
REVERSER 2
YAW DAMPER 2
STEEP APPR
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
FLAPS SLOW
CAT 3 SINGLE
(1)
(2)
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←O
PRO-ABN-HYD P 32/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B+Y SYS LO PR
Applicable to: ALL
Ident.: PRO-ABN-HYD-L-00018917.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the blue and yellow systems pressure ≤1 450 PSI (the alert resets if
pressure ≥1 750 PSI).
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
P→
PRO-ABN-HYD P 33/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B+Y SYS LO PR (Cont'd)
Ident.: PRO-ABN-HYD-L-00018727.0002001 / 21 MAR 16
L2
Note:
If the yellow hydraulic system is lost due to low level, the “HYD PTU FAULT” ECAM
message may appear, and requests that the flight crew switches the PTU off.
LAND ASAP
L1
If yellow sys lost by ENG 2 PUMP LO PR:
YELLOW ELEC PUMP.............................................................................................................ON
If blue sys lost by ELEC PUMP LO PR:
RAT..................................................................................................................................MAN ON
L2
To extend the RAT, the flight crew must press the RAT MAN ON pb located on the Hydraulic
overhead panel.
L1
MIN RAT SPD....................................................................................................................140 KT
AFFECTED PUMPS......................................................................................................................OFF
MAX SPEED...........................................................................................................................320/0.77
L2
Note:
Flight controls remain in normal law.
MANEUVER WITH CARE
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
L2
If blue or yellow sys recovered:
L1
See procedure for single failure.
L1
If neither system recovered:
SECONDARY FAILURES
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←P→
PRO-ABN-HYD P 34/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B+Y SYS LO PR (Cont'd)
Ident.: PRO-ABN-HYD-L-00018342.0009001 / 21 MAR 17
L12
STATUS
MIN RAT SPD..............................................................140 KT
(If B PUMP LO PR)
MAX SPEED.............................................................. 320/0.77
MANEUVER WITH CARE
APPR PROC
DUAL HYD LO PR
(Line not displayed for dual LO LVL)
If sys lost by RSVR LO AIR PR:
In approach, system lost by RSVR LO AIR PR may be
recovered at low altitude.
RELATED PUMP......................................................... ON
If sys lost by RSVR OVHT:
INOP SYS
B+Y HYD
R ELEV
SPLR 2+3+4
SPD BRK
AP 1+2
N/W STRG
CARGO DOOR (If Y RSVR LO
LVL)
REVERSER 2
B ELEC PUMP
EMER GEN (If B RSVR LO LVL)
YAW DAMPER 2
CAT 2
GLS AUTOLAND
STEEP APPR
In approach, system lost by RSVR OVHT may be
recovered if OVHT indication disappears.
IF BLUE OVHT OUT:
BLUE ELEC PUMP...........................................AUTO
IF YELLOW OVHT OUT:
YELLOW ENG 2 PUMP........................................ ON
IF HYD NOT RECOVERED (line not displayed for dual
LO LVL):
For A321 aircraft:
FOR LDG............................................... USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3”
when CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3..............................................ON
L/G..............................................................GRVTY EXTN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←P→
Continued on the following page
PRO-ABN-HYD P 35/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD B+Y SYS LO PR (Cont'd)
Landing gear is extended by gravity to preserve green
system integrity Refer to PRO-ABN-LG [QRH] L/G
GRAVITY EXTENSION.
For A321 aircraft:
APPR SPD..................................................VREF +10 KT
LDG DIST PROC......................................................... APPLY
SLATS/FLAPS SLOW
(1)
See
FUEL CONSUMPT INCRSD
(2)
See
FMS PRED UNRELIABLE
(3)
See
(1)
(2)
(3)
Note:
Following a yellow hydraulic system failure, the parking brake may be inoperative due to
yellow accumulator low pressure.
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS - Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←P
PRO-ABN-HYD P 36/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G+B SYS LO PR
Applicable to: ALL
Ident.: PRO-ABN-HYD-J-00018920.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the green and blue systems pressure ≤1 450 PSI (the alert resets if
pressure ≥1 750 PSI).
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Q→
PRO-ABN-HYD P 37/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G+B SYS LO PR (Cont'd)
Ident.: PRO-ABN-HYD-J-00018349.0002001 / 22 MAR 17
L2
Note:
If the green hydraulic system is lost due to low level, the “HYD PTU FAULT” ECAM
message may appear, and requests the flight crew to switch the PTU off.
LAND ASAP
L1
If blue sys lost by ELEC PUMP LO PR:
RAT..................................................................................................................................MAN ON
MIN RAT SPD....................................................................................................................140 KT
AFFECTED PUMPS......................................................................................................................OFF
MANEUVER WITH CARE
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
ASSOCIATED PROCEDURES
L2
F/CTL ALTN LAW
(PROT LOST)
The flight control normal laws and associated protections are lost. Only load factor limitation is
furnished (alternate law without protection).
L1 MAX SPEED...........................................................................................................................320/0.77
L2 Speed is limited due to loss of high speed protection.
L1 SPD BRK.......................................................................................................................DO NOT USE
If blue sys recovered:
See procedure for single failure.
If blue sys not recovered:
Refer to PRO-ABN-F_CTL [QRH] Landing with Slats or Flaps Jammed.
SECONDARY FAILURES
*WHEEL
*F/CTL
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←Q→
PRO-ABN-HYD P 38/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G+B SYS LO PR (Cont'd)
Ident.: PRO-ABN-HYD-J-00018350.0013001 / 22 MAR 17
L12
STATUS
MIN RAT SPD (IF RAT OUT)...................................... 140 KT
(If B PUMP LO PR)
MAX SPEED.............................................................. 320/0.77
MANEUVER WITH CARE
SPD BRK...........................................................DO NOT USE
APPR PROC
DUAL HYD LO PR
(Line not displayed for a double LO LVL):
If sys lost by RSVR LO AIR PR:
RELATED PUMPS....................................................... ON
If sys lost by RSVR OVHT:
IF BLUE OVHT OUT:
BLUE ELEC PUMP...........................................AUTO
INOP SYS
G+B HYD
F/CTL PROT
L ELEV
L+R AIL
SPLR 1+3+5
SLATS
AP 1+2
AUTO BRK
NORM BRK
L/G RETRACT
REVERSER 1
EMER GEN (If B RSVR LO LVL)
B ELEC PUMP
YAW DAMPER 1
CAT 2
GLS AUTOLAND
STEEP APPR
IF GREEN OVHT OUT:
GREEN ENG 1 PUMP.......................................... ON
IF HYD NOT RECOVERED (line not displayed for a
double LO LVL):
A/THR......................................................................... OFF
Select the target speed on the FCU . Due to the loss of
slats and some flight control surfaces, the A/THR may
not satisfactorily maintain speed.
FOR LDG......................................................USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3.................................................... ON
WHEN SPD 200 KT (displayed when slats are
retracted):
L/G....................................................... GRVTY EXTN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←Q→
Continued on the following page
PRO-ABN-HYD P 39/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G+B SYS LO PR (Cont'd)
Refer to PRO-ABN-LG [QRH] L/G GRAVITY
EXTENSION
Extend the landing gear at 200 kt to revert sooner in
direct law. This provides, below 200 kt , a better pitch
control than in alternate law with one elevator lost
and all slats lost.
APPR SPD........................................................ VREF +25 KT
Approach speed must be increased, due to the loss of
ailerons and slats.
LDG DIST PROC......................................................... APPLY
ALTN LAW: PROT LOST
WHEN L/G DN: DIRECT LAW
(1)
See
FUEL CONSUMPT INCRSD
(2)
See
FMS PRED UNRELIABLE
(3)
See
FLAPS SLOW
(1)
(2)
(3)
At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW).
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←Q
PRO-ABN-HYD P 40/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G+Y SYS LO PR
Applicable to: ALL
Ident.: PRO-ABN-HYD-K-00018921.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the green and yellow systems pressure ≤1 450 PSI (the alert resets if
pressure ≥1 750 PSI).
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
R→
PRO-ABN-HYD P 41/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G+Y SYS LO PR (Cont'd)
Ident.: PRO-ABN-HYD-K-00018352.0003001 / 22 MAR 17
LAND ASAP
PTU................................................................................................................................................OFF
AFFECTED PUMPS......................................................................................................................OFF
If yellow sys lost by ENG 2 PUMP LO PR:
YELLOW ELEC PUMP.............................................................................................................ON
MANEUVER WITH CARE
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
ASSOCIATED PROCEDURES
L2
F/CTL ALTN LAW
(PROT LOST)
Flight control normal laws and associated protections are lost. Only load factor limitation, high and
low speed stability are provided (alternate law with reduced protection).
L1 MAX SPEED...........................................................................................................................320/0.77
L2 Speed is limited due to loss of high speed protection.
L1
If yellow sys recovered:
See procedure for single failure.
If yellow sys not recovered:
Refer to PRO-ABN-F_CTL [QRH] Landing with Slats or Flaps Jammed.
SECONDARY FAILURES
*F/CTL
*WHEEL
Continued on the following page
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PRO-ABN-HYD P 42/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G+Y SYS LO PR (Cont'd)
Ident.: PRO-ABN-HYD-K-00018353.0014001 / 22 MAR 17
L12
STATUS
MAX SPEED.............................................................. 320/0.77
MAX BRK PR.......................................................... 1 000 PSI
MANEUVER WITH CARE
APPR PROC
DUAL HYD LO PR
(Line not displayed for a double LO LVL)
If sys lost by RSVR LO AIR PR:
RELATED PUMP......................................................... ON
If sys lost by RSVR OVHT:
IF GREEN OVHT OUT:
GREEN ENG 1 PUMP.......................................... ON
IF YELLOW OVHT OUT:
YELLOW ENG 2 PUMP........................................ ON
IF HYD NOT RECOVERED (line not displayed for a
double LO LVL):
FOR LDG......................................................USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder.
GPWS FLAP MODE...................................................OFF
WHEN CONF 3 AND VAPP:
L/G....................................................... GRVTY EXTN
Refer to PRO-ABN-LG [QRH] L/G GRAVITY
EXTENSION. Being stabilized at VAPP, before
selecting the gear down, enables the aircraft to be
trimmed for approach.
APPR SPD........................................................ VREF +25 KT
Approach speed must be increased, due to the loss of flaps.
LDG DIST PROC......................................................... APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←R→
INOP SYS
G+Y HYD
F/CTL PROT
STABILIZER
REVERSER 1+2
SPLR 1+2+ 4+5
FLAPS
LAF
YAW DAMPER
AP 1+2
ANTI SKID
N/W STRG
NORM BRK
AUTO BRK
L/G RETRACT
CARGO DOOR (If Y RSVR LO
LVL)
CAT 2
GLS AUTOLAND
STEEP APPR
Continued on the following page
PRO-ABN-HYD P 43/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD G+Y SYS LO PR (Cont'd)
ALTN LAW: PROT LOST
WHEN L/G DN: DIRECT LAW
(1)
See
BRK Y ACCU PR ONLY
(2)
See
FUEL CONSUMPT INCRSD
(3)
See
FMS PRED UNRELIABLE
(4)
See
SLATS SLOW
(5)
See
(1)
(2)
(3)
(4)
(5)
At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW).
7 full brake applications are available.
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and refer to QRH/OPS Operational Data - Fuel Penalty Factors
Tables in order to find the applicable Fuel Penalty Factor.
Note:
Following a yellow hydraulic system failure, the parking brake may be inoperative due to
yellow accumulator low pressure.
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05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD PTU FAULT
Applicable to: ALL
Ident.: PRO-ABN-HYD-R-00017140.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ On ground, PTU does not run if the differential pressure is higher than 650 PSI between G
and Y system, or
‐ In flight, PTU at AUTO position does not run when G or Y reservoir level is low, and G or Y
system pressure is low.
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-R-00011657.0001001 / 31 AUG 17
L2
Note:
This warning is triggered, if the last engine is started within 40 s following the end of the
cargo doors operation. In this case, reset the warning by switching the yellow ELEC pump
ON, then OFF.
L1
If green or yellow reservoir low level and system low press:
PTU......................................................................................................................................... OFF
Continued on the following page
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05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD PTU FAULT (Cont'd)
Ident.: PRO-ABN-HYD-R-00011658.0001001 / 18 AUG 10
STATUS
INOP SYS
PTU
HYD RAT FAULT
Applicable to: ALL
Ident.: PRO-ABN-HYD-S-00017141.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The RAT is not fully stowed, or
‐ Pressure is present in the RAT stowing actuator, or
‐ The RAT pump is not available.
Flight Phase Inhibition:
Ident.: PRO-ABN-HYD-S-00011659.0001001 / 16 NOV 11
Crew awareness.
Continued on the following page
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PRO-ABN-HYD P 46/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
HYD RAT FAULT (Cont'd)
Ident.: PRO-ABN-HYD-S-00011660.0001001 / 18 AUG 10
STATUS
INOP SYS
RAT
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05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
HYD
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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PRO-ABN-HYD P 48/48
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
[QRH] LANDING WITH ABNORMAL L/G
Applicable to: ALL
Ident.: PRO-ABN-LG-AD-00018650.0002001 / 17 MAR 17
The procedure is intended for use when the nose or main landing gear fail to extend and/or lock
down following the application of the L/G GRVTY EXTN procedure.
It is preferable to use any available landing gear, rather than carry out a belly landing.
Under these circumstances, a hard surface runway landing is recommended.
Full advantage should be taken of any foam, spread on the runway.
CAUTION
Do not apply this procedure if at least one green triangle is displayed on each
landing gear on the WHEEL SD page. This is sufficient to confirm that the landing
gear is downlocked. Disregard any possible GPWS "TOO LOW GEAR" aural alert.
Ident.: PRO-ABN-LG-AD-00018651.0002001 / 17 MAR 17
CABIN CREW..........................................................................................................................NOTIFY
Notify the cabin crew of the nature of the emergency encountered and state intentions. Specify the
amount of available preparation time.
ATC..........................................................................................................................................NOTIFY
Notify ATC of the nature of the emergency and state intentions.
GALY & CAB.................................................................................................................................OFF
CONSIDER FUEL REDUCTION. This reduces VREF and, consequently, the load factor at impact
and the energy to be dissipated.
If NOSE L/G abnormal:
SHIFT CG AFT IF POSSIBLE
‐ 10 pax from front to rear moves the CG roughly 4 % aft
‐ 10 pax from mid to rear moves the CG roughly 2.5 aft.
If one MAIN L/G abnormal:
FUEL DISTRIBUTION.................................................................................................CONSIDER
Open the fuel X-FEED valve and switch off the pumps on the side with landing gear normally
extended.
OXYGEN CREW SUPPLY............................................................................................................OFF
SIGNS..............................................................................................................................................ON
CABIN and COCKPIT (LOOSE EQPT).................................................................................SECURE
Continued on the following page
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PRO-ABN-LG P 1/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
[QRH] LANDING WITH ABNORMAL L/G (Cont'd)
Ident.: PRO-ABN-LG-AD-00018652.0001001 / 17 MAR 17
For approach:
GPWS SYS.............................................................................................................................OFF
L/G lever............................................................................................................... CHECK DOWN
GRVTY GEAR EXTN handcrank....................................................... TURN BACK TO NORMAL
Rotating three turns back to normal may, in certain cases, pressurize the landing gear down
actuators, thereby reducing the probability of gear collapse after touchdown.
DO NOT ARM AUTOBRAKE
Manual braking will enable better pitch and roll control. Moreover, with at least one main
landing gear in the abnormal position the autobrake cannot be activated (ground spoilers not
armed).
EMER EXIT LT.........................................................................................................................ON
CABIN REPORT...............................................................................................................OBTAIN
A/SKID & N/W STRG............................................................................................................. OFF
With one main landing gear not extended, the reference speed used by the anti-skid to detect
a wheel blockage is not correctly initialized. As a result, the anti-skid must be switched off to
prevent permanent brake release.
MAX BRAKE PR : 1 000 PSI
Modulate the brake pressure to 1 000 PSI because the anti-skid is off.
If one or both MAIN L/G abnormal: DO NOT ARM GROUND SPOILERS
To keep as much roll authority as possible for maintaining the wings level.
Ground spoiler extension would prevent spoilers from acting as roll surfaces.
RAM AIR...................................................................................................................................ON
To ensure full depressurization of the aircraft before impact.
DOME LT.................................................................................................................................DIM
Set the dome light to DIM to ensure that there is a light source after both engines are shut
down after landing, in order to see and read the BRAKE PRESS indicator.
At 500 ft AGL:
BRACE FOR IMPACT...................................................................................................... ORDER
Continued on the following page
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PRO-ABN-LG P 2/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
[QRH] LANDING WITH ABNORMAL L/G (Cont'd)
Ident.: PRO-ABN-LG-AD-00018654.0001001 / 17 MAR 17
At flare, touchdown and rollout:
Engines should be shut down sufficiently early to ensure fuel is shut off before the nacelles
impact, but sufficiently late to ensure adequate hydraulic supplies for the flight controls.
Engine pumps continue to supply adequate hydraulic pressure for 30 s after engine shutdown.
DO NOT USE REVERSE
If NOSE L/G abnormal:
KEEP NOSE UP
After touchdown, keep the nose off the runway by the use of the elevator. Then, lower the
nose on to the runway before elevator control is lost.
BRAKES................................................................................................. SMOOTHLY APPLY
Adapt braking to the efficiency of the elevator.
BEFORE NOSE IMPACT : ALL ENG MASTERS OFF
If one MAIN L/G abnormal:
AT TOUCHDOWN : ALL ENG MASTERS OFF
KEEP AFFECTED SIDE WING UP
Use roll control, as necessary, to maintain the unsupported wing up as long as possible.
If both MAIN L/G abnormal:
DURING FLARE : ALL ENG MASTERS OFF
MIN PITCH ATT : 6 °
Continued on the following page
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PRO-ABN-LG P 3/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
[QRH] LANDING WITH ABNORMAL L/G (Cont'd)
Ident.: PRO-ABN-LG-AD-00018655.0001001 / 09 MAY 17
When aircraft stopped:
PARK BRK................................................................................................................................ON
ALL FIRE pb (ENG s & APU)............................................................................................. PUSH
ALL AGENT (ENG s & APU)............................................................................................. DISCH
If evacuation required:
EVACUATION...........................................................................................................INITIATE
Make a short and precise announcement to order the emergency evacuation.
Press the EVAC COMMAND pb .
If evacuation not required:
CABIN CREW and PASSENGERS (PA)................................................................... NOTIFY
Ensure that all the landing gears are secured before initiating the disembarkation (before
switching OFF the seat belts signs).
Continued on the following page
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PRO-ABN-LG P 4/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
[QRH] LANDING WITH ABNORMAL L/G (Cont'd)
Ident.: PRO-ABN-LG-AD-00018711.0001001 / 17 MAR 17
REFERENCE AIRCRAFT ATTITUDE AFTER IMPACT
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PRO-ABN-LG P 5/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
[QRH] L/G GRAVITY EXTENSION
Ident.: PRO-ABN-LG-00011286.0011001 / 17 MAR 17
Applicable to: ALL
CAUTION
Do not apply this procedure if at least one green triangle is displayed on each
landing gear on the WHEEL SD page. This is sufficient to confirm that the landing
gear is downlocked. Disregard any possible GPWS "TOO LOW GEAR" aural alert.
GRAVITY GEAR EXTN handcrank......................................................................... PULL AND TURN
Rotate the handle clockwise 3 turns until reaching the mechanical stop, even if resistance is felt.
L/G lever .................................................................................................................................. DOWN
The landing gear lever should be confirmed in the DOWN position for the following reasons:
‐ To extinguish the UNLK lights on the landing gear indication panel
‐ To prevent the L/G CTL message from appearing on the WHEEL SD page
‐ To minimize the risk of landing gear retraction on the ground, due to an unknown system fault,
when the free-fall system is reset.
GEAR DOWN indications (if available)....................................................................................CHECK
The L/G LGCIU 2 FAULT or BRAKES SYS 1(2) FAULT alert may be spuriously triggered after a
gravity extension.
Note:
1. Depending on aircraft speed, the display may show the landing gear doors in the amber
transit position.
2. In the event of gravity extension, caused by the failure of both LGCIU s, landing gear
position indication on ECAM are lost. LDG GEAR lights on LDG GEAR control panel
remain available, if LGCIU 1 is electrically supplied.
3. If the three green downlock arrows are not on, it is possible that the handcrank is not at
the mechanical stop. Check that the handcrank is firmly against the mechanical stop.
If successful:
DO NOT RESET LDG GEAR GRVTY EXTN
Do not reset the free-fall system. This will avoid such undesirable effects as further loss of fluid,
in the event of a leak, or possible landing gear unlocking, in the event of a gear selector valve
jamming in the UP position.
Note:
The free-fall system may be reset in flights used for training. If the green hydraulic
system is available, resetting the free-fall system allows the landing gear doors to be
closed and the nosewheel steering to operate.
The flight crew should not reset the free-fall system on the ground after flight.
Continued on the following page
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PRO-ABN-LG P 6/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
[QRH] L/G GRAVITY EXTENSION (Cont'd)
If unsuccessful:
LDG WITH ABNORMAL L/G PROC.................................................................................. APPLY
Refer to PRO-ABN-LG [QRH] Landing with Abnormal L/G.
L/G DOORS NOT CLOSED
Applicable to: ALL
Ident.: PRO-ABN-LG-D-00017734.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one gear door is not uplocked.
Flight Phase Inhibition:
Continued on the following page
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PRO-ABN-LG P 7/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G DOORS NOT CLOSED (Cont'd)
Ident.: PRO-ABN-LG-D-00011287.0003001 / 01 DEC 14
If the L/G lever is UP:
WHEN SPD < 220/0.54:
L/G LEVER............................................................................................................. RECYCLE
Note:
L2
L1
To recycle the landing gear, the flight crew must perform the following actions:
‐ Move the landing gear lever down
‐ Wait for the landing gear to downlock and for the landing gear doors to close.
Simultaneously monitor the WHEEL page on the System Display (SD)
‐ Move the landing gear lever up.
The active LGCIU changes when the landing gear is recycled.
IF UNSUCCESSFUL:
MAX SPEED.................................................................................................................... 250/0.60
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
Ident.: PRO-ABN-LG-D-00011288.0002001 / 17 MAR 17
L12
STATUS
MAX SPEED................................................................ 250/.60
L/G DOOR
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
(1)
(2)
INOP SYS
This message is triggered when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
Disregard FMS fuel predictions and Refer to QRH/OPS Fuel Penalty Factors/ECAM Alert Table in
order to find the applicable Fuel Penalty Factor.
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05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G GEAR NOT DOWN
Applicable to: ALL
Ident.: PRO-ABN-LG-AA-00017859.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
1. L/G is not downlocked and radio height is lower than 750 ft and both engines N1 lower than
75% (or if engine shutdown N1 of remaining engine lower than 97%) or
2. L/G is not downlocked and radio height is lower than 750 ft and both engines are not at T.O
power and flaps at 1, 2, 3 or FULL or
3. L/G is not downlocked and flaps at 3 or FULL and both radio altimeters are failed.
Note:
In the cases 2 and 3 above, the aural warning can only be cancelled by the
emergency cancel pushbutton.
Flight Phase Inhibition:
Ident.: PRO-ABN-LG-AA-00018573.0002001 / 21 MAR 16
L2
When this warning appears, the red arrow on the instrument panel comes on.
L1
Crew awareness.
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PRO-ABN-LG P 9/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G GEAR NOT DOWNLOCKED
Applicable to: ALL
Ident.: PRO-ABN-LG-C-00017860.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one gear is not downlocked and L/G is selected down.
Flight Phase Inhibition:
Ident.: PRO-ABN-LG-C-00011284.0002001 / 01 DEC 14
L2
This warning appears, if the landing gear sequence is not completed after 30 s.
L1
L/G LEVER.......................................................................................................................... RECYCLE
L2
Note:
To recycle the landing gear, the flight crew must perform the following actions:
‐ Move the landing gear lever up
‐ Wait for the landing gear to uplock and for the landing gear doors to close.
Simultaneously monitor the WHEEL page on the System Display (SD)
‐ Move the landing gear lever down.
The active LGCIU changes when the landing gear is recycled.
L1
IF UNSUCCESSFUL AFTER 120 s:
L/G.......................................................................................................................... GRVTY EXTN
L2
Rotate the handle clockwise about 3 turns until reaching the mechanical stop. Refer to
PRO-ABN-LG [QRH] L/G GRAVITY EXTENSION.
Continued on the following page
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PRO-ABN-LG P 10/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G GEAR NOT DOWNLOCKED (Cont'd)
Ident.: PRO-ABN-LG-C-00011285.0003001 / 21 MAR 16
L12
STATUS
L/G.................................................................... GRVTY EXTN
CAT 3 SINGLE ONLY
(1)
See
(1)
INOP SYS
CAT 3 DUAL
If gravity extension is unsuccessful, Refer to PRO-ABN-LG [QRH] Landing with Abnormal L/G.
L/G GEAR NOT UPLOCKED
Applicable to: ALL
Ident.: PRO-ABN-LG-B-00017736.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one gear is not uplocked and L/G is not selected down.
Flight Phase Inhibition:
Continued on the following page
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PRO-ABN-LG P 11/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G GEAR NOT UPLOCKED (Cont'd)
Ident.: PRO-ABN-LG-B-00011061.0003001 / 01 DEC 14
L2
This warning appears if the landing gear sequence is not completed after 30 s.
L1
L/G doors closed:
AVOID EXCESS G FACTOR
L2
Because the gear rests on the doors, avoid excessive load factors in order not to damage door
structure.
L1
L/G doors not closed and shock absorber fault:
MAX SPEED.................................................................................................................... 220/0.54
L/G...................................................................................................................................... DOWN
MAX SPEED.................................................................................................................... 280/0.67
L/G doors not closed and no shock absorber fault:
MAX SPEED.................................................................................................................... 220/0.54
L/G LEVER....................................................................................................................RECYCLE
L2
Note:
L1
IF UNSUCCESSFUL:
L/G................................................................................................................................DOWN
MAX SPEED..............................................................................................................280/0.67
To recycle the landing gear, the flight crew must perform the following actions:
‐ Move the landing gear lever down
‐ Wait for the landing gear to downlock and for the landing gear doors to close.
Simultaneously monitor the WHEEL page on the System Display (SD)
‐ Move the landing gear lever up.
The active LGCIU changes when the landing gear is recycled.
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
Continued on the following page
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PRO-ABN-LG P 12/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G GEAR NOT UPLOCKED (Cont'd)
Ident.: PRO-ABN-LG-B-00018687.0002001 / 25 JUL 17
L12
STATUS
MAX SPEED................................................................ 280/.67
L/G RETRACT
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
(1)
See
(1)
INOP SYS
If the flight is continued (to destination or to alternate) with landing gear extended:
‐ Disregard FMS fuel predictions. Refer to QRH/OPS Fuel Penalty Factors/ECAM Alert Table in
order to find the applicable Fuel Penalty Factor
‐ Disregard FMS altitude and speed predictions. Time predictions are only valid in cruise
‐ Do not use the managed speed mode (except in approach)
‐ Do not use the CLB and the DES autopilot modes.
Also Refer to PRO-NOR-SUP-L/G- Flight with Gear Down.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-ABN-LG P 13/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G GEAR UPLOCK FAULT
Applicable to: ALL
Ident.: PRO-ABN-LG-E-00017737.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one gear uplock is engaged with corresponding gear downlocked.
Flight Phase Inhibition:
Ident.: PRO-ABN-LG-E-00011289.0002001 / 27 NOV 12
L/G.................................................................................................................................. KEEP DOWN
The landing gear must be left down to avoid structural damage, because the uplock device will stay
in the locked position.
L1 MAX SPEED.............................................................................................................................280/.67
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
L2
Continued on the following page
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PRO-ABN-LG P 14/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G GEAR UPLOCK FAULT (Cont'd)
Ident.: PRO-ABN-LG-E-00018719.0002001 / 25 JUL 17
L12
STATUS
MAX SPEED................................................................ 280/.67
L/G..................................................................... KEEP DOWN
INOP SYS
L/G RETRACT
FUEL CONSUMPT INCRSD
(1)
See
FMS PRED UNRELIABLE
(2)
See
(1)
(2)
This message triggers when the failure (or combination of failures) affects the nominal
aerodynamic characteristics of the aircraft.
If the flight is continued (to destination or to alternate) with landing gear extended:
‐ Disregard FMS fuel predictions. Refer to QRH/OPS Fuel Penalty Factors/ECAM Alert Table in
order to find the applicable Fuel Penalty Factor
‐ Disregard FMS altitude and speed predictions. Time predictions are only valid in cruise
‐ Do not use the managed speed mode (except in approach)
‐ Do not use the CLB and the DES autopilot modes.
Also Refer to PRO-NOR-SUP-L/G- Flight with Gear Down.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-ABN-LG P 15/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G LGCIU 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-LG-G-00018059.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when LGCIU 1(2) is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-LG-G-00018681.0002001 / 21 MAR 16
If LGCIU 1 is failed:
GPWS SYS.............................................................................................................................OFF
L2
GPWS receives “L/G in up position” information even if the landing gear is down.
Set the GPWS SYS pb-sw to OFF in order to prevent untimely warnings during the approach.
Continued on the following page
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PRO-ABN-LG P 16/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G LGCIU 1(2) FAULT (Cont'd)
Ident.: PRO-ABN-LG-G-00018682.0001001 / 21 MAR 16
L12
STATUS
INOP SYS
ENG 1(2) APPR IDLE ONLY
(2)
See
Note:
(1)
(2)
LGCIU 1(2)
REVERSER 1(2)
GPWS
(1)
1. The partial spoiler extension at landing when only one main landing gear is
compressed is not available. The spoilers extend normally on ground when wheel
speed greater than 72 kt.
2. Depending on the LGCIU failure, only a part of the above systems may be lost.
(If LGCIU 1 is failed)
When idle is selected on ground with slats extended, only approach idle is available.
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PRO-ABN-LG P 17/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G LGCIU 1+2 FAULT
Applicable to: ALL
Ident.: PRO-ABN-LG-V-00017739.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both LGCIUs are failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-LG-V-00018683.0002001 / 21 MAR 16
L2
Normal landing gear control and position indications are lost. LDG GEAR lights on LDG GEAR
control panel remain available if LGCIU 1 is electrically supplied.
L/G................................................................................................................................. GRVTY EXTN
Refer to PRO-ABN-LG [QRH] L/G GRAVITY EXTENSION.
L1 GPWS SYS................................................................................................................................... OFF
L2 As LGCIU 1 is lost, GPWS receives “L/G in up position” information even if the landing gear is
down.
Set the GPWS SYS pb-sw to OFF in order to prevent untimely warnings during approach.
L1
L2
Continued on the following page
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PRO-ABN-LG P 18/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G LGCIU 1+2 FAULT (Cont'd)
Ident.: PRO-ABN-LG-V-00018684.0006001 / 05 OCT 16
L12
STATUS
If the selected configuration is not FLAP 3:
FOR LDG......................................................USE FLAP 3
If the selected configuration is FLAP 3:
FOR LDG: USE FLAP 3
L/G.................................................................... GRVTY EXTN
L/G CONTROL NOT AVAIL
ENG 1 APPR IDLE ONLY
ENG 2 APPR IDLE ONLY
Note:
(1)
INOP SYS
REVERSER 1+2
AP 1+2
(1)
(1)
CAT 2
A/THR
GLS AUTOLAND
LGCIU 1
LGCIU 2
GPWS
ROW/ROP
1. The partial spoiler extension at landing when only one main landing gear is
compressed is not available. The spoilers extend normally on ground when wheel
speed greater than 72 kt.
2. In flight with both LGCIU s "faulty", whatever the landing gear configuration, when
the flight crew switches ON Wing Anti-Ice pb, the Wing Anti-Ice pb will illuminate
"on" and there will be only 30 s of heating. This loss of Wing Anti-ice will not have an
ECAM/Aural warning, although BLEED SD page shows a "no-Anti-ice" legend.
(Except in LAND mode)
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PRO-ABN-LG P 19/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G SHOCK ABSORBER FAULT
(SHOCK ABSORBER EXTENDED ON GROUND)
Applicable to: ALL
Ident.: PRO-ABN-LG-AB-00017733.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one shock absorber is not compressed after landing.
Flight Phase Inhibition:
Ident.: PRO-ABN-LG-AB-00011056.0001001 / 25 FEB 14
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J
PRO-ABN-LG P 20/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G SHOCK ABSORBER FAULT
(SHOCK ABSORBER NOT EXTENDED AFTER LIFTOFF)
Applicable to: ALL
Ident.: PRO-ABN-LG-A-00018062.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one shock absorber is not extended when airborne.
Flight Phase Inhibition:
Ident.: PRO-ABN-LG-A-00011058.0003001 / 25 FEB 14
Shock absorber not extended after liftoff and L/G uplocked :
Crew awareness.
Shock absorber not extended after liftoff and L/G not uplocked :
MAX SPEED...................................................................................................................... 280/.67
If L/G lever still down :
L/G.....................................................................................................................KEEP DOWN
If L/G lever selected up :
L/G................................................................................................................................DOWN
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
Continued on the following page
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PRO-ABN-LG P 21/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G SHOCK ABSORBER FAULT (Cont'd)
(SHOCK ABSORBER NOT EXTENDED AFTER LIFTOFF)
Ident.: PRO-ABN-LG-A-00011059.0003001 / 25 JUL 17
L12
STATUS
If L/G not uplocked:
MAX SPEED..........................................................280/.67
L/G...............................................................KEEP DOWN
INOP SYS
L/G RETRACT
FUEL CONSUMPT INCRSD
FMS PRED UNRELIABLE
(1)
See
(1)
If the flight is continued (to destination or to alternate) with landing gear extended:
‐ Disregard FMS fuel predictions. Refer to QRH/OPS Fuel Penalty Factors/ECAM Alert Table in
order to find the applicable Fuel Penalty Factor
‐ Disregard FMS altitude and speed predictions. Time predictions are only valid in cruise
‐ Do not use the managed speed mode (except in approach)
‐ Do not use the CLB and the DES autopilot modes.
Also Refer to PRO-NOR-SUP-L/G- Flight with Gear Down.
Note:
In few cases, autothrust and autopilot may also be lost.
If WHEEL N.W. STEER FAULT is also displayed, then the nose wheels may be at
maximum deflection. (Turned 90 ° from center.) During landing, delay nose wheel
touchdown for as long as possible.
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PRO-ABN-LG P 22/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
L/G SYS DISAGREE
Applicable to: ALL
Ident.: PRO-ABN-LG-AC-00017861.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when LGCIU 1 and LGCIU 2 detect a discrepancy between the landing gear
positions.
Flight Phase Inhibition:
Ident.: PRO-ABN-LG-AC-00018664.0002001 / 21 MAR 16
Crew awareness.
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FCOM
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PRO-ABN-LG P 23/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
L/G
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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PRO-ABN-LG P 24/24
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[MEM] EMER DESCENT
Ident.: PRO-ABN-MISC-00012092.0001001 / 17 MAR 17
Applicable to: ALL
CREW OXY MASKS................................................................................................................... USE
SIGNS............................................................................................................................................ ON
EMER DESCENT................................................................................................................. INITIATE
If A/THR not active:
THR LEVERS....................................................................................................................... IDLE
SPD BRK....................................................................................................................................FULL
When descent established:
SPEED......................................................................................................... MAX/APPROPRIATE
If structural damage suspected: MANEUVER WITH CARE
CONSIDER L/G EXTENSION
ENG MODE SEL..................................................................................................................... IGN
ATC................................................................................................................................... NOTIFY
Notify ATC of the nature of the emergency, and state intention. The flight crew can
communicate with the ATC using voice, or CPDLC when the voice contact cannot be
established or has poor quality.
EMER DESCENT (PA)..............................................................................................ANNOUNCE
The flight crew must inform the cabin of emergency descent on the PA system.
ATC XPDR 7700.........................................................................................................CONSIDER
Squawk 7700 unless otherwise specified by ATC.
CREW OXY MASKS DILUTION.........................................................................................NORM
‐ To save oxygen, set the oxygen diluter selector to the N position
‐ If the oxygen diluter selector remains set to 100 %, oxygen quantity may be insufficient to
cover the entire emergency descent profile
‐ Ensure that crew communication is established with oxygen masks. Avoid the continuous
use of the interphone to minimize interference with the breathing noise in the oxygen mask.
MAX FL: 100/MEA-MORA
If CAB ALT above 14 000 ft:
OXYGEN PAX MASK MAN ON..................................................................................PRESS
This action confirms that the passenger oxygen masks are released.
Continued on the following page
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PRO-ABN-MISC P 1/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[MEM] EMER DESCENT (Cont'd)
Note:
Notify the cabin crew, when the aircraft reaches a safe flight level, and when
cabin oxygen is no more necessary.
[MEM] STALL RECOVERY
Ident.: PRO-ABN-MISC-00013768.0001001 / 17 MAR 17
Applicable to: ALL
As soon as any stall indication (could be aural warning, buffet...) is recognized, apply the immediate
actions:
NOSE DOWN PITCH CONTROL.............................................................................................APPLY
This will reduce angle of attack
Note:
In case of lack of pitch down authority, reducing thrust may be necessary.
BANK............................................................................................................................WINGS LEVEL
When out of stall (no longer stall indications) :
THRUST........................................................................... INCREASE SMOOTHLY AS NEEDED
Note:
In case of one engine inoperative, progressively compensate the thrust asymmetry
with rudder.
SPEEDBRAKES......................................................................................... CHECK RETRACTED
FLIGHT PATH.........................................................................................RECOVER SMOOTHLY
If in clean configuration and below 20 000 ft :
FLAP1........................................................................................................................ SELECT
Note:
If a risk of ground contact exists, once clearly out of stall (no longer stall
indications), establish smoothly a positive climb gradient.
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PRO-ABN-MISC P 2/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[MEM] STALL WARNING AT LIFT-OFF
Ident.: PRO-ABN-MISC-00013769.0001001 / 17 MAR 17
Applicable to: ALL
Spurious stall warning may sound in NORMAL law, if an angle of attack probe is damaged. In this
case, apply immediately the following actions:
THRUST..................................................................................................................................... TOGA
At the same time:
PITCH ATTITUDE..........................................................................................................................15 °
BANK............................................................................................................................WINGS LEVEL
Note:
When a safe flight path and speed are achieved and maintained, if stall warning
continues, consider it as spurious.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-MISC P 3/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] BOMB ON BOARD
Ident.: PRO-ABN-MISC-00012095.0002001 / 17 MAR 17
Applicable to: ALL
COCKPIT PROCEDURES
BACKGROUND
To avoid the activation of an altitude-sensitive bomb, the cabin altitude should not exceed the
value at which the bomb has been discovered.
To reduce the effects of the explosion, the aircraft should fly as long as possible with
approximately 1 PSI differential pressure, to help the blast go outwards. 1 PSI differential
pressure corresponds to a 2 500 ft difference between the aircraft and the cabin altitude.
These conditions are achieved by using the manual pressure control.
PROCEDURE
The following procedure assumes that it is initiated during climb or cruise:
First, maintain the cabin altitude using manual pressure mode.
While maintaining the cabin altitude, descend the aircraft to the cabin altitude + 2 500 ft and
maintain delta P at 1 PSI.
During further steps of descent, maintain delta P at 1 PSI using the cabin V/S target selector.
During the approach, use automatic pressure mode in order to reduce the differential pressure
to zero at touchdown.
If flight conditions are different, the crew should adapt the procedure, bearing in mind the
above-mentioned principles (background paragraph).
CKPT / CAB COM.................................................................................................... ESTABLISH
Continued on the following page
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PRO-ABN-MISC P 4/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] BOMB ON BOARD (Cont'd)
If landing and evacuation possible within 30 min:
ATC / COMPANY..................................................................................................... NOTIFY
EVAC.....................................................................................................................PREPARE
If landing and evacuation NOT possible within 30 min:
AIRCRAFT (IF CLIMBING).................................................................................LEVEL OFF
CABIN PRESS MODE SEL........................................................................................... MAN
The purpose is to immediately prevent the cabin altitude from increasing, in order to avoid
the activation of an altitude-sensitive bomb.
MAINTAIN CAB ALT
Use MAN V/S CTL selector to maintain the cabin altitude at the value it had when the
bomb was discovered.
ATC / COMPANY..................................................................................................... NOTIFY
To obtain expert advice from explosive specialists.
TRGT SPEED: PREFER LO IAS
Low speed could reduce the consequences of possible structural damage, if the bomb
explodes.
DESCENT TO CAB ALT + 2 500 ft or MEA - MORA............................................. INITIATE
Descending to 2 500 ft above the cabin altitude gives a cabin differential pressure of
approximately 1 PSI, which helps to ensure that the blast goes outwards, if the bomb
explodes.
AVOID SHARP MANEUVERS
Which might result in the bomb moving.
MAINTAIN CAB ALT
Use MAN V/S CTL selector to maintain the cabin altitude. Initially brief UP input should be
required; but, be careful not to increase the cabin altitude.
When at CAB ALT + 2 500 ft:
MAINTAIN 1 PSI ΔP
Use MAN V/S CTL selector to adjust delta P to 1 PSI. Brief DN input should be initially
required to set 0 ft/min cabin vertical speed.
GALLEY.................................................................................................................... OFF
FUEL RESERVES...................................................................................... DETERMINE
When flying at cabin altitude + 2 500 ft, fuel consumption in CONF 1, with landing gear
down, will be about 2.1 times that consumed in clean configuration.
Continued on the following page
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PRO-ABN-MISC P 5/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] BOMB ON BOARD (Cont'd)
When bomb secured at the LRBL or cannot be moved:
Least Risk Bomb Location (LRBL) is the center of the RH aft cabin door
EMER EXIT LT....................................................................................................ON
To recover minimum cabin lighting when the COMMERCIAL pb-sw will be
switched OFF
COMMERCIAL................................................................................................... OFF
If fuel permits:
FLAPS....................................................................................... AT LEAST CONF 1
L/G lever (except for flight over water)..........................................................DOWN
The detonation could damage the landing systems. Therefore, if fuel permits,
configure the aircraft for landing as soon as possible. Reducing the speed will
minimize stress on the aircraft structure.
USE NORMAL CONF FOR LANDING
DURING FURTHER DESCENT: MAINTAIN MAX 1 PSI ΔP
Use MAN V/S CTL selector to DN to adjust delta P to 1 PSI.
During approach:
CABIN PRESS MODE SEL...................................................................................AUTO
This allows CPC to automatically control the cabin altitude to 0 during final approach.
When aircraft on ground and stopped in a remote area (if possible):
Refer to PRO-ABN-MISC [QRH] EMER EVAC
CABIN PROCEDURES
If a suspect device is found in the cabin:
WARNING
Do not cut or disconnect any wires and do not open or attempt to gain entry to
internal components of a closed or concealed suspect device. Any attempt may
result in an explosion. Booby-trapped closed devices have been used on aircraft
in the past.
WARNING
Alternate locations must not be used without consulting with an aviation
explosives security specialist. Never take a suspect device to the flight deck.
CAUTION
The least risk bomb location for the aircraft structure and systems is center of
the RH aft cabin door.
EOD PERSONNEL ON BOARD..........................................................................................CHECK
Continued on the following page
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PRO-ABN-MISC P 6/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] BOMB ON BOARD (Cont'd)
Announce “Is there any EOD personnel on board ?”. By using the initials, only persons familiar
with EOD (Explosive Ordnance Disposal) will be made aware of the problem.
DO NOT OPEN THE BOMB
DO NOT CUT BOMB’S WIRES
SECURE BOMB AGAINST SLIPPING
PROTECT BOMB AGAINST SHOCKS
Secure in the attitude found and do not lift before having checked for an anti-lift ignition device.
PASSENGERS.................................................................................... LEAD AWAY FROM BOMB
Move passengers at least 4 seat rows away from the bomb location. On full flights, it may be
necessary to double up passengers to achieve standoff from the suspect device.
Passengers near the bomb should protect their heads with pillows, blankets.
All passengers must remain seated with seatbelts on and, if possible, head below the top of the
head rest. Seat backs and tray tables should be in their full upright position.
Service items may need to be collected in order to secure tray tables.
PORTABLE ELECTRONIC DEVICES....................................................................... SWITCH OFF
The cabin crews must command passengers to switch off all portable electronic devices.
BOMB............................................................................................CHECK NO ANTI-LIFT DEVICE
To check for an anti-lift switch or lever, slide a string or stiff card, (such as the emergency
information card) under the bomb, without disturbing the bomb.
If the string or card cannot be slipped under the bomb, it may indicate that an anti-lift switch or
lever is present and that the bomb cannot be moved.
If a card is used and can be slid under the bomb, leave it under the bomb and move together
with the bomb.
If it is not possible to move the bomb, then it should be surrounded with a single thin sheet of
plastic (e. g. trash bag), then with wetted materials, and other blast attenuation materials such as
seat cushions and soft carry-on baggage. Move personnel as far away from the bomb location as
possible.
EMERGENCY EQUIPMENT........................................................................ REMOVE AND STOW
Emergency equipment (PBE, fire extinguisher, ...) located close to the LRBL must be removed
and stowed in alternate location.
GALLEY/IFE POWER................................................................................................................OFF
All galley and IFE equipment located close to the LRBL must be switched off.
If the bomb can be moved:
RH AFT CABIN DOOR SLIDE.................................................................................... DISARM
LEAST RISK BOMB LOCATION (LRBL)................................................................. PREPARE
Continued on the following page
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PRO-ABN-MISC P 7/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] BOMB ON BOARD (Cont'd)
Build up a platform of solid baggage against the door up to about 25 cm (10 in) below the
middle of the door.
On top of this, build up at least 25 cm (10 in) of wetted material such as blankets and pillows.
Place a single thin sheet of plastic (e. g. trash bag) on top of the wetted materials. This
prevents any possible short circuit.
CAUTION
DO NOT OMIT THE PLASTIC SHEETS, AS THE SUSPECT DEVICE
COULD GET WET AND POSSIBLY SHORT CIRCUIT ELECTRONIC
COMPONENTS CAUSING INADVERTENT DEVICE ACTIVATION.
BOMB INDICATION LINE.........................................................................................POSITION
Note:
A bomb location indicator line is a 6 to 8 ft (1.8 to 2.4 m) (e.g. neckties, headset
cord, or belts connected together) preferably of constrating color, that helps the
responding bomb squad find the precise location of the suspect device within the
LRBL stack once constructed.
Position the bomb indication line from the location on the platform where you will place the
suspect device, EXTENDING outward into the aisle.
BOMB..............................................................................................................MOVE TO LRBL
Carefully carry in the attitude found and place on top of the wetted materials in the same
attitude and as close to the door structure as possible.
CAUTION
Ensure that the suspect device, when placed on the stack against the door,
is above the slide pack but not against the door handle, and if possible,
avoid placement in the view port.
LEAST RISK BOMB LOCATION (LRBL)...............................................................COMPLETE
Place an additional single thin sheet of plastic over the bomb.
CAUTION
DO NOT OMIT THE PLASTIC SHEETS, AS THE SUSPECT DEVICE
COULD GET WET AND POSSIBLY SHORT CIRCUIT ELECTRONIC
COMPONENTS CAUSING INADVERTENT DEVICE ACTIVATION.
Build up at 25 cm (10 in) of wetted material around the sides and on top of the bomb.
DO NOT PLACE ANYTHING BETWEEN THE BOMB AND THE DOOR, AND MINIMIZE
AIRSPACE AROUND THE BOMB.
The idea is to build up a protective surrounding of the bomb so that the explosive force is
directed in the only unprotected area into the door structure.
Fill the area around the bomb with seat cushions and other soft materials such as hand
luggage (saturated with water or any other nonflammable liquid) up to the cabin ceiling,
Continued on the following page
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PRO-ABN-MISC P 8/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] BOMB ON BOARD (Cont'd)
compressing as much as possible. Secure the LRBL stack in place using belt, ties or other
appropriate materials. The more material stacked around the bomb, the less the damage will
be.
USE ONLY SOFT MATERIAL. AVOID USING MATERIALS CONTAINING ANY
INFLAMMABLE LIQUID AND ANY METAL OBJECTS WHICH COULD BECOME
DANGEROUS PROJECTILES.
LRBL STACK
PASSENGERS.................................................................................................. MOVE/ADVISE
Move passengers at least 4 seat rows away from the least risk bomb location (RH aft cabin
door). On full flights, it may be necessary to double up passengers to achieve standoff from
the suspect device.
Passengers near the bomb should protect their heads with pillows, blankets. All passengers
must remain seated with seatbelts on and, if possible, head below the top of the head rest.
Seat backs and tray tables must be in their full upright position.
CABIN CREW........................................................................................ NOTIFY COCKPIT CREW
Cabin crew notify the flight crew that the bomb is secured at the LRBL.
EVACUATION/DISEMBARKATION.................................................................................EXECUTE
Evacuate through normal and emergency exits on the opposite side of the “bomb” location. Do
not use the door just opposite the “bomb”.
Continued on the following page
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PRO-ABN-MISC P 9/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] BOMB ON BOARD (Cont'd)
Use all available airport facilities to disembark without delay.
[QRH] COCKPIT WINDSHIELD / WINDOW ARCING
Ident.: PRO-ABN-MISC-00012099.0001001 / 17 MAR 17
Applicable to: ALL
Affected WINDOW / WINDSHIELD ANTI-ICE C/B..................................................................... PULL
Pull the circuit breaker of the affected window/windshield heating system, in case of:
‐ Electrical arcing of the cockpit windshield/window, or
‐ Burning smell or smoke identified as coming from the bottom right corner of CAPT windshield or
bottom left corner of the F/O windshield.
On the rear C/B panel:
‐
‐
‐
‐
ANTI-ICE L WSHLD AF10 C/B [123VU],
ANTI-ICE R WSHLD AF03 C/B [123VU],
ANTI-ICE/WINDOWS L X14 C/B [122VU],
ANTI-ICE/WINDOWS R W14 C/B [122VU].
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FCOM
← D to E
PRO-ABN-MISC P 10/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] COCKPIT WINDSHIELD / WINDOW CRACKED
Ident.: PRO-ABN-MISC-00012097.0001001 / 17 MAR 17
Applicable to: ALL
TOUCH THE CRACK WITH A PEN (OR CAREFULLY WITH FINGERNAIL)
If no crack on cockpit side:
NO LIMITATION
The inner ply is not affected. Therefore, the window/windshield is still able to sustain the
differential pressure up to the maximum flight level.
If cracks on cockpit side:
MAX FL: 230 / MEA-MORA
The inner ply is affected. The flight crew is not able to easily determine if other plies are
affected. Descend to FL 230/MEA and reduce differential pressure to 5 PSI .
Note:
The maximum flight level is restricted to FL 230/MEA to obtain ΔP 5 PSI , without
resulting in an excessive cabin altitude and an EXCESS CAB ALT warning.
The following procedure enables maintaining ΔP 5 PSI in manual cabin pressure mode.
CAB PRESS MODE SEL...................................................................................................... MAN
DISREGARD THE CAB ALT TARGET TABLE DISPLAYED ON THE ECAM
MAN V/S CTL................................................................................................................AS RQRD
SET THE CABIN ALTITUDE ACCORDING TO THE TABLE BELOW TO MAINTAIN ΔP 5 PSI
FL
CABIN ALTITUDE
100
0
150
3 000
200
6 000
230
8 000
When starting the descent for approach:
CAB PRESS MODE SEL..............................................................................................AUTO
Note:
Due to the increased noise level, pay particular attention to visual warnings.
If visibility not sufficient for approach due to damage:
CONSIDER AUTOLAND
For approach, if AUTOLAND not available:
CAB PRESS MODE SEL................................................................................................MAN
MAN V/S CTL...........................................................................................................FULL UP
MAX SPEED: 200 kt
PF SLIDING WINDOW................................................................................................. OPEN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-ABN-MISC P 11/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] DITCHING
Ident.: PRO-ABN-MISC-00012087.0056001 / 17 MAR 17
Applicable to: ALL
This procedure applies when engines are running. If engines are not running, Refer to
QRH/ABN-19 ENG DUAL FAILURE - FUEL REMAINING - DITCHING or Refer to QRH/ABN-19
ENG DUAL FAILURE - NO FUEL REMAINING - DITCHING
ATC..........................................................................................................................................NOTIFY
ATC XPDR 7700............................................................................................................... CONSIDER
PREPARE CABIN AND COCKPIT
Notify the cabin crew of the nature of the emergency and state intentions.
Specify the available time:
‐ Loose equipment secured
‐ Survival equipment prepared
‐ Belts and shoulder harnesses locked
GPWS SYS................................................................................................................................... OFF
GPWS TERR.................................................................................................................................OFF
Pressing OFF the SYS pb and TERR pb avoids nuisance warnings.
SIGNS..............................................................................................................................................ON
EMER EXIT LT............................................................................................................................... ON
COMMERCIAL...............................................................................................................................OFF
LDG ELEV.........................................................................................................................SELECT 00
BARO............................................................................................................................................. SET
DISREGARD NORM C/Ls
ELT (when conditions permit)......................................................................................................... ON
For approach and ditching:
KEEP LANDING GEAR UP
SLATS / FLAPS..........................................................................................................MAX AVAIL
FOR FLARE: TARGET PITCH 11 ° & MIN V/S
Note:
Prefer ditching parallel to the swell. If that causes a strong crosswind, ditch into the
wind.
At 2 000 ft AGL:
CAB PRESS MODE SEL.................................................................................................... AUTO
The outflow valve would remain open, if the MODE SEL pb were not at AUTO.
ALL BLEEDS (ENGs & APU).................................................................................................OFF
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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PRO-ABN-MISC P 12/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] DITCHING (Cont'd)
CABIN CREW........................................................................................NOTIFY FOR DITCHING
DITCHING pb .......................................................................................................................... ON
The outflow valve, emergency ram air inlet, avionics ventilation inlet and extract valves, and
pack flow control valves, and the forward cargo outlet isolation valve, close.
At 500 ft AGL:
BRACE FOR IMPACT...................................................................................................... ORDER
At touchdown:
ALL ENG MASTERS.............................................................................................................. OFF
APU MASTER SW..................................................................................................................OFF
After ditching:
ATC (VHF 1).....................................................................................................................NOTIFY
With engine and APU shut down, only VHF 1 is supplied.
ALL FIRE pb (ENGs & APU)...............................................................................................PUSH
ALL AGENTS (ENGs and APU).........................................................................................DISCH
EVACUATION................................................................................................................. INITIATE
ELT..................................................................................................................CHECK EMITTING
If not, switch on the transmitter.
After impact the lowest point of the passenger exits (aft door) remains above the waterline for
more than 7 min.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-ABN-MISC P 13/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] EMER EVAC
Ident.: PRO-ABN-MISC-00012083.0001001 / 09 MAY 17
Applicable to: ALL
Apply this procedure when considering an emergency evacuation, or when required by the ECAM.
Carefully analyze the situation before deciding to evacuate passengers. However do not waste
valuable time.
AIRCRAFT / PARKING BRK.............................................................................................STOP / ON
ATC (VHF1).............................................................................................................................NOTIFY
Notify ATC of the nature of the emergency, and state intentions.
Only VHF 1 is available on batteries.
CABIN CREW (PA)...................................................................................................................ALERT
Make a short and precise announcement to warn that an emergency evacuation may be required.
ΔP (only if MAN CAB PR has been used)................................................................... CHECK ZERO
If ΔP is not at zero, MODE selector on MAN and V/S CTL FULL UP, to fully open the outflow valve.
If ΔP not at zero:
CAB PR MODE SEL..............................................................................................................MAN
V/S CTL.......................................................................................................................... FULL UP
ALL ENG MASTER....................................................................................................................... OFF
Associated LP and HP valves close.
ALL FIRE pb (ENGs & APU)..................................................................................................... PUSH
ALL AGENTS (ENGs & APU)............................................................................................. AS RQRD
Engine Agent 2 is not available.
The use of agents is required if the ENG FIRE or APU FIRE is displayed.
If evacuation required:
EVACUATION................................................................................................................. INITIATE
Make a short and precise announcement to order the emergency evacuation.
Press the EVAC COMMAND pb .
If evacuation not required:
CABIN CREW AND PASSENGERS (PA)........................................................................NOTIFY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
PRO-ABN-MISC P 14/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] EMER LANDING
ALL ENG FAILURE
Ident.: PRO-ABN-MISC-00015075.0009001 / 17 MAR 17
Applicable to: ALL
Apply the following if not able to maintain altitude after the loss of thrust near the ground.
If ditching anticipated:
APU.................................................................................................................................... START
L/G LEVER..................................................................................................................CHECK UP
FOR LANDING..........................................................................................................USE FLAP 2
L2
Only slats extend, and slowly.
L1
VAPP.........................................................................................................................DETERMINE
Weight
VAPP
L2
L1
40 t
/ 90 klb
150 kt
50 t
/ 110 klb
150 kt
60 t
/ 130 klb
163 kt
70 t
/ 155 klb
173 kt
80 t
/ 175 klb
183 kt
90 t
/ 200 klb
193 kt
95 t
/ 210 klb
198 kt
DITCHING pb .......................................................................................................................... ON
Ditch the aircraft parallel to the swell. If that causes a strong crosswind, ditch the aircraft into
the wind.
At 500 ft AGL or below:
BRACE FOR IMPACT................................................................................................ORDER
For flare:
TOUCH DOWN AT MIN V/S
TARGET PITCH ATT 11 °
L2
At touchdown:
ALL ENG MASTERS........................................................................................................OFF
APU MASTER SW........................................................................................................... OFF
EMER EVAC PROC.................................................................................................... APPLY
Refer to PRO-ABN-MISC [QRH] EMER EVAC
L1
If forced landing anticipated:
APU.................................................................................................................................... START
FOR LANDING..........................................................................................................USE FLAP 2
L2
Only slats extend, and slowly.
L1
VAPP.........................................................................................................................DETERMINE
Weight
40 t
50 t
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
60 t
70 t
I→
80 t
90 t
95 t
Continued on the following page
PRO-ABN-MISC P 15/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] EMER LANDING (Cont'd)
ALL ENG FAILURE
VAPP
L2
L1
/ 90 klb
150 kt
/ 110 klb
150 kt
/ 130 klb
163 kt
/ 155 klb
173 kt
/ 175 klb
183 kt
/ 200 klb
193 kt
/ 210 klb
198 kt
GND SPLRs........................................................................................................................... ARM
At 1 000 ft AGL at the latest:
GRAVITY GEAR EXTN handcrank............................................................ PULL AND TURN
Flight controls revert to direct law at landing gear extension. To ensure correct aircraft
trimming for approach, extend the landing gear only when the aircraft is in CONF 2 and
at VAPP . Disregard the ″USE MAN PITCH TRIM″ message on the PFD, because the
stabilizer is jammed, due to not sufficient hydraulic power.
When L/G downlocked:
L/G LEVER............................................................................................................ DOWN
At 500 ft AGL or below:
BRACE FOR IMPACT................................................................................................ORDER
For flare:
TOUCH DOWN AT MIN V/S
L2
At touchdown:
ALL ENG MASTERS........................................................................................................OFF
APU MASTER SW........................................................................................................... OFF
EMER EVAC PROC.................................................................................................... APPLY
Refer to PRO-ABN-MISC [QRH] EMER EVAC
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I
PRO-ABN-MISC P 16/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] FORCED LANDING
Ident.: PRO-ABN-MISC-00012090.0032001 / 09 MAY 17
Applicable to: ALL
If engines are not running, Refer to QRH/ABN-19 ENG DUAL FAILURE - FUEL REMAINING FORCED LANDING or Refer to QRH/ABN-19 ENG DUAL FAILURE - NO FUEL REMAINING FORCED LANDING
ATC..........................................................................................................................................NOTIFY
ATC XPDR 7700............................................................................................................... CONSIDER
PREPARE CABIN AND COCKPIT
Notify the cabin crew of the nature of the emergency and state intentions.
Specify the available time:
‐ Loose equipment secured.
‐ Survival equipment prepared.
‐ Belts and shoulder harnesses locked.
GPWS SYS................................................................................................................................... OFF
GPWS TERR.................................................................................................................................OFF
Switching the SYS pb and TERR pb OFF avoids nuisance warnings.
SIGNS..............................................................................................................................................ON
EMER EXIT LT............................................................................................................................... ON
COMMERCIAL...............................................................................................................................OFF
LDG ELEV..................................................................................................................................... SET
If not known, select an approximate value.
BARO............................................................................................................................................. SET
DISREGARD NORM C/Ls
ELT (when conditions permit)......................................................................................................... ON
For approach and landing:
RAM AIR...................................................................................................................................ON
Switch ON the RAM AIR to ensure complete cabin depressurization on ground.
L/G lever ............................................................................................................................DOWN
SLATS / FLAPS..........................................................................................................MAX AVAIL
GND SPLR.............................................................................................................................ARM
MAX BRK PR: 1000 PSI
At 2 000 ft AGL:
CABIN CREW......................................................................................... NOTIFY FOR LANDING
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J→
PRO-ABN-MISC P 17/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] FORCED LANDING (Cont'd)
At 500 ft AGL:
BRACE FOR IMPACT...................................................................................................... ORDER
At touchdown:
ALL ENG MASTERS.............................................................................................................. OFF
APU MASTER SW..................................................................................................................OFF
BRAKES ON ACCU ONLY
When aircraft stopped:
PARKING BRK......................................................................................................................... ON
ATC (VHF 1)...........................................................................................................................USE
With both engines and APU shut down, only VHF 1 is supplied.
ALL FIRE pb (ENGs & APU)...............................................................................................PUSH
ALL AGENTS (ENGs & APU)............................................................................................ DISCH
If evacuation required:
EVACUATION...........................................................................................................INITIATE
Make a short and precise announcement to order the emergency evacuation.
Press the EVAC COMMAND pb .
ELT........................................................................................................... CHECK EMITTING
If not, switch on the transmitter.
If evacuation not required:
CABIN CREW AND PASSENGERS (PA)................................................................. NOTIFY
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←J
PRO-ABN-MISC P 18/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] OVERWEIGHT LANDING
Ident.: PRO-ABN-MISC-00012093.0057001 / 17 MAR 17
Applicable to: ALL
USE CONF FULL FOR LANDING UNLESS SPECIFIED BY ABN PROC OR LIMITED BY
LANDING PERF
MAX WEIGHT (1 000 kg) FOR LANDING IN CONF FULL (GO AROUND IN CONF 3 CLIMB GRADIENT 2.1 %)
AIRPORT ELEVATION (feet)
0
2 000
4 000
6 000
8 000
10 000
12 000
14 000
85
83
84
81
77
71
66
61
<10
OAT (°C)
15
20
25
30
35
40
45
50
55
85
83
83
81
77
70
64
85
83
83
79
72
64
58
85
84
84
84
82
78
83
83
83
81
76
72
83
81
79
75
70
81
77
73
69
75
69
67
61
57
55
66
If aircraft weight above maximum weight for landing in conf FULL: USE FLAP 3 FOR
LANDING
LDG DIST.................................................................................................................................CHECK
For approach:
PACK 1...........................................................................................OFF OR SUPPLIED BY APU
PACK 2...........................................................................................OFF OR SUPPLIED BY APU
Selecting packs OFF (or supplied from APU) will increase the maximum thrust available from
the engines, in the event of a go-around.
If landing CONF other than full: USE CONF 1+F FOR GO AROUND
SPEED AT RUNWAY THRESHOLD: VLS
Reduce the selected speed on the FCU to reach VLS at runway threshold.
MINIMIZE V/S AT TOUCHDOWN
At main landing gear touchdown: USE MAX REVERSER
After nosewheel touchdown: APPLY BRAKES AS NECESSARY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K→
Continued on the following page
PRO-ABN-MISC P 19/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] OVERWEIGHT LANDING (Cont'd)
Maximum braking may be used after nosewheel touchdown. But, if landing distance permits,
delay or reduce braking to take full benefit of the available runway length.
When landing completed:
BRAKE FANS ................................................................................................................... ON
Be prepared for tire deflation, if temperatures exceed 800 °C.
[QRH] SEVERE TURBULENCE
Applicable to: ALL
Ident.: PRO-ABN-MISC-10-00002202.0001001 / 17 MAR 17
Whenever possible, avoid areas with known or forecasted severe turbulence. If turbulence is
unavoidable, aim to keep the speed in the region of the target speed given in this section, so as to
provide the best protection against the effect of gust on the structural limits, whilst maintaining an
adequate margin above VLS.
Sufficient buffet margin exists at optimum altitude. In order to further increase the margin to buffet
onset, consider descending to a lower altitude.
Severe turbulence is defined as turbulence that causes large, abrupt changes in altitude and/or
attitude. It usually causes large variations in airspeed. Occupants are forced violently against their
seat belts and loose objects will move around the aircraft.
If severe turbulence occurs during a flight, the flight crew must make a logbook entry in order to
initiate maintenance action.
Note:
Recommendations for severe turbulence are also applicable to extreme turbulence.
Ident.: PRO-ABN-MISC-10-00002203.0001001 / 22 FEB 17
Before the aircraft enters an area where turbulence is expected:
‐ All loose equipment must be secured in the cockpit and in the cabin
‐ The flight crew must set the SEAT BELTS sw to ON.
Ident.: PRO-ABN-MISC-10-00002301.0001001 / 09 DEC 09
Keep the autopilot ON.
When thrust changes become excessive : Disconnect Autothrust.
For approach : Use A/THR for managed speed.
Ident.: PRO-ABN-MISC-10-00002208.0002001 / 22 MAY 12
Set the thrust to give the recommended speed (Refer to PRO-ABN-MISC [QRH] Thrust Setting (N1)
for Recommended Speed). This thrust setting attempts to obtain, in stabilized conditions, the speed
for turbulence penetration given in the graph below.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← K to L →
PRO-ABN-MISC P 20/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
Only change thrust in case of an extreme variation in airspeed, and do not chase your Mach or
airspeed.
A transient increase is preferable to a loss of speed, that decreases buffet margins and is difficult to
recover.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←L→
PRO-ABN-MISC P 21/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
Ident.: PRO-ABN-MISC-10-00007380.0009001 / 16 NOV 11
Ident.: PRO-ABN-MISC-10-00007386.0001001 / 09 JUN 15
If the flight crew flies the aircraft manually:
‐ The flight crew may expect large variations in altitude, but should not chase altitude.
‐ The flight crew should consider descending to or below OPT FL, in order to increase the margin to
buffet.
Ident.: PRO-ABN-MISC-10-00007388.0002001 / 29 SEP 15
Configuration FULL, or 3, can be used.
CONF FULL provides better handling capability in turbulent conditions, however, CONF 3 provides
more energy and less drag.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←L
PRO-ABN-MISC P 22/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] TAILSTRIKE
Ident.: PRO-ABN-MISC-00012273.0001001 / 17 MAR 17
Applicable to: ALL
LAND ASAP
MAX FL: 100 / MEA-MORA
500 ft/min should be targeted for the climb, to minimize pressure changes, and for passenger and
crew comfort. Similarly, the rate of descent must be limited to about 1 000 ft/min, except for the final
approach that must be performed normally.
Notify the ATC of the aircraft’s rate of climb.
RAM AIR......................................................................................................................................... ON
PACK 1..........................................................................................................................................OFF
PACK 2..........................................................................................................................................OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-ABN-MISC P 23/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] VOLCANIC ASH ENCOUNTER
Ident.: PRO-ABN-MISC-00012176.0001001 / 17 MAR 17
Applicable to: ALL
180° TURN.............................................................................................................................INITIATE
The performance of a 180 ° turn will usually enable the aircraft to exit the volcanic ash clouds as
quickly as possible, because volcanic ash clouds can extend for hundreds of nautical miles.
ATC..........................................................................................................................................NOTIFY
Note:
Electrostatic conditions may cause communication problems.
A/THR............................................................................................................................................ OFF
This prevents the autothrust from generating thrust variations.
THRUST (IF CONDS PERMIT)............................................................................................ REDUCE
Reduced thrust minimizes ash ingestion.
If altitude permits, reduce thrust to idle. This maximizes engine surge margin and lowers engine
turbine temperature.
CREW OXY MASKS......................................................................................... USE / 100 % / EMER
CABIN CREW..........................................................................................................................NOTIFY
OXYGEN PASSENGER MASK MAN ON........................................................................... AS RQRD
Depending on contamination.
ENG ANTI ICE................................................................................................................................ ON
WING ANTI ICE.............................................................................................................................. ON
PACK FLOW..................................................................................................................................... HI
Maximum air bleed gives the engines additional stall margin.
CARGO ISOL VALVES ........................................................................................................OFF
Note:
To prevent a cargo smoke warning being triggered
ENGINE PARAMETERS..................................................................................................... MONITOR
Monitor particularly EGT . If EGT exceeds limits, it may become necessary to consider a
precautionary engine shutdown and engine restart in flight.
Note:
In the case of precautionary shutdown:
‐ restart when clear of the volcanic ash cloud
‐ Upon restart, the engine may accelerate very slowly. Do not misinterpret this as a
failure to start
‐ Consider that the compressor and turbine blades have been eroded and avoid sudden
changes in thrust. Fuel flow and EGT may increase.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-ABN-MISC P 24/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
[QRH] VOLCANIC ASH ENCOUNTER (Cont'd)
AIRSPEED INDICATIONS...................................................................................................MONITOR
If airspeed is unreliable or lost, Refer to PRO-ABN-NAV UNRELIABLE SPEED INDICATION Memory Items.
Note:
If both engines flame out and speed indications are lost,Refer to DUAL ENGINE FAILURE
procedure to get the required pitch attitude for the optimum relight speed. In case of
engine failure, switch off the wing anti ice before engine restart.
If visibility not sufficient for approach due to windshield damage:
CONSIDER AUTOLAND
For approach, if AUTOLAND is not available:
CAB PRESS MODE SEL................................................................................................MAN
MAN V/S CTL...........................................................................................................FULL UP
Due to the increased noise level, pay particular attention to visual warnings.
MAX SPEED: 200 kt
PF SLIDING WINDOW................................................................................................. OPEN
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PRO-ABN-MISC P 25/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
MISC
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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PRO-ABN-MISC P 26/26
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
[MEM] UNRELIABLE SPEED INDICATION
Applicable to: ALL
Ident.: PRO-ABN-NAV-AM-00017720.0002001 / 17 MAR 17
If the safe conduct of the flight is impacted:
AP.......................................................................................................................................... OFF
A/THR.................................................................................................................................... OFF
FD.......................................................................................................................................... OFF
PITCH/THRUST:
Below THRUST RED ALT.........................................................................................15° / TOGA
Above THRUST RED ALT and Below FL 100............................................................. 10° / CLB
Above THRUST RED ALT and Above FL 100...............................................................5° / CLB
FLAPS (if CONF 0(1)(2)(3)).......................................................... MAINTAIN CURRENT CONF
FLAPS (if CONF FULL)........................................................ SELECT CONF 3 AND MAINTAIN
SPEEDBRAKES........................................................................................CHECK RETRACTED
L/G........................................................................................................................................... UP
When at, or above MSA or Circuit Altitude: Level off for troubleshooting.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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PRO-ABN-NAV P 1/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
[MEM] UNRELIABLE SPEED INDICATION (Cont'd)
Ident.: PRO-ABN-NAV-AM-00017722.0008001 / 17 MAR 17
To level off:
AP............................................................................................................................................OFF
A/THR......................................................................................................................................OFF
FD............................................................................................................................................OFF
SPEEDBRAKES......................................................................................... CHECK RETRACTED
PITCH/THRUST TABLE.....................................................................................................APPLY
CONF
3
2
1+F
1
PITCH
7°
5.5°
5°
6.5°
PITCH
4°
at or below FL250
FL
100
200
300
350
400
3°
above
FL250
PITCH / THRUST FOR LEVEL OFF
70 t
60 t
155 000 lb
130 000 lb
SLATS / FLAPS EXTENDED
THRUST % N1 (Resultant speed)
64% (155 kt)
60% (140 kt)
62% (170 kt)
58% (160 kt)
62% (190 kt)
58% (175 kt)
62% (205 kt)
58% (190 kt)
CLEAN
THRUST % N1 (Resultant speed)
62% (245 kt)
60% (225 kt)
70% (245 kt)
66% (225 kt)
80% (265 kt)
76% (245 kt)
84% (255 kt)
80% (240 kt)
/
86% (235 kt)
50 t
110 000 lb
56% (130 kt)
54% (145 kt)
54% (160 kt)
54% (170 kt)
54% (205 kt)
62% (205 kt)
72% (225 kt)
76% (220 kt)
80% (220 kt)
FLYING TECHNIQUE TO STABILIZE SPEED
Stabilize the altitude. When altitude is stabilized:
‐ If the pitch is above the target pitch, increase the thrust and maintain the altitude.
‐ If the pitch is below the target pitch, decrease the thrust and maintain the altitude.
When the pitch reaches the target pitch, adjust the thrust to keep this target pitch.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-ABN-NAV P 2/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
[MEM] UNRELIABLE SPEED INDICATION (Cont'd)
Ident.: PRO-ABN-NAV-AM-00017724.0002001 / 17 MAR 17
When flight path is stabilized:
AP............................................................................................................................................OFF
A/THR......................................................................................................................................OFF
FD............................................................................................................................................OFF
SPEEDBRAKES......................................................................................... CHECK RETRACTED
FLIGHT PATH................................................................................................ KEEP STABILIZED
RESPECT STALL WARNING
Ident.: PRO-ABN-NAV-AM-00017725.0001001 / 17 MAR 17
AFFECTED ADR IDENTIFICATION
PROBE/WINDOW HEAT.............................................................................................................ON
ALL SPEED INDICATIONS.....................................................................................CROSSCHECK
ADR 3 and STBY speeds use the data of the same probe.
If at least one ADR confirmed reliable:
RELIABLE AIR DATA.........................................................................................................USE
UNRELIABLE ADR pb(s)....................................................................................................OFF
If affected ADR(s) cannot be identified, or all ADRs affected:
KEEP ONE ADR ON
TWO ADR pbs....................................................................................................................OFF
This prevents the flight control laws from using two coherent but unreliable ADR data.
FOR LANDING: USE FLAP 3
APP SPD ................................................................................................................VLS +10 kt
LDG DIST PROC........................................................................................................... APPLY
For flight continuation: USE PITCH/THRUST TABLES
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-ABN-NAV P 3/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
[MEM] UNRELIABLE SPEED INDICATION (Cont'd)
Ident.: PRO-ABN-NAV-AM-00017726.0008001 / 17 MAR 17
CLIMB
THRUST
CLB
FL
50
100
200
300
400
CLIMB IN CLEAN CONFIGURATION
70 t
60 t
155 000 lb
130 000 lb
PITCH (Resultant speed)
11° (235 kt)
13° (215 kt)
10° (235 kt)
12° (215 kt)
7° (235 kt)
8° (220 kt)
5° (235 kt)
6° (220 kt)
/
4° (215 kt)
50 t
110 000 lb
16° (195 kt)
14° (195 kt)
10° (195 kt)
7° (200 kt)
5° (195 kt)
CRUISE
FLYING TECHNIQUE TO STABILIZE SPEED
Stabilize the altitude. When altitude is stabilized:
‐ If the pitch is above the target pitch, increase the thrust and maintain the altitude.
‐ If the pitch is below the target pitch, decrease the thrust and maintain the altitude.
When the pitch reaches the target pitch, adjust the thrust to keep this target pitch.
PITCH
4°
at or below FL250
3°
above
FL250
Note:
LEVEL FLIGHT IN CLEAN CONFIGURATION
70 t
60 t
50 t
155 000 lb
130 000 lb
110 000 lb
FL
THRUST % N1 (Resultant speed)
100
62% (245 kt)
60% (225 kt)
54% (205 kt)
200
70% (245 kt)
66% (225 kt)
62% (205 kt)
300
80% (265 kt)
76% (245 kt)
72% (225 kt)
350
84% (255 kt)
80% (240 kt)
76% (220 kt)
400
/
86% (235 kt)
80% (220 kt)
If the failure is due to radome destruction, the drag will increase and therefore N1 must
be increased by 5 %. Fuel flow will increase by about 27 %.
DESCENT
THRUST
IDLE
DESCENT IN CLEAN CONFIGURATION
70 t
60 t
155 000 lb
130 000 lb
PITCH
Resultant speed
1°
245 kt
230 kt
50 t
110 000 lb
210 kt
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-ABN-NAV P 4/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
[MEM] UNRELIABLE SPEED INDICATION (Cont'd)
INITIAL / INTERMEDIATE APPROACH
APPLY FLYING TECHNIQUE TO STABILIZE SPEED
CONF
0
1
1+F
2
PITCH
5.5°
6.5°
5°
5.5°
3
7°
LEVEL FLIGHT
70 t
60 t
155 000 lb
130 000 lb
WITH LANDING GEAR UP
THRUST % N1 (Resultant speed)
58% (225 kt)
54% (205 kt)
62% (205 kt)
58% (190 kt)
62% (190 kt)
58% (175 kt)
62% (170 kt)
58% (160 kt)
WITH LANDING GEAR DOWN
70% (155 kt)
64% (140 kt)
50 t
110 000 lb
50% (185 kt)
54% (170 kt)
54% (160 kt)
54% (145 kt)
60% (130 kt)
FINAL APPROACH AT -3° DESCENT FLIGHT PATH
CONF
3
APPROACH IN CONF 3 AND L/G EXTENDED
70 t
60 t
155 000 lb
130 000 lb
PITCH
THRUST (% N1)
4°
54%
50%
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
50 t
110 000 lb
46%
PRO-ABN-NAV P 5/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
[QRH] ADR 1+2+3 FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-C-00017828.0002001 / 17 MAR 17
In case of a triple ADR failure, ECAM only displays dual ADR alerts.
All dual ADR alerts trigger: NAV ADR 1+2 FAULT, and NAV ADR 1+3 FAULT, and NAV ADR 2+3
FAULT.
L2
L1
Note:
In case of a simultaneous ADR and IR (same ADIRU ) failure, apply the ADR FAULT
procedure prior to the IR FAULT procedure.
ALL ADR pbs................................................................................................................................ OFF
WHEN ALL ADR OFF BOTH FMS LOST
STBY INST....................................................................................................................................USE
BACK UP NAV..............................................................................................................................USE
Revert to Back Up Nav via the NAV B/UP Prompt on the MCDU MENU page.
USE RMP FOR NAVAID TUNING
DISREGARD ECAM ACTIONS FOR AIR DATA SWTG AND ATC
Air data switching and ATC have no effect.
TCAS & ATC ALT RPTG INOP
Ident.: PRO-ABN-NAV-C-00017830.0002001 / 22 MAR 17
MAX SPEED...........................................................................................................................320/0.82
See the following table for the IAS/M relationship for 0.82
FL
MAX SPD
390
252
370
265
350
278
330
290
310
305
290
315
280 and below
320
WHEN L/G DN: DIRECT LAW
At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW).
Note:
Use manual control of cabin pressurization:
MODE SEL.................................................................................................................... MAN
MAN V/S CTL....................................................................................................... AS RQRD
These lines are not displayed on the ECAM. (For details, Refer to PRO-ABN-CAB_PR
CAB PR SYS 1+2 FAULT - FWSPAGE).
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-ABN-NAV P 6/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
[QRH] ADR 1+2+3 FAULT (Cont'd)
Ident.: PRO-ABN-NAV-C-00021399.0009001 / 17 MAR 17
EXPECT ALTN LAW
FL
MAX SPEED (kt)
390
252
370
265
350
278
330
290
310
305
290
315
280 and below
320
This table provides IAS/MACH 0.82 relationship at or above FL 280.
USE RUDDER WITH CARE
At slats extension, full rudder travel authority is recovered.
WHEN L/G DOWN: DIRECT LAW
At landing gear extension, flight controls revert to direct law in pitch and in roll.
CABIN PRESS MODE SEL......................................................................................................... MAN
MAN V/S CTL...................................................................................................................... AS RQRD
Target CAB PRESS V/S:
‐ Climb: 500 ft/min
‐ Descent: 300 ft/min
AIRCRAFTCRZ FL
410
350
300
250
<200
CAB ALT TARGET (ft)
8000
7000
5500
3000
0
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-NAV P 7/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
[QRH] ADR 1+2+3 FAULT (Cont'd)
Ident.: PRO-ABN-NAV-C-00021262.0001001 / 17 MAR 17
For approach:
CAT 1 ONLY
FOR LANDING: USE FLAP 3
GPWS LDG FLAP 3.................................................................................................................ON
LDG DIST PROC............................................................................................................... APPLY
For L/G GRVTY EXTN:
LDG GEAR GRVTY EXTN handcrank....................................................... PULL AND TURN
When L/G downlocked:
L/G lever.......................................................................................................................DOWN
GEAR DOWN indications........................................................................................... CHECK
L/G DOORS REMAIN OPEN
During final approach:
MAN V/S CTL...........................................................................................................FULL UP
Before door opening: CHECK ΔP ZERO
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-NAV P 8/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
[QRH] ADR 1+2+3 FAULT (Cont'd)
Ident.: PRO-ABN-NAV-C-00016863.0002001 / 22 MAR 17
STATUS
MAX SPEED.............................................................. 320/0.82
MANEUVER WITH CARE
RUD WITH CARE ABV 160 KT
(1)
See
APPR PROC
FOR LDG............................................................ USE FLAP 3
Do not select CONF FULL, so as not to degrade handling
qualities.
GPWS LDG FLAP 3...........................................................ON
Displayed, when CONF 3 is selected.
APPR SPD........................................................ VREF +10 KT
LDG DIST PROC......................................................... APPLY
Note:
As the landing gear safety valve is closed, landing
gear extension must be performed by gravity
(Refer to PRO-ABN-LG [QRH] L/G GRAVITY
EXTENSION).
WHEN L/G DN : DIRECT LAW
At landing gear extension, control reverts to direct law in
pitch, as well as in roll.
DURING FINAL APPR
MAN V/S CTL.....................................................FULL UP
Note:
INOP SYS
F/CTL PROT
WINDSHEAR DET
GPWS
ADR 1+2+3
AP 1+2
A/THR
RUD TRV LIM 1+2
CAB PR 1+2
YAW DAMPER
ATC/XPDR 1
ATC/XPDR 2
STEEP APPR
ROW/ROP
Other INOP SYS
ATC ALTI MODE
TCAS
L/G RETRACT
RAT AUTOMATIC EXTENSION
CAT 2
In case of a go-around, respect the maximum
speed of 215 kt in CONF 1+F, due to loss of
flap auto retraction to CONF 1.
CAUTION
Check that the outflow valve is fully
open and that cabin altitude is at airfield
elevation before opening the doors.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-ABN-NAV P 9/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
[QRH] ADR 1+2+3 FAULT (Cont'd)
(1)
The rudder travel limit value is frozen at the moment when the failure occurs. Therefore, to
prevent damage to the aircraft structure, use the rudder with care, when the speed is above
160 kt. At slats’ extension, full rudder travel authority is recovered.
[QRH] ADR CHECK PROC
Ident.: PRO-ABN-NAV-00015311.0001001 / 17 MAR 17
Applicable to: ALL
For the ADR CHECK procedure, apply the UNRELIABLE SPEED INDICATION procedure. Refer to
PRO-ABN-NAV UNRELIABLE SPEED INDICATION - Memory Items.
[QRH] IR ALIGNMENT IN ATT MODE
Ident.: PRO-ABN-NAV-00012425.0006001 / 17 MAR 17
Applicable to: ALL
If IR alignment is lost, the navigation mode is inoperative (red ATT flag on PFD and red HDG flag
on ND).
Aircraft attitude and heading may be recovered by applying the following procedure:
IR MODE sel (affected IR)............................................................................................................ ATT
KEEP SPEED, HEADING, AND FL CONSTANT FOR 30 s
FMS DATA page.................................................................................................................... SELECT
The DATA INDEX page is displayed
IRS MONITOR key...................................................................................................................PRESS
[SET HDG key] A/C HDG........................................................................................................ ENTER
CROSSCHECK HEADING REGULARLY WITH STBY COMPASS AND UPDATE AS REQUIRED
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to D
PRO-ABN-NAV P 10/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ADR 1(2)(3) FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-A-00018111.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the ADR 1(2)(3) is failed.
Flight Phase Inhibition:
Note:
(a) Not inhibited in flight phase 3 in the case of NAV ADR 3 FAULT while the ADR 3 is in
use.
Not inhibited in flight phases 3, 5, and 7 in the case of NAV ADR 1(2) FAULT.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
PRO-ABN-NAV P 11/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ADR 1(2)(3) FAULT (Cont'd)
Ident.: PRO-ABN-NAV-A-00017302.0003001 / 21 MAR 16
L2
Note:
In case of simultaneous failure of ADR and IR (same ADIRU ), apply ADR FAULT
procedure before IR FAULT procedure.
L1
ADR 1 FAULT:
AIR DATA SWTG..............................................................................................................CAPT 3
L2
Select ADR 3 to captain side.
For aircraft equipped with EGPWS , T2CAS or T3CAS , the GPWS TERR FAULT
light comes on, because the predictive functions of the GPWS are inhibited. As such, the
GPWS TERR pb-sw should be switched OFF.
L1
ADR 1 P/B.............................................................................................................................. OFF
ADR 2 FAULT:
AIR DATA SWTG................................................................................................................. F/O 3
L2
Select ADR 3 to first officer side.
L1
ADR 2 P/B.............................................................................................................................. OFF
BARO REF........................................................................................................................ CHECK
L2
If ADR 2 fails, both baro reference channels are driven by the same FCU channel.
Consequently the baro reference displays must be checked.
L1
ADR 3 FAULT:
ADR 3 P/B.............................................................................................................................. OFF
AIR DATA SWTG (IF ADR 3 IN USE)............................................................................... NORM
Ident.: PRO-ABN-NAV-A-00017505.0001001 / 21 MAR 16
STATUS
INOP SYS
CAT 3 SINGLE ONLY
ADR 1(2)(3)
CAT 3 DUAL
GPWS
(1)
(1)
(in case of ADR 1 FAULT only)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-ABN-NAV P 12/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ADR 1+2(1+3)(2+3) FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-B-00018113.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when two ADRs are failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PRO-ABN-NAV P 13/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ADR 1+2(1+3)(2+3) FAULT (Cont'd)
Ident.: PRO-ABN-NAV-B-00017147.0003001 / 22 MAR 17
L2
Flight control normal laws are lost. Pitch alternate law preserves the neutral static stability. All
protections, except maneuver protections are lost.
Note:
In case of a simultaneous ADR and IR (same ADIRU ) failure, apply the ADR FAULT
procedure prior to the IR FAULT procedure.
L1
ADR 1+2 FAULT:
AIR DATA SWTG..............................................................................................................CAPT 3
L2
Set ADR 3 pb-sw (if available) to the captain's side.
L1
ADR (AFFECTED) P/B........................................................................................................... OFF
L2
As the enhanced functions of the EGPWS or the predictive functions of the GPWS (for
aircraft equipped with T2CAS or T3CAS ) are inhibited, the GPWS TERR FAULT light
comes on. As such, the GPWS TERR pb-sw should be switched OFF.
L1
ASSOCIATED PROCEDURES
L2
L1
L2
F/CTL ALTN LAW
(PROT LOST)
MAX SPEED...................................................................................................................... 320 KT
Speed is limited, due to the loss of high-speed protections.
ADR 1+3 (or 2+3) FAULT:
Air data information is lost on one PFD.
Note:
L1
L2
In case of an ADR 1+3 FAULT, the landing gear safety valve is controlled closed:
‐ Landing gear retraction is inoperative
‐ Landing gear extension must be performed by gravity.
AIR DATA SWTG................................................................................................................NORM
ATC/XPDR (IF ADR 1 FAILED).......................................................................................... SYS 2
ATC/XPDR (IF ADR 2 FAILED).......................................................................................... SYS 1
ADR (AFFECTED) P/B........................................................................................................... OFF
As the enhanced functions of the EGPWS or the predictive functions of the GPWS (for
aircraft equipped with T2CAS or T3CAS ) are inhibited, the GPWS TERR FAULT light
comes on in case of an ADR 1+3 FAULT. As such, the GPWS TERR pb-sw should be switched
OFF.
Continued on the following page
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FCOM
←F→
PRO-ABN-NAV P 14/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ADR 1+2(1+3)(2+3) FAULT (Cont'd)
L1
ASSOCIATED PROCEDURES
L2
F/CTL ALTN LAW
(PROT LOST)
MAX SPEED...................................................................................................................... 320 KT
Speed is limited, due to the loss of high-speed protections.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-ABN-NAV P 15/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ADR 1+2(1+3)(2+3) FAULT (Cont'd)
Ident.: PRO-ABN-NAV-B-00017397.0009001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320 KT
APPR PROC
FOR LDG............................................................ USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF3 is selected, as a reminder.
GPWS LDG FLAP 3...........................................................ON
Appears when CONF 3 is selected.
If ADR 1+3 FAULT:
L/G..............................................................GRVTY EXTN
Refer to PRO-ABN-LG [QRH] L/G GRAVITY
EXTENSION
INOP SYS
F/CTL PROT
ADR 1 + 2 or (2 + 3) or (1 + 3)
AP 1 + 2
A/THR
ATC/XPDR 1
ATC/XPDR 2
(1)
(2)
(3)
RUD TRV LIM 1(2)
GPWS (if ADR 1 fault)
CAT 2
GLS AUTOLAND
STEEP APPR
ROW/ROP
APPR SPD....................................................... VREF + 10 KT
LDG DIST PROC......................................................... APPLY
ALTN LAW : PROT LOST
WHEN L/G DN : DIRECT LAW
At L/G extension, control reverts to direct law in pitch and roll
(Refer to PRO-ABN-F_CTL F/CTL DIRECT LAW).
FLS LIMITED TO F–APP + RAW
If ADR 1 + 3 (or 2 + 3) FAULT:
BOTH PFD ON THE SAME FAC
As the enhanced functions of the EGPWS or the
predictive functions of the GPWS (for aircraft equipped
with T2CAS or T3CAS ) are inhibited, the GPWS
TERR FAULT light comes on in case of an ADR 1+3
FAULT. As such, the GPWS TERR pb-sw should be
switched OFF.
(1)
(2)
(ATC/XPDR 1 in the case of ADR 1 failure)
(ATC/XPDR 2 in the case of ADR 2 failure)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Continued on the following page
←F→
PRO-ABN-NAV P 16/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ADR 1+2(1+3)(2+3) FAULT (Cont'd)
(3)
(in the case of an ADR 1 + 3 FAULT or in the case of an ADR 2 + 3 FAULT)
NAV ADR DISAGREE
Applicable to: ALL
Ident.: PRO-ABN-NAV-U-00018110.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the following conditions occur:
‐ The ELAC rejected an ADR , or an ADR is faulty
‐ The speed or the Angle Of Attack (AOA ) from the two remaining ADRs are different.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G →
PRO-ABN-NAV P 17/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ADR DISAGREE (Cont'd)
Ident.: PRO-ABN-NAV-U-00017130.0002001 / 22 MAR 17
L2
L1
L2
L1
The alternate law activates, and protections are lost.
AIR SPD............................................................................................................................... X CHECK
IF SPD DISAGREE:
ADR CHECK PROC...........................................................................................................APPLY
To determine the faulty ADR, Refer to PRO-ABN-NAV UNRELIABLE SPEED INDICATION Memory Items.
IF NO SPD DISAGREE:
AOA DISCREPANCY
ASSOCIATED PROCEDURES
F/CTL ALTN LAW
(PROT LOST)
MAX SPEED.............................................................................................................................320 KT
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
PRO-ABN-NAV P 18/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ADR DISAGREE (Cont'd)
Ident.: PRO-ABN-NAV-U-00017131.0001001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320 KT
APPR PROC
INOP SYS
F/CTL PROT
STEEP APPR
FOR LDG............................................................ USE FLAP 3
Do not select CONF FULL, so as not to degrade handling
qualities.
GPWS LDG FLAP 3...........................................................ON
Displayed, when CONF 3 is selected.
APPR SPD.............................................................. VREF +10
LDG DIST PROC......................................................... APPLY
IF NO SPD DISAGREE:
RISK OF UNDUE STALL WARN
ALTN LAW: PROT LOST
WHEN L/G DN: DIRECT LAW
(1)
See
(1)
At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-ABN-NAV P 19/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ALTI DISCREPANCY
Applicable to: ALL
Ident.: PRO-ABN-NAV-AO-00018116.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the difference between the altitude displayed on the CAPT and F/O
PFDs is greater than:
‐ 500 ft, if STD BARO reference is selected
‐ 250 ft, if QNH or QFE BARO reference is selected.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-AO-00012411.0002001 / 09 APR 14
ALT....................................................................................................................................... X CHECK
Crosscheck with the standby altimeter.
L1 AIR DATA SWTG................................................................................................................ AS RQRD
L2 Select ADR 3 to the faulty side.
L2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
PRO-ABN-NAV P 20/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV CAPT(F/O)(STBY) AOA FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-V-00018124.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the CAPT (F/O )(STBY ) Angle Of Attack (AOA) sensor is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-V-00012458.0003001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-NAV-V-00012459.0003001 / 19 JUN 12
STATUS
INOP SYS
CAPT (F/O) (STBY)
AOA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I
PRO-ABN-NAV P 21/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ATT DISCREPANCY
Applicable to: ALL
Ident.: PRO-ABN-NAV-AQ-00018122.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the difference between the roll or pitch angle displayed on the CAPT
and F/O PFDs is greater than 5 °.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-AQ-00012410.0001001 / 19 AUG 10
ATT....................................................................................................................................... X CHECK
Crosscheck with standby horizon.
L1 ATT HDG SWTG................................................................................................................. AS RQRD
L2 Select IR 3 (if available) to faulty side.
L2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J
PRO-ABN-NAV P 22/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV BARO REF DISCREPANCY
Applicable to: ALL
Ident.: PRO-ABN-NAV-AR-00018123.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the BARO reference is not the same on CAPT and F/O sides.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-AR-00012413.0001001 / 16 NOV 11
L2
BARO REF........................................................................................................................... X CHECK
Crosscheck the barometric reference selection, captain side versus first officer side.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K
PRO-ABN-NAV P 23/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV FM/GPS POS DISAGREE
Applicable to: ALL
Ident.: PRO-ABN-NAV-AG-00017090.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the FM and GPS positions disagree.
Flight Phase Inhibition:
Note:
(a) Alert inhibited only for the first 15 s in flight phase 5.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
L→
PRO-ABN-NAV P 24/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV FM/GPS POS DISAGREE (Cont'd)
Ident.: PRO-ABN-NAV-AG-00017148.0003001 / 17 MAR 17
A/C POS...................................................................................................................................CHECK
The following procedure is not displayed on the ECAM:
During climb, cruise, or descent:
Check accuracy on the MCDU PROG page:
If ESTIMATED ACCUR below REQUIRED ACCUR:
CONSIDER NAV MODE AND ND ARC/ROSE NAV
If ESTIMATED ACCUR above REQUIRED ACCUR:
HDG/TRK MODE.......................................................................................................SELECT
USE RAW DATA
When possible, compare the positions of both FMs with the GPIRS position, on the MCDU
POSITION MONITOR page:
If one FM position agrees with onside GPIRS position:
USE ASSOCIATED AP/FD
If both FM positions DO NOT agree with onside GPIRS position:
GPS...................................................................................................................... DESELECT
USE RAW DATA
During ILS/MLS /LOC approach:
NAV MODE: DO NOT USE
CONTINUE APPROACH
During LOC only approach with FLS :
NAV MODE: DO NOT USE
DISREGARD F-G/S DEVIATION
REVERT TO VERTICAL SELECTED MODE
During RNAV GNSS, RNAV RNP, or GLS approach:
If visual references not sufficient: GO AROUND
During VOR, VOR-DME, NDB, or NDB-DME approach:
HDG/TRK MODE............................................................................................................. SELECT
USE RAW DATA
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←L→
PRO-ABN-NAV P 25/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV FM/GPS POS DISAGREE (Cont'd)
If FLS used:
LS pb........................................................................................................................... PRESS
FLS deviations are removed from PFD.
NAV GPS 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-L-00018144.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the GPS 1(2) is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-L-00017127.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-NAV-L-00017128.0001001 / 21 MAR 16
STATUS
If both GPS FAULT
FLS LIMITED TO F-APP + RAW
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
INOP SYS
GPS 1(2)
← L to M
PRO-ABN-NAV P 26/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV GPWS FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-N-00018129.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alerts triggers when the GPWS fails.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-N-00012443.0001001 / 16 NOV 11
L2
GPWS............................................................................................................................................ OFF
This line remains displayed, even after the GPWS pb-sw has been switched OFF.
Ident.: PRO-ABN-NAV-N-00012444.0001001 / 19 AUG 10
STATUS
INOP SYS
GPWS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
N
PRO-ABN-NAV P 27/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV GPWS TERR DET FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-AS-00018130.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the enhanced TCF and TAD modes of the EGPWS or the
predictive function of the GPWS (for aircraft equipped with T2CAS or T3CAS ) are
inoperative.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-AS-00017542.0001001 / 21 MAR 16
L2
GPWS TERR.................................................................................................................................OFF
The basic GPWS mode 1 to mode 5 are still operative if SYS pb-sw lights FAULT or OFF are not
illuminated.
Ident.: PRO-ABN-NAV-AS-00019752.0001001 / 01 JUN 16
STATUS
INOP SYS
GPWS TERR
ROW/ROP
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
O
PRO-ABN-NAV P 28/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV HDG DISCREPANCY
Applicable to: ALL
Ident.: PRO-ABN-NAV-AT-00018131.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the difference between the headings on the CAPT and F/O displays
(PFD and ND) is greater than 5 °.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-AT-00012409.0003001 / 19 AUG 10
HDG......................................................................................................................................X CHECK
Compare the 3 IR headings on MCDU or crosscheck with standby compass.
L1 ATT HDG SWTG................................................................................................................. AS RQRD
L2 Select IR 3 (if available) to faulty side.
L2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
P
PRO-ABN-NAV P 29/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV IAS DISCREPANCY
Applicable to: ALL
Ident.: PRO-ABN-NAV-W-00018146.0003001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the speed displayed on the CAPT and F/O PFDs are different.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-W-00017528.0001001 / 21 MAR 16
AIR SPD............................................................................................................................... X CHECK
AIR DATA SWTG................................................................................................................ AS RQRD
Ident.: PRO-ABN-NAV-W-00017525.0001001 / 21 MAR 16
STATUS
INOP SYS
CAT 3 SINGLE ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
CAT 3 DUAL
Q
PRO-ABN-NAV P 30/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV ILS 1(2)(1+2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-M-00018138.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the ILS 1(2)(1+2) is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-M-00017125.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-NAV-M-00017126.0002001 / 21 MAR 16
STATUS
INOP SYS
ILS 1(2)(1+2)
CAT 2
GPWS
(1)
(2)
(1)
(2)
(If ILS 1 FAULT or if ILS 2 FAULT)
(if ILS 1 FAULT on ground or if ILS 1+2 FAULT)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
R
PRO-ABN-NAV P 31/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV IR 1(2)(3) FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-D-00018140.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the IR 1(2)(3) is failed.
Flight Phase Inhibition:
Note:
(a) Alert not inhibited in flight phase 3 in the case of NAV IR 3 FAULT while the ADR 3 is
in use.
Alert not inhibited in flight phase 3 in the case of NAV IR 1(2) FAULT.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
S→
PRO-ABN-NAV P 32/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV IR 1(2)(3) FAULT (Cont'd)
Ident.: PRO-ABN-NAV-D-00017521.0003001 / 21 MAR 16
L2
L1
Note:
In case of a simultaneous ADR and IR (same ADIRU ) failure, apply the ADR FAULT
procedure before the IR FAULT procedure.
IR 1 FAULT:
ATT HDG SWTG.............................................................................................................. CAPT 3
ATC/XPDR...........................................................................................................................SYS 2
IR 2 FAULT:
ATT HDG SWTG..................................................................................................................F/O 3
ATC/XPDR...........................................................................................................................SYS 1
IR 3 FAULT:
ATT HDG SWTG (IF IR 3 IN USE).................................................................................... NORM
L2
This line is not displayed on the ECAM.
Ident.: PRO-ABN-NAV-D-00017123.0001001 / 21 MAR 16
L12
STATUS
INOP SYS
IR MAY BE AVAIL IN ATT
Refer to PRO-ABN-NAV [QRH] IR ALIGNMENT IN ATT
MODE
CAT 3 SINGLE ONLY
IR 1(2)(3)
cat 3 DUAL
GPWS TERR
TCAS
ATC/XPDR 1
ATC/XPDR 2
See
(1)
(2)
(3)
(1)
(1)
(1)
(2)
(3)
(In case of an IR 1 fault)
(In case of an IR 2 fault )
Note:
In Case of an IR 1 fault, the TCAS may be inoperative (depending on the TCAS
manufacturer). If the IR 1 is available in ATT mode, the TCAS can be recovered by
entering the aircraft magnetic heading into the CDU , as per the IR ALIGNMENT IN ATT
MODE procedure.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←S→
PRO-ABN-NAV P 33/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV IR 1(2)(3) FAULT (Cont'd)
Ident.: PRO-ABN-NAV-D-00015142.0001001 / 29 JUL 13
The loss or the failure of an Inertial Reference System (IRS ) may result in the loss of the FMS.
Refer to DSC-22_20-100-20 Loss Of FMS Position Further To IRS Loss.
NAV IR 1+2(1+3)(2+3) FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-E-00018139.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when IR 1+2(1+3)(2+3) are failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← S to T →
PRO-ABN-NAV P 34/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV IR 1+2(1+3)(2+3) FAULT (Cont'd)
Ident.: PRO-ABN-NAV-E-00017111.0002001 / 22 MAR 17
L2
Note:
In case of a simultaneous ADR and IR (same ADIRU ) failure, apply the ADR FAULT
procedure prior to the IR FAULT procedure.
L1
If IR 1 + 2 FAULT:
ATT HDG SWTG.............................................................................................................. CAPT 3
L2
Set IR 3 (If available) to the Captain's side.
Attitude information is lost on first officer's PFD.
L1
If IR 1 + 3 (or 2 + 3) FAULT:
ATT HDG SWTG................................................................................................................ NORM
L2
Attitude information is lost on one side (Captain or first officer).
L1
ASSOCIATED PROCEDURES
L2
L1
L2
F/CTL ALTN LAW
(PROT LOST)
Flight control normal laws are lost. Pitch alternate law with static stability becomes active.
All protections, except maneuver protections, are lost.
MAX SPEED...................................................................................................................... 320 KT
Speed is limited, due to the loss of high speed protection.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←T→
PRO-ABN-NAV P 35/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV IR 1+2(1+3)(2+3) FAULT (Cont'd)
Ident.: PRO-ABN-NAV-E-00016864.0004001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320 KT
APPR PROC
FOR LDG............................................................ USE FLAP 3
This line is replaced by “FOR LDG : USE FLAP 3” when
CONF 3 is selected, as a reminder.
GPWS LDG FLAP 3...........................................................ON
Will appear, when CONF 3 is selected.
APPR SPD : VREF + 10 KT
LDG DIST PROC......................................................... APPLY
ALTN LAW : PROT LOST
WHEN L/G DN : DIRECT LAW
At landing gear extension, control reverts to direct law, in
pitch, as well as in roll (Refer to PRO-ABN-F_CTL F/CTL
DIRECT LAW).
IR (AFFECTED) MAY BE AVAIL IN ATT
Refer to PRO-ABN-NAV [QRH] IR ALIGNMENT IN ATT
MODE
FLS LIMITED TO F–APP + RAW
Note:
(1)
(2)
(3)
(4)
INOP SYS
F/CTL PROT
IR 1 (2)(3)
IR 1+2 or 1+3 or 2+3
AP 1+2
A/THR
YAW DAMPER 1
(1)
(2)
YAW DAMPER 2
GPWS TERR (if IR 1 fault)
TCAS
CAT 2
ATC/XPDR 1
(3)
(4)
ATC/XPDR 2
GLS AUTOLAND
STEEP APPR (if at least 2
IRs are lost)
ROW/ROP
In case of an IR 1 fault, the TCAS may be inoperative (depending on the TCAS
manufacturer). If the IR 1 is available in ATT mode, the TCAS can be recovered by
entering the aircraft magnetic heading into the CDU , as per IR ALIGNMENT IN ATT
MODE procedure.
(In case of an IR 1+3 fault)
(In case of an IR 2+3 fault)
(In the case of an IR 1 or IR 1+2 or IR 1+3 failure)
(In the case of an IR 2 or IR 1+2 or IR 2+3 failure)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←T
PRO-ABN-NAV P 36/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV IR DISAGREE
Applicable to: ALL
Ident.: PRO-ABN-NAV-G-00018147.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one IR is failed, and the information received from the two remaining
IRs is different.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
U→
PRO-ABN-NAV P 37/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV IR DISAGREE (Cont'd)
Ident.: PRO-ABN-NAV-G-00016851.0001001 / 22 MAR 17
L2
Direct law becomes active. All protections (pitch and roll) are lost.
ATT....................................................................................................................................... X CHECK
L2 Use the standby horizon to determine the faulty IR.
L1
L1
IF DISAGREE CONFIRMED:
FAULTY IR............................................................................................................................ OFF
L2
‐ If the ADIRS Control Panel has the IR pb, turn off the faulty IR using the associated IR pb.
‐ If the ADIRS Control Panel does not have the IR pb, set the ADIRS selector to OFF. This
action will also switch off the associated ADR.
L1
ELAC 2..................................................................................................................OFF THEN ON
ELAC 1..................................................................................................................OFF THEN ON
L2
Note:
When the ELAC 1 computer is reset on ground, the pitch trim returns to the ground
setting position (0 °).
After corrective action (faulty IR switched off and ELACs reset), pitch alternate law
with reduced protections is recovered.
L1
ASSOCIATED PROCEDURES
F/CTL ALTN LAW
(PROT LOST)
MAX SPEED...................................................................................................................... 320 KT
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←U→
PRO-ABN-NAV P 38/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV IR DISAGREE (Cont'd)
Ident.: PRO-ABN-NAV-G-00016852.0001001 / 22 MAR 17
L12
STATUS
MAX SPEED................................................................ 320 KT
APPR PROC
INOP SYS
F/CTL PROT
STEEP APPR
FOR LDG............................................................ USE FLAP 3
Do not select CONF FULL, so as not to degrade handling
qualities.
GPWS LDG FLAP 3...........................................................ON
Will be displayed, when CONF 3 is selected.
APPR SPD.............................................................VREF + 10
LDG DIST PROC......................................................... APPLY
ALTN LAW: PROT LOST
WHEN L/G DN: DIRECT LAW
(1)
See
(1)
At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←U
PRO-ABN-NAV P 39/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV IR NOT ALIGNED
Applicable to: ALL
Ident.: PRO-ABN-NAV-AU-00018141.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is a problem during IR alignment.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-AU-00012570.0001001 / 19 AUG 10
L2
This caution is available in Phase 2 (after first engine start, until takeoff)
L1
POSITION DISAGREE
POSITION MISSING
PRESENT POS....................................................................................................................... INSERT
EXCESS MOTION
IR 1 (2) (3) (1+2) (2+3) (1+2+3) IN ALIGN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
V
PRO-ABN-NAV P 40/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV PRED W/S DET FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-F-00018855.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the predictive function is lost.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-F-00018853.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-NAV-F-00018854.0001001 / 21 MAR 16
STATUS
INOP SYS
PRED W/S DET
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
W
PRO-ABN-NAV P 41/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV RA 1 AND 2 FAULT
(DUAL RA FAILURE)
Applicable to: ALL
Ident.: PRO-ABN-NAV-J-00018403.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both RAs are failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-J-00012432.0001001 / 25 FEB 14
Crew awareness.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
X→
PRO-ABN-NAV P 42/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV RA 1 AND 2 FAULT (Cont'd)
(DUAL RA FAILURE)
Ident.: PRO-ABN-NAV-J-00016850.0003001 / 01 JUN 16
L12
STATUS
INOP SYS
WHEN L/G DN: DIRECT LAW
(1)
See
(1)
RA 1+2
A/CALL OUT
GPWS
CAT 2
GLS AUTOLAND
STEEP APPR
REAC W/S DET
TCAS
ROW/ROP
At landing gear extension, flight controls revert to direct law in pitch, as well as in roll (Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW).
ILS APPR mode cannot be engaged, LOC mode is available via the FCU LOC pb.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←X
PRO-ABN-NAV P 43/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV RA 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-I-00018135.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the RA 1(2) is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-I-00012430.0001001 / 25 FEB 14
Crew awareness.
Ident.: PRO-ABN-NAV-I-00016849.0001001 / 01 JUN 16
STATUS
INOP SYS
CAT 2 ONLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
RA 1(2)
CAT 3
GPWS (If RA 1 fault)
ROW/ROP
Y
PRO-ABN-NAV P 44/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV RA DEGRADED
Applicable to: ALL
Ident.: PRO-ABN-NAV-AV-00018134.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the height that RA 1 and RA 2 provide are significantly different.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-AV-00018933.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Z
PRO-ABN-NAV P 45/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV TCAS FAULT
Applicable to: ALL
Ident.: PRO-ABN-NAV-K-00018397.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when there is an internal failure of the TCAS.
Flight Phase Inhibition:
Ident.: TDU / PRO-ABN-NAV-K-00015480.0017001 / 14 FEB 14
Impacted DU: 00012434 NAV TCAS FAULT (If Installed)
Crew awareness.
Note:
On ground, if the alert is triggered while the ADIRU s are OFF, or while IR 1 is not yet
aligned, the flight crew can disregard it. The alert automatically disappears once the
ADIRU s are powered and upon the alignment of IR1.
Ident.: PRO-ABN-NAV-K-00012434.0001001 / 25 FEB 14
Impacted by TDU: 00015480 NAV TCAS FAULT
Crew awareness.
Continued on the following page
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AA →
PRO-ABN-NAV P 46/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
NAV TCAS FAULT (Cont'd)
Ident.: PRO-ABN-NAV-K-00012435.0001001 / 19 AUG 10
STATUS
INOP SYS
TCAS
NAV TCAS STBY
Applicable to: ALL
Ident.: PRO-ABN-NAV-AW-00018133.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the flight crew sets the TCAS on STBY in flight.
Flight Phase Inhibition:
Ident.: PRO-ABN-NAV-AW-00018847.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← AA to AB
PRO-ABN-NAV P 47/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
NAV
FLIGHT CREW
OPERATING MANUAL
STALL WARNING
Ident.: PRO-ABN-NAV-00013994.0001001 / 21 MAR 17
Applicable to: ALL
When the threshold is reached, a permanent aural warning is triggered "STALL + CRICKET"
as long as a correct angle-of-attack is not recovered. (Refer to PRO-ABN-MISC [MEM] Stall
Recovery).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AC
PRO-ABN-NAV P 48/48
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
OVERSPEED
FLIGHT CREW
OPERATING MANUAL
OVERSPEED
Applicable to: ALL
Ident.: PRO-ABN-OVERSPEED-AX-00018108.0001001 / 20 APR 17
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The aircraft speed/mach is greater than VMO + 4 kt/MMO + 0.006, or
‐ The aircraft speed is greater than VLE + 4 kt, with L/G not uplocked or L/G doors not closed,
or
‐ The aircraft speed is greater than VFE + 4 kt, with slats and/or flaps extended.
Flight Phase Inhibition:
Ident.: PRO-ABN-OVERSPEED-AX-00016848.0001001 / 21 MAR 16
VMO/MMO................................................................................................................................ 350/.82
(235/0.60 in case of dispatch with landing gear down).
L1 VLE........................................................................................................................................... 280/.67
VFE..................................................................................................................................SEE BELOW
L2
CONF
FULL
3
2
1+F
1
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
VFE
177
185
200
215
230
A
PRO-ABN-OVERSPEED P 1/2
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
OVERSPEED
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-OVERSPEED P 2/2
19 JUN 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
RECORDER
FLIGHT CREW
OPERATING MANUAL
RECORDER DFDR FAULT
Applicable to: ALL
Ident.: PRO-ABN-RECORDER-A-00017312.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the DFDR is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-RECORDER-A-00010046.0001001 / 10 AUG 10
Crew awareness.
Ident.: PRO-ABN-RECORDER-A-00010047.0001001 / 10 AUG 10
STATUS
INOP SYS
DFDR
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-RECORDER P 1/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
RECORDER
FLIGHT CREW
OPERATING MANUAL
RECORDER SYS FAULT
Applicable to: ALL
Ident.: PRO-ABN-RECORDER-B-00017313.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the FDIU is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-RECORDER-B-00010048.0002001 / 10 AUG 10
Crew awareness.
Ident.: PRO-ABN-RECORDER-B-00010049.0002001 / 10 AUG 10
STATUS
INOP SYS
RECORDER SYS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PRO-ABN-RECORDER P 2/2
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] SMOKE / FUMES / AVNCS SMOKE
Applicable to: ALL
Ident.: PRO-ABN-SMOKE-D-00012212.0004001 / 17 MAR 17
This procedure includes all the steps of the AVIONICS SMOKE ECAM procedure.
Apply this procedure when:
‐ The flight (cabin) crew suspect that smoke is coming from any of the following:
• The avionics
• The air conditioning
• The cabin equipment
‐ Requested by the AVIONICS SMOKE ECAM procedure.
‐ There is a smell of smoke / fumes in the cockpit :
• If the smell is similar to that of orange peels, suspect a toxic leak of rain repellent fluid.
• If the smell is similar to that of pine needles, suspect a non-toxic leak.
If any other ECAM SMOKE alert triggers (CARGO, ...), the crew must first apply the ECAM
procedure, then consider applying this procedure.
Note that these ECAM alerts may be caused by another source, that should usually first be
detected by the flight crew/cabin crew/avionics smoke detectors.
The following explains the layout of this procedure:
‐ The procedure lines above the text boxes indicate the actions that the flight crew must
immediately perform, if smoke is detected (with or without ECAM activation and regardless of
the smoke source). These immediate actions correspond to the most common steps to be taken
in smoke cases. In all cases, the flight crew must also be prepared to immediately perform a
diversion. However, this diversion may be avoided if the smoke source is obvious, accessible
and extinguishable or confirmed isolated (after completion of the immediate actions).
‐ The text boxes indicate the actions that the flight crew must consider, if at any time during the
remainder of the procedure but always after the initial steps:
• Smoke / fumes become the greatest threat and removal of smoke / fumes is required, and/or
• The situation becomes critical and can no longer be controlled.
‐ The procedure lines below the text boxes indicate the actions that the flight crew must perform,
as soon as they suspect a source of smoke. The actions will depend on whether the smoke is
coming from the avionics, and/or air conditioning, and/or cabin equipment.
LAND ASAP
IF PERCEPTIBLE SMOKE APPLY IMMEDIATELY:
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A→
Continued on the following page
PRO-ABN-SMOKE P 1/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] SMOKE / FUMES / AVNCS SMOKE (Cont'd)
If smoke is confirmed, the following procedure must be applied.
OXY MASK / GOGGLE (if required).....................................................................USE/100%/EMERG
Ensure crew communication is established. Avoid continuous use of the interphone to minimize
interference from the oxygen mask breathing noise.
Turn the emergency knob to remove condensation or smoke from the mask.
VENTILATION BLOWER........................................................................................................... OVRD
VENTILATION EXTRACT.......................................................................................................... OVRD
Avionics ventilation air is extracted overboard.
CAB FANS.....................................................................................................................................OFF
To prevent smoke from entering the cockpit and cabin.
GALY & CAB.................................................................................................................................OFF
SIGNS..............................................................................................................................................ON
CKPT / CABIN COM........................................................................................................ ESTABLISH
Communication must be established with the cabin crew in order to follow up on the smoke origin
and dissipation.
If smoke source immediately obvious, accessible, and extinguishable:
FAULTY EQPT............................................................................................................... ISOLATE
If smoke source not immediately isolated:
DIVERSION..................................................................................................................... INITIATE
DESCENT TO FL 100 / MEA -MORA ........................................................................... INITIATE
At ANY TIME of the procedure, if SMOKE / FUMES becomes the GREATEST THREAT:
REMOVAL OF SMOKE / FUMES............................................................................. CONSIDER
Refer to PRO-ABN-SMOKE [QRH] REMOVAL OF SMOKE / FUMES
ELEC EMER CONFIG...............................................................................................CONSIDER
Refer to PRO-ABN-SMOKE [QRH] SMOKE / FUMES / AVNCS SMOKE - ELEC EMER
CONFIG
At ANY TIME of the procedure, if situation becomes UNMANAGEABLE:
IMMEDIATE LANDING.............................................................................................. CONSIDER
L2
Depending on the situation, the Captain can consider an overweight landing, a tailwind
landing, a ditching, a forced landing, etc.
Continued on the following page
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←A→
PRO-ABN-SMOKE P 2/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] SMOKE / FUMES / AVNCS SMOKE (Cont'd)
L1
Guidelines to determine smoke source:
‐ If smoke initially comes out of the ventilation outlets, the crew may suspect AIR COND SMOKE.
In addition, very shortly thereafter, several SMOKE warnings (cargo, lavatory, avionics) will be
triggered. The displayed ECAM procedures must be applied.
‐ After an ENG or APU failure, smoke may come from the faulty item via the bleed system and
be perceived in the cockpit and/or cabin. In such a case, it will be recirculated throughout the
aircraft, until it completely disappears from the air conditioning system.
‐ If only the AVIONICS SMOKE warning is triggered, the crew may suspect avionics smoke.
‐ If the smoke is detected while an equipment is declared faulty, the crew may suspect that smoke
is coming from this equipment.
‐ Avionics or forward galley smoke may be smelt, or may enter in the cockpit before ECAM
warning activation.
Continued on the following page
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←A→
PRO-ABN-SMOKE P 3/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] SMOKE / FUMES / AVNCS SMOKE (Cont'd)
Ident.: PRO-ABN-SMOKE-D-00012214.0005001 / 17 MAR 17
If Air COND smoke suspected:
APU BLEED............................................................................................................................OFF
VENTILATION BLOWER and EXTRACT............................................................................AUTO
Note:
When both VENTILATION BLOWER and VENTILATION EXTRACT are in the OVRD
position, a single pack may not be able to maintain the cabin pressure.
CARGO FWD ISOL VALVE................................................................................................... OFF
To prevent a cargo smoke warning from being triggered due to cabin smoke.
PACK 1................................................................................................................................... OFF
If smoke continues:
PACK 1.............................................................................................................................. ON
PACK 2.............................................................................................................................OFF
If smoke persists:
PACK 2........................................................................................................................ON
Restore normal configuration if PACK 2 is not suspected to cause smoke
VENTILATION BLOWER........................................................................................OVRD
VENTILATION EXTRACT...................................................................................... OVRD
REMOVAL OF SMOKE / FUMES.............................................................................. CONSIDER
Refer to PRO-ABN-SMOKE [QRH] REMOVAL OF SMOKE / FUMES
If CABIN EQPT smoke suspected:
If smoke continues:
EMER EXIT LIGHT............................................................................................................ ON
COMMERCIAL..................................................................................................................OFF
SMOKE DISSIPATION............................................................................................... CHECK
FAULTY EQPT...................................................................................... SEARCH / ISOLATE
Once the cabin has been secured, try to find the smoke source and isolate it.
Cabin lights, reading lights, passenger systems, galleys have dedicated control C/B in the
cabin or cockpit.
If smoke persists or if faulty equipment confirmed isolated:
COMMERCIAL....................................................................................................... NORM
REMOVAL OF SMOKE / FUMES........................................................................ CONSIDER
Refer to PRO-ABN-SMOKE [QRH] REMOVAL OF SMOKE / FUMES
Continued on the following page
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PRO-ABN-SMOKE P 4/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] SMOKE / FUMES / AVNCS SMOKE (Cont'd)
Ident.: PRO-ABN-SMOKE-D-00012215.0001001 / 17 MAR 17
If smoke source cannot be determined and persists or AVNCS / ELECTRICAL smoke
suspected:
ELEC EMER CONFIG................................................................................................ CONSIDER
Refer to the end of the procedure to set ELEC EMER CONFIG.
If smoke disappears within 5 min:
NORMAL VENTILATION.............................................................................................. RESTORE
Continued on the following page
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←A→
PRO-ABN-SMOKE P 5/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] SMOKE / FUMES / AVNCS SMOKE (Cont'd)
Ident.: PRO-ABN-SMOKE-D-00012565.0019001 / 17 MAR 17
TO SET ELEC EMER CONFIG
EMER ELEC GEN 1 LINE........................................................................................................ OFF
GEN 1 LINE contactor opens. GEN 1 remains running and supplies one fuel pump in each wing
tank. AC BUS 1 is supplied by GEN 2 through the bus tie contactor.
EMER ELEC PWR.............................................................................................................MAN ON
RAT is extended and the EMER GEN is connected to the aircraft network. Check emergency
generator parameters on the ELEC SD page (displayed automatically).
When EMER GEN AVAIL:
APU GEN............................................................................................................................OFF
GEN 2................................................................................................................................. OFF
ELEC EMER CONFIG
Two different procedures can be displayed on the ECAM , depending on whether the
AVIONICS SMOKE ECAM caution is triggered or not before the flight crew sets the electrical
emergency configuration.
If AVIONICS SMOKE not triggered:
APPLY ELEC EMER CONFIG PROCEDURE, BUT DO NOT RESET GEN, EVEN IF
REQUESTED BY ECAM
At 3 min or 2 000 ft AAL before landing:
Restore all generators only 3 min before landing or at 2 000 ft AAL to recover normal
braking, while minimizing possible reactivation of a smoke source.
GEN 2...................................................................................................................... ON
EMER ELEC GEN 1 LINE...................................................................................... ON
When aircraft stopped:
ALL GENs.............................................................................................................. OFF
If AVIONICS SMOKE triggered:
The ECAM displays a specific ELEC EMER CONFIG procedure. The flight crew must
apply the following ECAM procedure.
MIN RAT SPEED.....................................................................................................140 KT
Note:
The electrical configuration is the same as for loss of both generators (except
that one fuel pump in each wing tank remains supplied).
Continued on the following page
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←A→
PRO-ABN-SMOKE P 6/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] SMOKE / FUMES / AVNCS SMOKE (Cont'd)
VHF 1 / HF 1 / ATC 1................................................................................................. USE
Only VHF 1, HF 1 and ATC 1 are supplied in this configuration. Notify the ATC of the
nature of the emergency, and state intentions. If there is no contact with the ATC, switch
to code A7700, or transmit a distress message on one of the emergency frequencies.
FAC 1......................................................................................................... OFF THEN ON
Rudder trim is recovered, despite the fact that no indication is available.
At 3 min or 2 000 ft AAL before landing:
Restore all generators only 3 min before landing or at 2 000 ft AAL to recover normal
braking, while minimizing possible reactivation of a smoke source.
GEN 2...................................................................................................................... ON
EMER ELEC GEN 1 LINE...................................................................................... ON
F/CTL ALTN LAW (PROT LOST)
Flight control normal laws and associated protections are lost. Only the load factor
limitation, and the high and low speed stability remain (ALTN law with reduced
protection).
MAX SPEED............................................................................................................320 KT
Continued on the following page
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PRO-ABN-SMOKE P 7/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] SMOKE / FUMES / AVNCS SMOKE (Cont'd)
Ident.: PRO-ABN-SMOKE-D-00012217.0057001 / 31 AUG 17
ECAM lower display is not available. STATUS SD page is displayed on the upper ECAM display, as
long as the STATUS pb is pressed.
L12
STATUS
MIN RAT SPEED......................................................... 140 KT
MAX SPEED................................................................ 320 KT
MAX BRK PR............................................................1000 PSI
FOR LDG..........................................................USE FLAPS 3
GPWS LDG FLAP 3...........................................................ON
APPR SPD........................................................ VREF +10 KT
LDG DIST PROC......................................................... APPLY
ENG 1+2 APPR IDLE ONLY
ENG 1+2 N1 DEGRADED MODE
(IAE-powered aircraft)
ALTN LAW: PROT LOST
WHEN L/G DN: DIRECT LAW
CTR TK FUEL UNUSABLE
FUEL CONSUMPT INCRSD
This message is triggered when the failure (or combination of
failures) affects the nominal aerodynamic characteristics of
the aircraft.
FMS PRED UNRELIABLE
Disregard FMS fuel predictions and refer to QRH/OPSOperational Data - Fuel Penalty Factors Tables in order to
find the applicable Fuel Penalty Factor.
SLATS/FLAPS SLOW
After recovery of normal electrical supply, the
following STATUS will be displayed:
MAX SPEED..........................................................320 KT
APPR SPD..................................................VREF +10 KT
LDG DIST PROC...................................................APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
INOP SYS
Refer to PRO-ABN-ELEC-[QRH]
ELEC EMER CONFIG SYS
REMAINING.
Continued on the following page
PRO-ABN-SMOKE P 8/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] SMOKE / FUMES / AVNCS SMOKE (Cont'd)
APPR PROC
3 MN/2000 FT BEFORE LDG:
GEN 2.......................................................................... ON
EMER ELEC GEN 1 LINE........................................... ON
WHEN A/C IS STOPPED:
ALL GEN.................................................................... OFF
ALTN LAW: PROT LOST
(1)
See
WHEN L/G DN: DIRECT LAW
(2)
See
(1)
(2)
Flight controls remain in alternate law, due to the loss of IR 2 and 3.
At landing gear extension, control reverts to direct law in pitch, as well as in roll (Refer to
PRO-ABN-F_CTL F/CTL DIRECT LAW).
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←A
PRO-ABN-SMOKE P 9/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] REMOVAL OF SMOKE / FUMES
Ident.: PRO-ABN-SMOKE-00012218.0003001 / 17 MAR 17
Applicable to: ALL
Apply the REMOVAL OF SMOKE / FUMES QRH procedure, if smoke / fumes become the greatest
threat when applying the SMOKE / FUMES / AVNCS SMOKE QRH procedure.
EMER EXIT LIGHT......................................................................................................................... ON
If fuel vapors:
CAB FANS................................................................................................................................ON
The recirculating air ventilates the air mixer bay and other fuselage area. This prevents fuel
vapors from accumulating and the risk of explosion. Passenger health is not affected.
PACK 1................................................................................................................................... OFF
PACK 2................................................................................................................................... OFF
If no fuel vapors:
CAB FANS.............................................................................................................................. OFF
To prevent smoke from entering the cockpit and cabin.
PACK FLOW.............................................................................................................................. HI
To provide maximum airflow from the packs.
Do not shut down the air conditioning packs, and do not reduce ventilation in an attempt to
smother the fire.
Do not deploy oxygen masks, if fire is suspected in the cabin.
LDG ELEV..................................................................................................... 10 000 ft / MEA-MORA
DESCENT TO FL 100 / MEA -MORA ................................................................................. INITIATE
The most effective means of smoke removal is use of ram air. Therefore, descent is initiated to
FL 100 or the MEA -MORA , while the cabin altitude is increased to 10 000 ft or the MEA -MORA.
The increase in cabin altitude also reduces, at least temporarily, the smoke concentration. Cabin
depressurization starts, when descent is initiated.
ATC..........................................................................................................................................NOTIFY
SMOKE / FUMES / AVNCS SMOKE PROC.....................................................................CONTINUE
Refer to PRO-ABN-SMOKE [QRH] SMOKE / FUMES / AVNCS SMOKE - GENERAL
At FL 100 or MEA-MORA:
If in ELEC EMER CONFIG:
APU MASTER sw .............................................................................................................ON
Continued on the following page
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PRO-ABN-SMOKE P 10/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] REMOVAL OF SMOKE / FUMES (Cont'd)
In electrical emergency configuration, when the APU MASTER sw is ON, the battery
contactors will automatically close for a maximum of 3 min. This will enable the flight crew
to manually control the outflow valve that is powered by the DC BAT BUS.
PACK 1................................................................................................................................... OFF
PACK 2................................................................................................................................... OFF
MODE SEL.............................................................................................................................MAN
MAN V/S CTL................................................................................................................. FULL UP
RAM AIR...................................................................................................................................ON
At FL 100, or MEA -MORA, it is possible to open the RAM AIR valve when ΔP is 1 PSI or
below. Opening the RAM AIR enables flying with both packs OFF.
APU MASTER sw ..................................................................................................................OFF
If smoke persists:
If there is smoke in the cockpit, open the cockpit (CKPT) window to evacuate the smoke.
MAX SPEED: 200 kt
COCKPIT DOOR...........................................................................................................OPEN
HEADSETS........................................................................................................................ ON
PM SLIDING WINDOW.................................................................................................OPEN
When window open:
NON-AFFECTED PACK(s)..........................................................................................ON
VISUAL WARNINGS (noisy CKPT).................................................................MONITOR
Due to the increased noise level, pay particular attention to visual warnings.
SMOKE / FUMES / AVNCS SMOKE PROC................................................. CONTINUE
Refer to PRO-ABN-SMOKE [QRH] SMOKE / FUMES / AVNCS SMOKE - GENERAL
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PRO-ABN-SMOKE P 11/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
[QRH] SMOKE / FIRE FROM LITHIUM BATTERY
Ident.: PRO-ABN-SMOKE-00016024.0001001 / 17 MAR 17
Applicable to: ALL
If necessary, transfer control to the flight crew member seated on the opposite side of the fire.
CKPT / CAB COM............................................................................................................ ESTABLISH
STORAGE AFTER Li BAT FIRE cabin procedure..........................................REQUEST INITIATION
If flames:
CREW OXY MASK (PF)........................................................................................................ USE
SMOKE HOOD (PM)..............................................................................................................USE
HALON EXTINGUISHER........................................................................................................USE
If no flames or when flames extinguished:
If not possible to remove device from the cockpit:
WATER or NON-ALCOHOLIC LIQUID....................................................POUR ON DEVICE
DEVICE...................................................................................................................MONITOR
If possible to remove device from the cockpit:
DEVICE..............................................................................................TRANSFER TO CABIN
At ANY TIME of the procedure, if SMOKE becomes the GREATEST THREAT:
REMOVAL OF SMOKE / FUMES procedure............................................................CONSIDER
Refer to PRO-ABN-SMOKE [QRH] REMOVAL OF SMOKE / FUMES
At ANY TIME of the procedure, if situation becomes UNMANAGEABLE:
IMMEDIATE LANDING.............................................................................................. CONSIDER
L2
Depending on the situation, the Captain can consider an overweight landing, a tailwind
landing, a ditching, a forced landing, etc.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-SMOKE P 12/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
SMOKE AFT CARGO SMOKE
Applicable to: ALL
Ident.: PRO-ABN-SMOKE-O-00018698.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when smoke in the AFT cargo compartment is detected.
Flight Phase Inhibition:
Continued on the following page
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PRO-ABN-SMOKE P 13/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
SMOKE AFT CARGO SMOKE (Cont'd)
Ident.: PRO-ABN-SMOKE-O-00018589.0007001 / 21 MAR 16
LAND ASAP
L2
L1
L2
AFT ISOL VALVE (IF NOT AUTOMATICALLY CLOSED)....................................................OFF
CAB FANS.....................................................................................................................................OFF
IF AFT CRG CLOSED (displayed on ground only):
Order the ground crew not to open the door of the affected cargo compartment, unless the
passengers have disembarked and fire services are present. Also ensure that the AFT cargo
door is closed before discharging the extinguishing agent.
AGENT................................................................................................................................ DISCH
Note:
Expect the SMOKE warning to remain after agent discharge, even if the smoke
source is extinguished. Gases from the smoke source are not evacuated, and smoke
detectors are also sensitive to the extinguishing agent.
L1
ON GROUND BEFORE OPEN CRG DOOR:
PAX........................................................................................................................... DISEMBARK
L2
Note:
For aircraft equipped with AFT Cargo Ventilation , if the warning has been displayed
temporarily, and agent has not been discharged, normal cargo ventilation may be
recovered when ventilation is required for livestock transportation:
C/B of CARGO VENT controller (S20 on 122VU , or C7 on 49VU, as installed for AFT
CARGO) ...... PULL then PUSH
Ident.: PRO-ABN-SMOKE-O-00018590.0002001 / 21 MAR 16
STATUS
BEFORE OPEN CRG DOORS (displayed on ground
only):
PAX...............................................................DISEMBARK
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
INOP SYS
AFT CRG VENT
AFT CRG HEAT
PRO-ABN-SMOKE P 14/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
SMOKE AFT CRG DET FAULT
Applicable to: ALL
Ident.: PRO-ABN-SMOKE-P-00018699.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the AFT smoke detection is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-SMOKE-P-00018592.0001001 / 21 MAR 16
IF NO LIVE STOCK:
AFT ISOL VALVE ........................................................................................................... OFF
Ident.: PRO-ABN-SMOKE-P-00018593.0001001 / 21 MAR 16
STATUS
INOP SYS
AFT CRG DET
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E
PRO-ABN-SMOKE P 15/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
SMOKE FWD CARGO SMOKE
Applicable to: ALL
Ident.: PRO-ABN-SMOKE-E-00017408.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when smoke in the FWD cargo compartment is detected.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PRO-ABN-SMOKE P 16/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
SMOKE FWD CARGO SMOKE (Cont'd)
Ident.: PRO-ABN-SMOKE-E-00018287.0005001 / 21 MAR 16
LAND ASAP
L2
L1
L2
FWD ISOL VALVE (IF NOT AUTOMATICALLY CLOSED).................................................. OFF
CAB FANS.....................................................................................................................................OFF
IF FWD CRG CLOSED (displayed on ground only):
Order the ground crew not to open the door of the affected cargo compartment, unless the
passengers have disembarked and fire services are present. Also ensure that the FWD Cargo
Door is closed before discharging the extinguishing agent.
AGENT................................................................................................................................ DISCH
Note:
Expect the SMOKE warning to remain after agent discharge, even if the smoke
source is extinguished. Gases from the smoke source are not evacuated, and smoke
detectors are also sensitive to the extinguishing agent.
L1
ON GROUND BEFORE OPEN CRG DOOR:
PAX........................................................................................................................... DISEMBARK
L2
Note:
For aircraft equipped with FWD Cargo Ventilation , if the warning has been displayed
temporarily, and agent has not been discharged, normal cargo ventilation may be
recovered when ventilation is required for livestock transportation:
C/B of CARGO VENT controller (T20 on 122VU , or C8 on 49VU , as installed for FWD
CARGO) ...... PULL then PUSH
Ident.: PRO-ABN-SMOKE-E-00018588.0002001 / 21 MAR 16
STATUS
BEFORE OPEN CRG DOOR (displayed on ground
only):
PAX...............................................................DISEMBARK
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
INOP SYS
FWD CRG VENT
FWD CRG HEAT
PRO-ABN-SMOKE P 17/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
SMOKE FWD(AFT) CRG BTL 1(2) FAULT
Applicable to: ALL
Ident.: PRO-ABN-SMOKE-L-00017414.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ FWD or AFT bottle 1 (2) squib is failed, or
‐ FWD or AFT bottle 1 (2) is at low pressure.
Flight Phase Inhibition:
Ident.: PRO-ABN-SMOKE-L-00018325.0001001 / 21 MAR 16
L2
If bottle 1 is lost, fire extinguishing capability is lost in the FWD(AFT) cargo compartment.
If bottle 2 is lost, agent concentration will not be ensured after fire extinguishing.
L1
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
PRO-ABN-SMOKE P 18/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
SMOKE FWD CRG DET FAULT
Applicable to: ALL
Ident.: PRO-ABN-SMOKE-F-00017689.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the FWD smoke detection is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-SMOKE-F-00018336.0001001 / 21 MAR 16
IF NO LIVE STOCK:
FWD ISOL VALVE ..........................................................................................................OFF
Ident.: PRO-ABN-SMOKE-F-00018337.0001001 / 21 MAR 16
STATUS
INOP SYS
FWD CRG DET
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
PRO-ABN-SMOKE P 19/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
SMOKE DET FAULT
Applicable to: ALL
Ident.: PRO-ABN-SMOKE-G-00017400.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when both SDCU or CIDS-SDF are failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-SMOKE-G-00018423.0002001 / 21 MAR 16
IF NO LIVE STOCK:
FWD ISOL VALVE ..........................................................................................................OFF
AFT ISOL VALVE ........................................................................................................... OFF
PAX SYS ............................................................................................................................... OFF
Ident.: PRO-ABN-SMOKE-G-00012226.0011001 / 01 APR 11
STATUS
INOP SYS
SMOKE DET
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I
PRO-ABN-SMOKE P 20/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
SMOKE LAVATORY DET FAULT
Applicable to: ALL
Ident.: PRO-ABN-SMOKE-H-00017407.0002001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the lavatory smoke detection is failed.
Flight Phase Inhibition:
Ident.: PRO-ABN-SMOKE-H-00018724.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-SMOKE-H-00012228.0001001 / 18 AUG 10
STATUS
INOP SYS
LAV DET
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J
PRO-ABN-SMOKE P 21/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SMOKE
FLIGHT CREW
OPERATING MANUAL
SMOKE LAVATORY SMOKE
Applicable to: ALL
Ident.: PRO-ABN-SMOKE-N-00017406.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when smoke in one of the lavatory is detected.
Flight Phase Inhibition:
Ident.: PRO-ABN-SMOKE-N-00018427.0002001 / 21 MAR 17
L2
Communication must be established with the cabin crew in order to follow up on the smoke origin
and dissipation.
Consider applying the SMOKE/FUMES/AVNCS SMOKE QRH procedure.
L1
CKPT/CAB COM...............................................................................................................ESTABLISH
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K
PRO-ABN-SMOKE P 22/22
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SURV
FLIGHT CREW
OPERATING MANUAL
[MEM] EGPWS CAUTIONS
Ident.: PRO-ABN-SURV-00018751.0009001 / 17 MAR 17
Applicable to: ALL
"TERRAIN TERRAIN" - "TOO LOW TERRAIN" - "CAUTION TERRAIN" - "CAUTION
OBSTACLE"
During night or IMC:
Simultaneously:
AP....................................................................................................................................OFF
PITCH......................................................................................................................PULL UP
L2
Pull to full backstick and maintain in that position.
L1
THRUST LEVERS....................................................................................................... TOGA
SPEED BRAKES lever.......................................................................CHECK RETRACTED
BANK......................................................................................... WINGS LEVEL or ADJUST
L2
Aircraft achieve the best climb performance when the wings are as level as possible.
L1
Note:
For some airports, the operator may define a specific procedure.
During daylight and VMC, with terrain and obstacles clearly in sight:
FLIGHT PATH.......................................................................................................... ADJUST
L2
L1
Adjust pitch, bank and thrust to silence the alert.
Note:
For some airports, the operator may define a specific procedure.
"SINK RATE"
Above 1 000 ft AAL in IMC or above 500 ft AAL in VMC:
FLIGHT PATH.......................................................................................................... ADJUST
L2
L1
Adjust pitch and thrust to silence the alert.
Below 1 000 ft AAL in IMC or below 500 ft AAL in VMC:
GO-AROUND...................................................................................................... CONSIDER
"DON'T SINK"
FLIGHT PATH................................................................................................................ ADJUST
L2
Adjust pitch and thrust to silence the alert.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-ABN-SURV P 1/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SURV
FLIGHT CREW
OPERATING MANUAL
[MEM] EGPWS CAUTIONS (Cont'd)
L1
"TOO LOW GEAR" - "TOO LOW FLAPS"
GO-AROUND..............................................................................................................PERFORM
"GLIDESLOPE"
Above 1 000 ft AAL in IMC or above 500 ft AAL in VMC:
FLIGHT PATH.......................................................................................................... ADJUST
L2
Adjust pitch and thrust to reduce the vertical deviation from the glideslope.
L1
When conditions require a deliberate approach below glideslope:
G/S MODE................................................................................................................OFF
Below 1 000 ft AAL in IMC or below 500 ft AAL in VMC:
GO-AROUND...................................................................................................... CONSIDER
[MEM] EGPWS WARNINGS
Ident.: PRO-ABN-SURV-00016878.0020001 / 17 MAR 17
Applicable to: ALL
"PULL UP" - "TERRAIN TERRAIN PULL UP" - "OBSTACLE OBSTACLE PULL UP"
Simultaneously:
AP.......................................................................................................................................... OFF
PITCH............................................................................................................................ PULL UP
L2
Pull to full backstick and maintain in that position.
L1
THRUST LEVERS..............................................................................................................TOGA
SPEED BRAKES lever............................................................................. CHECK RETRACTED
BANK................................................................................................WINGS LEVEL or ADJUST
L2
Aircraft achieve the best climb performance when the wings are as level as possible.
If the "TERRAIN TERRAIN PULL UP" or "OBSTACLE OBSTACLE PULL UP" aural alert
triggers, a turning maneuver can be initiated if the flight crew concludes that turning is the
safest action. The PULL UP maneuver must be performed before the turn towards the safe
direction, as climbing increases the terrain clearance.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B
PRO-ABN-SURV P 2/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SURV
FLIGHT CREW
OPERATING MANUAL
[MEM] TCAS WARNINGS
Ident.: PRO-ABN-SURV-00012455.0022001 / 17 MAR 17
Applicable to: ALL
Traffic advisory: “TRAFFIC” messages:
Do not perform a maneuver based on a TA alone.
Resolution advisory: All “CLIMB” and “DESCEND” or “MAINTAIN VERTICAL SPEED
MAINTAIN” or “LEVEL OFF, LEVEL OFF” or “MONITOR VERTICAL SPEED” type
messages:
AP (if engaged).......................................................................................................................OFF
BOTH FDs.............................................................................................................................. OFF
Respond promptly and smoothly to a RA by adjusting or maintaining the pitch, as required, to
reach the green area and/or avoid the red area of the vertical speed scale.
Note:
Avoid excessive maneuvers while aiming to keep the vertical speed just outside the
red area of the VSI , and within the green area. If necessary, use the full speed range
between Vαmax and VMAX.
Respect stall, GPWS, or windshear warning.
Notify ATC.
GO AROUND procedure must be performed when a RA “CLIMB” or “INCREASE
CLIMB” is triggered on final approach:
Note:
Resolution Advisories (RA) are inhibited below 900 ft.
When “CLEAR OF CONFLICT” is announced:
Resume normal navigation in accordance with ATC clearance.
AP/FD can be reengaged as desired.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-SURV P 3/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SURV
FLIGHT CREW
OPERATING MANUAL
[MEM] WINDSHEAR
Ident.: PRO-ABN-SURV-00012271.0002001 / 17 MAR 17
Applicable to: ALL
A red flag “WINDSHEAR” is displayed on each PFD associated with an aural synthetic voice
“WINDSHEAR” repeated three times.
If windshear is detected either by the system or by pilot observation, apply the following recovery
technique:
At Takeoff:
If before V1:
The takeoff should be rejected only if significant airspeed variations occur below indicated
V1 and the pilot decides that there is sufficient runway remaining to stop the airplane.
If after V1:
THR LEVERS...............................................................................................................TOGA
REACHING VR........................................................................................................ROTATE
SRS ORDERS........................................................................................................ FOLLOW
If necessary the flight crew may pull the sidestick fully back.
Note:
If the FD bars are not displayed, move toward an initial pitch attitude of 17.5 °.
Then, if necessary, to prevent a loss in altitude, increase the pitch attitude.
Airborne, initial climb or landing:
THR LEVERS AT TOGA.............................................................................. SET OR CONFIRM
AP (if engaged)............................................................................................................ KEEP ON
SRS ORDERS...............................................................................................................FOLLOW
If necessary the flight crew may pull the sidestick fully back.
Note:
1. Autopilot disengages if the angle of attack value goes above α prot.
2. If the FD bars are not displayed, move toward an initial pitch attitude of 17.5 °.
Then, if necessary, to prevent a loss in altitude, increase the pitch attitude.
DO NOT CHANGE CONFIGURATION (SLATS/FLAPS, GEAR) UNTIL OUT OF
WINDSHEAR.
CLOSELY MONITOR FLIGHT PATH AND SPEED.
RECOVER SMOOTHLY TO NORMAL CLIMB OUT OF WINDSHEAR.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PRO-ABN-SURV P 4/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SURV
FLIGHT CREW
OPERATING MANUAL
[MEM] WINDSHEAR AHEAD
Ident.: PRO-ABN-SURV-00012272.0001001 / 17 MAR 17
Applicable to: ALL
The “W/S AHEAD” message is displayed on each PFD. The color of the message depends on the
severity and location of the windshear
Note:
When a predictive windshear alert (“WINDSHEAR AHEAD” or "GO AROUND
WINDSHEAR AHEAD") is triggered, if the flight crew makes a positive verification that no
hazard exists, then the alert may be disregarded, as long as:
‐ There are no other signs of possible windshear conditions, and
‐ The reactive windshear system is operational.
Known cases of spurious predictive windshear alerts have been reported at some airports,
during either takeoff or landing, due to the specific obstacle environment.
However, always rely on any reactive windshear (“WINDSHEAR”).
W/S AHEAD RED
Takeoff
Associated with an aural synthetic voice “WINDSHEAR AHEAD, WINDSHEAR AHEAD”.
Before takeoff:
Delay takeoff, or select the most favorable runway.
During the takeoff run:
Reject takeoff.
Note:
Predictive windshear alerts are inhibited above 100 kt until 50 ft.
When airborne:
THR LEVERS...........................................................................................................TOGA
As usual, the slat/flap configuration can be changed, provided the windshear is not
entered.
AP (if engaged)..................................................................................................KEEP ON
SRS ORDERS.................................................................................................... FOLLOW
If necessary the flight crew may pull the sidestick fully back.
Note:
1. Autopilot disengages if the angle of attack value goes above α prot.
2. If the FD bars are not displayed, move toward an initial pitch attitude of
17.5 °. Then, if necessary, to prevent a loss in altitude, increase the pitch
attitude.
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
PRO-ABN-SURV P 5/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
SURV
FLIGHT CREW
OPERATING MANUAL
[MEM] WINDSHEAR AHEAD (Cont'd)
Landing:
Associated with an aural synthetic voice “GO AROUND, WINDSHEAR AHEAD”.
GO-AROUND.......................................................................................................... PERFORM
AP (if engaged)........................................................................................................ KEEP ON
If necessary the flight crew may pull the sidestick fully back.
Note:
1. Autopilot disengages if the angle of attack value goes above α prot.
2. If the FD bars are not displayed, move toward an initial pitch attitude of 17.5 °.
Then, if necessary, to prevent a loss in altitude, increase the pitch attitude.
W/S AHEAD AMBER
Apply precautionary measures, as indicated in FCTM Windshear Operational Recommendations
Refer to FCTM/PR-NP-SP-10-10-3 Operational Recommendations.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-ABN-SURV P 6/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
VENT
FLIGHT CREW
OPERATING MANUAL
VENT AVNCS SYS FAULT
Applicable to: ALL
Ident.: PRO-ABN-VENT-AA-00017332.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The power up test is not satisfactory, or
‐ The AEVC is not supplied, or
‐ The valve position disagrees with the commanded position.
Flight Phase Inhibition:
Ident.: PRO-ABN-VENT-AA-00018047.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-VENT-AA-00010775.0001001 / 05 AUG 10
STATUS
INOP SYS
AVNCS VENT
VENT BLOWER
(1)
VENT EXTRACT
(1)
(1)
(If AEVC not supplied)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-ABN-VENT P 1/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
VENT
FLIGHT CREW
OPERATING MANUAL
VENT BLOWER FAULT
Applicable to: ALL
Ident.: PRO-ABN-VENT-X-00017329.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
The alert triggers when the blowing pressure is low or there is a duct overheat.
Flight Phase Inhibition:
Ident.: PRO-ABN-VENT-X-00010768.0005001 / 12 APR 16
If NO DC ESS BUS FAULT:
BLOWER..............................................................................................................................OVRD
L2
The ventilation system is in closed circuit configuration and air from air conditioning is added to
the ventilation air.
L1
If DC ESS BUS FAULT:
LAND ASAP
Ident.: PRO-ABN-VENT-X-00010769.0005001 / 27 MAY 13
STATUS
INOP SYS
VENT BLOWER
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PRO-ABN-VENT P 2/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
VENT
FLIGHT CREW
OPERATING MANUAL
VENT EXTRACT FAULT
Applicable to: ALL
Ident.: PRO-ABN-VENT-Y-00017330.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the extract pressure is low.
Flight Phase Inhibition:
Ident.: PRO-ABN-VENT-Y-00010770.0001001 / 05 AUG 10
L2
EXTRACT................................................................................................................................... OVRD
The ventilation system is in closed circuit configuration and air from air conditioning is added to the
ventilation air.
Ident.: PRO-ABN-VENT-Y-00010771.0001001 / 05 AUG 10
STATUS
INOP SYS
VENT EXTRACT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-ABN-VENT P 3/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
VENT
FLIGHT CREW
OPERATING MANUAL
VENT SKIN VALVE FAULT
Applicable to: ALL
Ident.: PRO-ABN-VENT-Z-00017331.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when:
‐ The extract valve is fully open in phase 3, or
‐ The extract valve is fully open in flight, or
‐ The inlet valve is not fully closed in flight.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PRO-ABN-VENT P 4/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
VENT
FLIGHT CREW
OPERATING MANUAL
VENT SKIN VALVE FAULT (Cont'd)
Ident.: PRO-ABN-VENT-Z-00018941.0001001 / 21 MAR 16
If INLET valve not fully closed in flight:
Crew awareness.
L2
No action is required, since there is a non return valve in the air inlet.
L1
If EXTRACT valve affected:
BLOWER..............................................................................................................................OVRD
EXTRACT............................................................................................................................ OVRD
L2
These actions send additional closure signals to the inlet and extract valves.
The weather radar image on both NDs may be lost, in case of insufficient ventilation.
L1
L2
IF UNSUCCESSFUL:
MAX FL.....................................................................................................................100/MEA
CAB PR MODE SEL....................................................................................................... MAN
MAN V/S CTL...........................................................................................................FULL UP
The aircraft is manually depressurized.
It may take 10 s in manual mode before the crew notices a change of the outflow valve
position.
Ident.: PRO-ABN-VENT-Z-00018942.0002001 / 21 MAR 16
STATUS
INOP SYS
MAX FL: 100/MEA
MAN CAB PR CTL
TGT V/S: CLIMB 500 FT/MIN
TGT V/S: DESC 300 FT/MIN
A/C FL
390
350
300
250
< 200
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
AVNCS VALVE
CAB ALT TGT
8 000
7 000
5 500
3 000
0
←D
PRO-ABN-VENT P 5/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
VENT
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-VENT P 6/6
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WHEEL
FLIGHT CREW
OPERATING MANUAL
[QRH] WHEEL TIRE DAMAGE SUSPECTED
Ident.: PRO-ABN-WHEEL-00019841.0001001 / 22 MAR 17
Applicable to: ALL
LDG DIST PROC......................................................................................................................APPLY
Performance impact of one burst tire is equivalent to one brake released.
TAXI WITH CARE
Refer to LIM-LG Taxi with Deflated or Damaged Tires
WHEEL HYD SEL FAULT
Applicable to: ALL
Ident.: PRO-ABN-WHEEL-AE-00017810.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the brake normal selector valve is failed, or the NWS selector valve is
at open position.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
PRO-ABN-WHEEL P 1/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WHEEL
FLIGHT CREW
OPERATING MANUAL
WHEEL HYD SEL FAULT (Cont'd)
Ident.: PRO-ABN-WHEEL-AE-00018363.0003001 / 21 MAR 16
L2
‐ If the normal brake selector valve is failed open, full green hydraulic pressure is present at
normal servovalves’ entry.
Nosewheel steering remains available.
‐ On ground, do not tow the aircraft with the yellow hydraulic system pressurized: If the steering
selector valve is failed open, nosewheel steering remains pressurized, and so towing may either
break the towbar shear pin, or the nose gear (if towbarless towing).
‐ If the steering selector valve is failed open, setting A/SKID & N/W STRG sw to OFF will cause
the nosewheel to go to maximum deflection.
L1
A/SKID & N/W STRG...........................................................................................................KEEP ON
As long as antiskid is operative, brake pressure is regulated by normal servovalves.
L2
WHEEL N/W STRG FAULT
Applicable to: ALL
Ident.: PRO-ABN-WHEEL-AF-00017744.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the nose wheel steering system is failed.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-ABN-WHEEL P 2/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WHEEL
FLIGHT CREW
OPERATING MANUAL
WHEEL N/W STRG FAULT (Cont'd)
Ident.: PRO-ABN-WHEEL-AF-00018712.0001001 / 21 MAR 16
Crew awareness.
Ident.: PRO-ABN-WHEEL-AF-00018713.0001001 / 21 MAR 16
L12
STATUS
INOP SYS
CAT 3 SINGLE ONLY
(1)
See
(1)
Note:
CAT 3 DUAL
N/W STRG
1. If the L/G SHOCK ABSORBER FAULT is also displayed, then the nose wheels may
be at maximum deflection (turned 90 ° from center). During landing, delay nose wheel
touchdown as long as possible.
2. Automatic rollout is not permitted (Refer to QRH/OPS Required Equipment for CAT2
and CAT3).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PRO-ABN-WHEEL P 3/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WHEEL
FLIGHT CREW
OPERATING MANUAL
WHEEL TYRE LO PR
Applicable to: ALL
Ident.: PRO-ABN-WHEEL-AG-00017824.0003001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when one of the following cases occurs:
‐ One tire pressure is below:
• 74% of nominal pressure between liftoff and engines shutdown, or
• 89% of nominal pressure in other cases.
‐ There is difference of pressure between two wheels of the same axle that is above:
• 21% of nominal pressure between liftoff and engines shutdown, or
• 15% of nominal pressure in other cases.
Flight Phase Inhibition:
Ident.: PRO-ABN-WHEEL-AG-00018714.0001001 / 21 MAR 16
Crew awareness.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PRO-ABN-WHEEL P 4/4
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WING A.ICE
FLIGHT CREW
OPERATING MANUAL
WING A.ICE L(R) HI PR
Applicable to: ALL
Ident.: PRO-ABN-W_A_ICE-Q-00017161.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the WING ANTI ICE pb-sw is set to ON and the pressure sensor
(downstream of the valve) indicates a high pressure in the duct.
Flight Phase Inhibition:
Ident.: PRO-ABN-W_A_ICE-Q-00018328.0001001 / 21 MAR 16
THRUST LIM PENALTY
Ident.: PRO-ABN-W_A_ICE-Q-00018330.0001001 / 21 MAR 16
STATUS
INOP SYS
THRUST LIM PENALTY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
WAI REGUL
A
PRO-ABN-W_A_ICE P 1/8
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WING A.ICE
FLIGHT CREW
OPERATING MANUAL
WING A.ICE L(R) VALVE OPEN
(FAILURE DETECTED IN FLIGHT)
Applicable to: ALL
Ident.: PRO-ABN-W_A_ICE-N-00017160.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the WING ANTI ICE pb-sw is set to OFF and one wing anti ice valve
remains open, in flight.
Flight Phase Inhibition:
Ident.: PRO-ABN-W_A_ICE-N-00018331.0001001 / 21 MAR 16
WAI AVAIL IN FLT
WING ANTI ICE...................................................................................................................AS RQRD
L2 Wing anti-ice is available if needed and anyway is continually on, on failed side.
L1 THRUST LIM PENALTY
After landing (automatic recall):
ENG BLEED (AFFECTED SIDE)........................................................................................... OFF
X BLEED (IF NOT CLOSED).............................................................................................. SHUT
APU BLEED (IF LEFT WING AFFECTED)............................................................................OFF
WING ANTI ICE......................................................................................................................OFF
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-ABN-W_A_ICE P 2/8
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WING A.ICE
FLIGHT CREW
OPERATING MANUAL
WING A.ICE L(R) VALVE OPEN (Cont'd)
(FAILURE DETECTED IN FLIGHT)
Ident.: PRO-ABN-W_A_ICE-N-00018332.0001001 / 21 MAR 16
STATUS
INOP SYS
In flight:
THRUST LIM PENALTY
WAI AVAIL IN FLT
ENG 1(2) BLEED (On ground
only)
PACK 1(2) (On ground only)
WING A.ICE L(R) VALVE OPEN
(FAILURE DETECTED ON GROUND)
Applicable to: ALL
Ident.: PRO-ABN-W_A_ICE-M-00017495.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the WING ANTI ICE pb-sw is set to OFF and one wing anti ice valve
remains open, on ground.
Flight Phase Inhibition:
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-ABN-W_A_ICE P 3/8
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WING A.ICE
FLIGHT CREW
OPERATING MANUAL
WING A.ICE L(R) VALVE OPEN (Cont'd)
(FAILURE DETECTED ON GROUND)
Ident.: PRO-ABN-W_A_ICE-M-00018333.0001001 / 21 MAR 16
WING ANTI ICE............................................................................................................................ OFF
ENG BLEED (AFFECTED SIDE)..................................................................................................OFF
X BLEED (IF NOT CLOSED).....................................................................................................SHUT
APU BLEED (IF LEFT WING AFFECTED AND IF APU RUNNING)........................................... OFF
WAI AVAIL IN FLT
After takeoff when above 1 500 ft (automatic recall):
WAI AVAIL IN FLT
ENG BLEED (AFFECTED SIDE)............................................................................................. ON
WING ANTI ICE............................................................................................................ AS RQRD
L2
Wing anti ice is available if needed and anyway is continually on, on failed side.
L1
THRUST LIM PENALTY
After landing (automatic recall):
WING ANTI ICE......................................................................................................................OFF
ENG BLEED (AFFECTED SIDE)........................................................................................... OFF
X BLEED (IF NOT CLOSED).............................................................................................. SHUT
APU BLEED (IF LEFT WING AFFECTED)............................................................................OFF
Ident.: PRO-ABN-W_A_ICE-M-00018334.0001001 / 21 MAR 16
STATUS
INOP SYS
Before takeoff:
WAI AVAIL IN FLT
In flight:
THRUST LIM PENALTY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
ENG 1 (2) BLEED (On ground
only)
PACK 1 (2) (On ground only)
←C
PRO-ABN-W_A_ICE P 4/8
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WING A.ICE
FLIGHT CREW
OPERATING MANUAL
WING A.ICE OPEN ON GND
Applicable to: ALL
Ident.: PRO-ABN-W_A_ICE-O-00017158.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the aircraft is on ground and the wing anti ice valves remain open for
more than 35 s after the WING ANTI ICE pb-sw is set to ON.
Flight Phase Inhibition:
Ident.: PRO-ABN-W_A_ICE-O-00018311.0001001 / 21 MAR 16
WING ANTI ICE............................................................................................................................ OFF
Ident.: PRO-ABN-W_A_ICE-O-00018335.0001001 / 21 MAR 16
STATUS
WAI AVAIL IN FLT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PRO-ABN-W_A_ICE P 5/8
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WING A.ICE
FLIGHT CREW
OPERATING MANUAL
WING A.ICE SYS FAULT
(ONE WING VALVE REMAINS CLOSED WHEN THE WING ANTI-ICE IS TURNED ON)
Applicable to: ALL
Ident.: PRO-ABN-W_A_ICE-P-00017159.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the WING ANTI ICE pb-sw is set to ON and one wing anti ice valve
remains closed.
Flight Phase Inhibition:
Ident.: PRO-ABN-W_A_ICE-P-00018338.0002001 / 21 MAR 16
WING ANTI ICE............................................................................................................................ OFF
AVOID ICING CONDITIONS
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
PRO-ABN-W_A_ICE P 6/8
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WING A.ICE
FLIGHT CREW
OPERATING MANUAL
WING A.ICE SYS FAULT (Cont'd)
(ONE WING VALVE REMAINS CLOSED WHEN THE WING ANTI-ICE IS TURNED ON)
Ident.: PRO-ABN-W_A_ICE-P-00018339.0004001 / 17 MAR 17
L12
STATUS
INOP SYS
AVOID ICING CONDITIONS
IF SEVERE ICE ACCRETION:
MIN SPD................................................. VLS +10/G DOT
MANEUVER WITH CARE
Note:
WING ANTI ICE
In the case of severe ice accretion, with wing
anti-ice failed, the Angle-of-Attack (AOA)
protections remain efficient. Manoeuvre with
care: avoid large roll inputs at high AOA and
high thrust setting. In the case of abnormal
response in pitch or roll, release the backstick
and reduce thrust.
LDG DIST PROC...................................................APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-ABN-W_A_ICE P 7/8
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
WING A.ICE
FLIGHT CREW
OPERATING MANUAL
WING A.ICE SYS FAULT
(THE WING ANTI-ICE IS TURNED ON AFTER ONE ENGINE
SHUTDOWN OR AFTER THE LOSS OF ONE BLEED)
Applicable to: ALL
Ident.: PRO-ABN-W_A_ICE-AA-00017496.0001001 / 21 MAR 16
ANNUNCIATIONS
Triggering Conditions:
L2
This alert triggers when the WING ANTI ICE pb-sw is set to ON and one wing anti ice valve
remains closed.
Flight Phase Inhibition:
Ident.: PRO-ABN-W_A_ICE-AA-00018340.0001001 / 21 MAR 16
X BLEED.................................................................................................................................... OPEN
L2
Note:
The affected pack has to be selected OFF due to precooler performance.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-ABN-W_A_ICE P 8/8
22 MAR 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DETAILED CABIN / COCKPIT EVACUATION PROCEDURE
GENERAL
Ident.: PRO-ABN-90-00010415.0001001 / 15 OCT 12
Applicable to: ALL
A successful outcome for an emergency situation depends, first of all, upon each crew member’s
perfect knowledge and execution of the duties assigned to him.
The captain should check frequently that all crew members know exactly their assigned positions and
their specific duties, as well as the duties of the other crew members, in case of an abnormal or an
emergency condition.
Since it is not possible to cover all the situations that may occur, the captain will be responsible
for adapting the following instructions to obtain the best coordination of the emergency operation.
Should it be physically impossible for the captain to carry out his duties, another crew member will
substitute for him according to the chain of command. The procedures in this manual are AIRBUS
procedures and should be considered to be a reference.
COCKPIT-ASSIGNED DUTIES FOR EVACUATION
Ident.: PRO-ABN-90-00010416.0001001 / 05 AUG 10
Applicable to: ALL
If it is NOT POSSIBLE to reach the passenger cabin:
The cockpit crew should evacuate the aircraft via the cockpit clearview windows, by using the
escape ropes.
On ground, each crewmember must help passengers, and direct them away from the aircraft.
If it is POSSIBLE to reach the passenger cabin:
‐ Is the last person to leave the cockpit: Proceeds to the cabin, and helps with passenger evacuation, as
necessary
CAPT ‐ Is the last person to leave the aircraft: Checks that all persons have evacuated the aircraft
‐ Evacuates the aircraft, via the rear door, or any other available exit, if he/she cannot reach the rear door.
‐ On ground, he/she takes command of operations until rescue units arrive.
F/O
‐ Proceeds to the cabin, and takes the emergency equipment.
‐ Evacuates the aircraft, using any available exit.
‐ Helps passengers on ground, and directs them away from the aircraft.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PRO-ABN-90 P 1/8
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DETAILED CABIN / COCKPIT EVACUATION PROCEDURE
CABIN CREW-ASSIGNED AREAS FOR EVACUATION
Ident.: PRO-ABN-90-00010607.0001001 / 17 MAR 11
Applicable to: ALL
CABIN CREW
DESIGNATION
1 PURSER
1 CABIN CREW
1 CABIN CREW
1 CABIN CREW
Note:
ASSIGNED JUMPSEAT
AND DOOR
DOOR 1 LH
DOOR 1 RH /LH
DOOR 2 RH
DOOR 2 LH
ASSIGNED DOOR
FWD OUTBOARD
FWD INBOARD
AFT CENTER
REARWARD
ASSIGNED AREA
FWD/MID
FWD/MID
MID/AFT
MID/AFT
These procedures are established for the minimum required number of 4 cabin crews.
COMMUNICATIONS
Ident.: PRO-ABN-90-00010418.0001001 / 04 JUL 17
Applicable to: ALL
1. EMERGENCY CALL
FROM
TO
CABIN
COCKPIT
CABIN
COCKPIT
COMMUNICATION METHOD(S)
‐ Press EMER pb-sw on the CALLS panel,
or
‐ Passenger Address (PA) System:
"PURSER TO COCKPIT PLEASE!"
‐ Interphone: "PRIO CAPT"
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D →
REMARKS
Purser must immediately go to the cockpit.
Any cabin crewmember can make such a
call. The cockpit crew must reply.
PRO-ABN-90 P 2/8
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DETAILED CABIN / COCKPIT EVACUATION PROCEDURE
FLIGHT CREW
OPERATING MANUAL
2. EMERGENCY ALERT
FROM
TO
CABIN
COCKPIT
COMMUNICATION METHOD(S)
‐ PA System: "ATTENTION CREW! AT
STATIONS!"
3. NOTIFICATION TO PASSENGERS
FROM
TO
COMMUNICATION METHOD(S)
CABIN
COCKPIT
‐ SIGNS ON
‐ PA System
PURSER
CABIN
4. FINISH PREPARATION
FROM
TO
CABIN
COCKPIT
5. BRACE FOR IMPACT
FROM
TO
CABIN
COCKPIT
‐ CABIN LIGHTS 100 %
‐ PA System
REMARKS
The cockpit crew makes a short and precise
announcement to warn that an emergency
evacuation may soon be required.
Cabin crews must proceed to their
emergency stations, and fasten their
seatbelts.
REMARKS
For psychological reasons, the cockpit crew
should be the first to inform of an intended
emergency landing.
Purser informs passengers that they have to
pay special attention to these warnings:
‐ “FINISH PREPARATION”
‐ “BRACE FOR IMPACT”
‐ “PASSENGERS EVACUATE”
COMMUNICATION METHOD(S)
REMARKS
The cockpit crew gives this order a short time
‐ Passenger Address (PA) System: "FINISH
before an emergency landing.
PREPARATION"
COMMUNICATION METHOD(S)
‐ PA System: "BRACE FOR IMPACT!"
REMARKS
The cockpit crew announces to brace for
impact approximately 1 min before landing.
6. INITIATE EVACUATION (RESTRICTED EXITS)
FROM
TO
COMMUNICATION METHOD(S)
REMARKS
CABIN
The cockpit crew orders an immediate
COCKPIT
‐ PA System: "PASSENGERS EVACUATE"
evacuation, and the cabin crew directs
‐ Activate EVAC signals
passengers to all available exists.
CABIN
CABIN
COCKPIT
‐ EVAC SIGNAL SYSTEM on FWD
AND CABIN
ATTND panel (FAP)
‐ PA System or megaphone
CABIN
‐ Verbal
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Used by the cabin crew, if there is no
signal or order from the cockpit, and if it is
unmistakably clear that the aircraft must be
evacuated.
The cabin crew stands up and shouts:
‐ "SEATBELTS OFF!"
‐ "LEAVE EVERYTHING!"
‐ "GET OUT!"
‐ "COME THIS WAY!"
←D→
PRO-ABN-90 P 3/8
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
DETAILED CABIN / COCKPIT EVACUATION PROCEDURE
FLIGHT CREW
OPERATING MANUAL
7. EVACUATION NOT REQUIRED
FROM
TO
COMMUNICATION METHOD(S)
CABIN
COCKPIT
‐ PA System: "CABIN CREW and
PASSENGERS REMAIN SEATED!"
REMARKS
When the Captain decides that an evacuation
is not required, the cockpit crew makes an
immediate announcement to this effect.
ON GROUND EVACUATION
Applicable to: ALL
Ident.: PRO-ABN-90-A-00010419.0001001 / 05 AUG 10
COCKPIT CREW PROCEDURES
The cockpit crew notifies the cabin crew of the nature of the emergency, and states intentions.
The cockpit crew uses the Passenger Address system to make an appropriate announcement,
such as: “PASSENGERS EVACUATE”, and presses the EVAC COMMAND pb.
Ident.: PRO-ABN-90-A-00010420.0001001 / 05 AUG 10
CABIN CREW PROCEDURES
When the cabin receives the order to evacuate, each cabin crewmember must proceed as follows:
STAND UP AND SHOUT........................................................................“UNFASTEN SEATBELTS”
OUTSIDE CONDITIONS........................................................................................................ CHECK
If outside conditions are safe:
DOOR IN ARMED POSITION............................................................................. OPEN FIRMLY
SHOUT......................................................................................................... “COME THIS WAY”
If the door does not open automatically:
DOOR..................................................................................PUSH AND OPEN MANUALLY
SLIDE (or SLIDERAFT) DEPLOYMENT......................................CHECK FULL DEPLOYMENT
It takes approximately 4 s for the slide (or slideraft) to deploy.
If the slide (or slideraft) does not automatically inflate:
RED, MANUAL INFLATION HANDLE..........................................................................PULL
The red, manual inflation handle is located on the right-hand side of the slide (or slideraft)
girt extension.
ORDER......................................................................................... “PASSENGERS EVACUATE”
PASSENGER EVACUATION ....................................................................................EXPEDITE
If the slide (or slideraft) becomes unserviceable:
PASSENGER EVACUATION.......................................................................................STOP
PASSENGERS TO ANOTHER USABLE EXIT...................................................REDIRECT
TOTAL ZONE EVACUATION..........................................................................................CHECK
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
PRO-ABN-90 P 4/8
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DETAILED CABIN / COCKPIT EVACUATION PROCEDURE
CABIN CREW........................................................................................................... EVACUATE
PASSENGERS AWAY FROM THE AIRCRAFT.............................................................DIRECT
If outside conditions are unsafe:
EXIT DOOR......................................................................................................................BLOCK
PASSENGERS TO NEAREST USABLE EXIT..........................................................REDIRECT
COCKPIT EVACUATION THROUGH WINDOW
Applicable to: ALL
Ident.: PRO-ABN-90-B-00010421.0001001 / 05 AUG 10
OPENING THE SLIDING WINDOW
HANDLE......................................................................................... PUSH DOWN AND PULL BACK
Pulling the handle backwards, opens the sliding window.
Ident.: PRO-ABN-90-B-00010422.0001001 / 24 NOV 15
COCKPIT EVACUATION WITH ESCAPE ROPE
ESCAPE ROPE STOWAGE.....................................................................................................OPEN
The escape rope stowage is located above the sliding window, on either side of the overhead
panel.
ESCAPE ROPE....................................................................................................................UNROLL
Unroll the escape rope, and throw it through the window.
SEAT................................................................................................................................... STEP ON
ESCAPE ROPE......................................................................................................................GRASP
Grasp the escape rope firmly with both hands, and slide down along the rope.
EVACUATION ON WATER
Applicable to: ALL
Ident.: PRO-ABN-90-C-00010423.0002001 / 17 MAR 11
CABIN CREW RESPONSIBLE FOR TYPE "I" DOORS
When the cabin receives the order to evacuate, each cabin crewmember must proceed as follows:
CHILDREN LIFEVESTS................................................................................................ DISTRIBUTE
STAND UP AND SHOUT.........................“UNFASTEN SEATBELTS – PUT ON YOUR LIFEVEST”
Inflate the lifevest, only once outside the aircraft.
ORDER................................................................................................................“REMOVE SHOES”
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to G →
PRO-ABN-90 P 5/8
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DETAILED CABIN / COCKPIT EVACUATION PROCEDURE
If the Type I door is usable:
DOOR IN ARMED POSITION........................................................................................... OPEN
SLIDERAFT....................................................................................................................DEPLOY
RED, MANUAL INFLATION HANDLE................................................................................ PULL
Do not wait for automatic inflation of the slideraft.
If the water level is close to the door sill:
The slideraft inflates on the water.
SLIDERAFT.................................................................. LEAVE ATTACHED TO CABIN FLOOR
PASSENGER LIFEVESTS....................................... INFLATE WHEN BOARDING SLIDERAFT
PASSENGERS........................................................................................... BOARD SLIDERAFT
TOTAL ZONE EVACUATION..........................................................................................CHECK
LAST CREWMEMBER............................................................................... BOARD SLIDERAFT
SLIDERAFT.............................................................................. SEPARATE FROM DOOR SILL
The last crewmember must separate the slideraft from the door sill, and board with all the
necessary safety equipment.
MOORING LINE....................................................................................................................CUT
SURVIVAL KIT........................................................................................................... RETRIEVE
The survival kit is attached to the slideraft via a lanyard.
If the water level is too far away from the door sill:
SLIDERAFT..........................................................................DISCONNECT FROM DOOR SILL
The slideraft remains tied to the aircraft by a 6 m (20 ft) mooring line.
MOORING LINE................................................................................................................. HOLD
To keep the slideraft close to the exit, hold the mooring line.
PASSENGER LIFEVESTS....................................... INFLATE WHEN BOARDING SLIDERAFT
PASSENGERS........................................................................................... BOARD SLIDERAFT
TOTAL ZONE EVACUATION..........................................................................................CHECK
LAST CREWMEMBER............................................................................... BOARD SLIDERAFT
The last crewmember must board with all the necessary safety equipment.
MOORING LINE....................................................................................................................CUT
SURVIVAL KIT........................................................................................................... RETRIEVE
The survival kit is attached to the slideraft via a lanyard.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
PRO-ABN-90 P 6/8
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
DETAILED CABIN / COCKPIT EVACUATION PROCEDURE
Evacuation is usually done through the passenger doors. However, if one of the
passenger doors is not usable, the overwing exit may be used for evacuation. The cabin
crew should install the lifeline to help passenger to stay on the wing. These passengers
will, however, be obliged to wait on the wing until the slideraft arrives, and until all other
passengers have evacuated from the passenger door exits, and have finished boarding
the sliderafts.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-ABN-90 P 7/8
05 SEP 17
PROCEDURES
ABNORMAL AND EMERGENCY PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DETAILED CABIN / COCKPIT EVACUATION PROCEDURE
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-ABN-90 P 8/8
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
Intentionally left blank
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-NOR-SOP Standard Operating Procedures
PRO-NOR-SOP-01 General Information
Foreword.................................................................................................................................................................. A
PRO-NOR-SOP-02 Flight Preparation
Technical Condition of the Aircraft.......................................................................................................................... A
Weather Briefing...................................................................................................................................................... B
NOTAMs.................................................................................................................................................................. C
GPS PRIMARY Availability (If Installed)................................................................................................................. D
Flight Plan and Operational Requirements............................................................................................................. E
Optimum Flight Level...............................................................................................................................................F
Fuel Requirements.................................................................................................................................................. G
PRO-NOR-SOP-03 Safety Exterior Inspection
Safety Exterior Inspection........................................................................................................................................A
PRO-NOR-SOP-04 Preliminary Cockpit Preparation
General.....................................................................................................................................................................A
Aircraft Setup........................................................................................................................................................... B
Battery Check/Setup................................................................................................................................................C
APU Fire Test/APU Start........................................................................................................................................ D
AIR COND............................................................................................................................................................... E
Cargo Heat ..................................................................................................................................................... F
Cockpit Lights.......................................................................................................................................................... G
ECAM.......................................................................................................................................................................H
FMGS Pre-Initialization............................................................................................................................................. I
EFB........................................................................................................................................................................... J
Before Walkaround.................................................................................................................................................. K
PRO-NOR-SOP-05 Exterior Walkaround
General.....................................................................................................................................................................A
Exterior Walkaround................................................................................................................................................ B
PRO-NOR-SOP-06 Cockpit Preparation
Introduction...............................................................................................................................................................A
Overhead Panel....................................................................................................................................................... B
CTR Instrument Panel.............................................................................................................................................C
Pedestal................................................................................................................................................................... D
RMP......................................................................................................................................................................... E
ACARS..................................................................................................................................................................... F
FMGS Preparation...................................................................................................................................................G
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-PLP-TOC P 1/8
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
Glareshield............................................................................................................................................................... H
Lateral Consoles....................................................................................................................................................... I
Instrument Panels.....................................................................................................................................................J
ECAM Control Panel............................................................................................................................................... K
ADIRS.......................................................................................................................................................................L
Takeoff Briefing....................................................................................................................................................... M
PC Dedicated to Maintenance ....................................................................................................................... N
Flow Pattern............................................................................................................................................................ O
PRO-NOR-SOP-07 Before Pushback or Start
Before Start Clearance............................................................................................................................................ A
At Start Clearance................................................................................................................................................... B
PRO-NOR-SOP-08 Engine Start
Automatic Engine Start............................................................................................................................................A
Ground Run Up - Danger Areas............................................................................................................................. B
PRO-NOR-SOP-09 After Start
After Start.................................................................................................................................................................A
PRO-NOR-SOP-10 Taxi
Taxi...........................................................................................................................................................................A
PRO-NOR-SOP-11 Before Takeoff
Before Takeoff......................................................................................................................................................... A
PRO-NOR-SOP-12 Takeoff
Takeoff..................................................................................................................................................................... A
PRO-NOR-SOP-13 After Takeoff
After Takeoff............................................................................................................................................................ A
PRO-NOR-SOP-14 Climb
Climb........................................................................................................................................................................ A
PRO-NOR-SOP-15 Cruise
Cruise....................................................................................................................................................................... A
PRO-NOR-SOP-16 Descent Preparation
Descent Preparation................................................................................................................................................ A
Continued on the following page
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PRO-NOR-SOP-17 Descent
Continued from the previous page
Descent Initiation..................................................................................................................................................... A
Descent Monitoring.................................................................................................................................................. B
Descent Adjustment.................................................................................................................................................C
Approach Checklist..................................................................................................................................................D
10 000 ft Flow Pattern.............................................................................................................................................E
PRO-NOR-SOP-18 Approach
PRO-NOR-SOP-18-A Approach General
Introduction...............................................................................................................................................................A
Cross-Reference Table............................................................................................................................................B
Flying Reference......................................................................................................................................................C
Stabilization Criteria.................................................................................................................................................D
Approach Speed Technique.................................................................................................................................... E
Discontinued Approach............................................................................................................................................ F
PRO-NOR-SOP-18-B Aircraft Configuration Management
Initial Approach........................................................................................................................................................ A
Intermediate/Final Approach....................................................................................................................................B
PRO-NOR-SOP-18-C Aircraft Guidance Management
Approach using LOC G/S Guidance....................................................................................................................... A
Approach using FINAL APP Guidance................................................................................................................... B
Approach using FPA Guidance...............................................................................................................................C
Circling Approach.................................................................................................................................................... D
RNAV Visual Approach........................................................................................................................................... E
Visual Approach....................................................................................................................................................... F
PRO-NOR-SOP-19 Landing
Manual Landing....................................................................................................................................................... A
Autoland................................................................................................................................................................... B
PRO-NOR-SOP-20 Go-Around
Go Around with FD..................................................................................................................................................A
PRO-NOR-SOP-21 After Landing
After Landing............................................................................................................................................................A
PRO-NOR-SOP-22 Parking
Parking..................................................................................................................................................................... A
Continued on the following page
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PRO-NOR-SOP-23 Securing the Aircraft
Continued from the previous page
Securing the Aircraft................................................................................................................................................ A
PRO-NOR-SOP-90 Standard Callouts
Communications and Standard Terms....................................................................................................................A
Checklist Callouts.................................................................................................................................................... B
Actions Commanded by PF.................................................................................................................................... C
FMA..........................................................................................................................................................................D
Altitude..................................................................................................................................................................... E
Flaps or Gear Callouts............................................................................................................................................ F
Flight Parameters.................................................................................................................................................... G
PF/PM Duties Transfer............................................................................................................................................H
Summary for Each Phase.........................................................................................................................................I
PRO-NOR-SUP Supplementary Procedures
PRO-NOR-SUP-SUP Supplementary Procedures Menu
Supplementary Procedures..................................................................................................................................... A
PRO-NOR-SUP-ADVWXR Adverse Weather
Airframe Deicing/Anti-Icing Procedure on Ground.................................................................................................. A
Ground Operations in Cold Weather Conditions.....................................................................................................B
Ground Operations in Heavy Rain..........................................................................................................................C
Minimum Speed with Ice Accretion.........................................................................................................................D
Operations on Contaminated Airports..................................................................................................................... E
Operations with Volcanic Ash, Sand or Dust.......................................................................................................... F
Securing the Aircraft for Cold Soak........................................................................................................................ G
For Draining Water Procedure................................................................................................................................ H
Water System Draining............................................................................................................................................. I
PRO-NOR-SUP-COM Communication
VHF, HF Utilization.................................................................................................................................................. A
Continued on the following page
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PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-NOR-SUP-ENG Engines
Continued from the previous page
Manual Engine Start................................................................................................................................................ A
Engine Start with External Pneumatic Power......................................................................................................... B
Crossbleed Engine Start......................................................................................................................................... C
Engine Start Valve Manual Operation.....................................................................................................................D
Engine Ventilation (Dry Cranking)........................................................................................................................... E
One Engine Taxi - General..................................................................................................................................... F
One Engine Taxi - At Departure.............................................................................................................................G
One Engine Taxi - At Arrival...................................................................................................................................H
PRO-NOR-SUP-FUEL Fuel
Refueling.................................................................................................................................................................. A
Refueling with One Engine Running....................................................................................................................... B
Ground Fuel Transfer.............................................................................................................................................. C
Defueling.................................................................................................................................................................. D
PRO-NOR-SUP-LG L/G
PRO-NOR-SUP-LG-LG_DN Flight with Landing Gear Down
General.....................................................................................................................................................................A
Limitations................................................................................................................................................................ B
Procedures...............................................................................................................................................................C
Takeoff..................................................................................................................................................................... D
Flight Planning......................................................................................................................................................... E
Climb........................................................................................................................................................................ F
Cruise.......................................................................................................................................................................G
Holding..................................................................................................................................................................... H
Descent......................................................................................................................................................................I
Go-Around................................................................................................................................................................ J
One Engine Inoperative...........................................................................................................................................K
PRO-NOR-SUP-LG-LG Operation with Nosewheel Steering Offset
Operation with Nosewheel Steering Offset............................................................................................................. A
PRO-NOR-SUP-MISC Miscellaneous
PRO-NOR-SUP-MISC-D Pushback with Power Push Unit
Pushback with Power Push Unit Via the Main Landing Gear.................................................................................A
PRO-NOR-SUP-MISC-A Hight Altitude Airport Operations
High Altitude Airport Operations..............................................................................................................................A
Continued on the following page
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PRO-NOR-SUP-MISC-C Operations at QNH Above 1050 hPa
Continued from the previous page
General.....................................................................................................................................................................A
Consequences......................................................................................................................................................... B
Procedures...............................................................................................................................................................C
PRO-NOR-SUP-NAV Navigation
Insertion of Approach Minima..................................................................................................................................A
PRO-NOR-SRP Systems Related Procedures
PRO-NOR-SRP-01 FMS
PRO-NOR-SRP-01-05 Introduction
Introduction...............................................................................................................................................................A
PRO-NOR-SRP-01-10 Cockpit Preparation
FMGS Initialization...................................................................................................................................................A
Flight Plan Initialization............................................................................................................................................B
FMGS Data Insertion...............................................................................................................................................C
FMGS Re-Initialization After a Canceled Flight...................................................................................................... D
PRO-NOR-SRP-01-15 Before Pushback or Start
Change of Runway.................................................................................................................................................. A
TAKEOFF FROM INTERSECTION.........................................................................................................................B
PRO-NOR-SRP-01-20 Taxi
FCU Selection for Takeoff.......................................................................................................................................A
FMA Mode Check....................................................................................................................................................B
Selecting a Navigation Display................................................................................................................................C
Selecting Takeoff Displays for Pilot's and Copilot's MCDU.................................................................................... D
PRO-NOR-SRP-01-30 Takeoff
Monitoring the Takeoff.............................................................................................................................................A
PRESELECTING A HDG OR A TRK......................................................................................................................B
Normal Takeoff Profile.............................................................................................................................................C
No Flight Director Takeoff....................................................................................................................................... D
TAKEOFF WITH NO V2 ENTRY............................................................................................................................ E
Takeoff Using the Localizer of the Opposite Runway.............................................................................................F
PRO-NOR-SRP-01-40 Climb
Monitoring the Climb Phase.................................................................................................................................... A
Expedite Climb.........................................................................................................................................................B
Immediate Return to Origin Airport......................................................................................................................... C
Continued on the following page
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PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-NOR-SRP-01-50 Cruise
Continued from the previous page
Reaching Cruise Flight Level.................................................................................................................................. A
Monitoring the Navigation Accuracy........................................................................................................................B
Monitoring the Fuel Predictions...............................................................................................................................C
Entering a Step Climb or a Step Descent.............................................................................................................. D
Immediate Change of Level in Cruise.....................................................................................................................E
Preparation for Descent and Approach................................................................................................................... F
PRO-NOR-SRP-01-60 Descent
DESCENT INITIATION............................................................................................................................................ A
Descent Monitoring.................................................................................................................................................. B
Expedite Descent (If installed)................................................................................................................................ C
Monitoring the Navigation in the Terminal Control Area.........................................................................................D
Too Steep Path........................................................................................................................................................E
Holding Pattern........................................................................................................................................................ F
MANUAL TERMINATION........................................................................................................................................G
PRO-NOR-SRP-01-70 Approach
Initial Approach........................................................................................................................................................ A
ILS/MLS/GLS/FLS Approach................................................................................................................................... B
Switching from Non ILS to ILS Approach............................................................................................................... C
Landing Categories..................................................................................................................................................D
Warnings for ILS Approach..................................................................................................................................... E
PRO-NOR-SRP-01-80 Go-Around
MONITORING THE GO-AROUND..........................................................................................................................A
Go-Around Profile.................................................................................................................................................... B
Missed Approach: Try Again...................................................................................................................................C
Missed Approach: Divert......................................................................................................................................... D
Task Sharing During a Go-Around..........................................................................................................................E
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STANDARD OPERATING PROCEDURES - GENERAL INFORMATION
FOREWORD
Ident.: PRO-NOR-SOP-01-00010142.0001001 / 02 MAY 17
Applicable to: ALL
The procedures contained in this Chapter are recommended by Airbus, and are consistent with the
other Chapters of this manual.
The Authorities do not certificate Standard Operating Procedures. The manufacturer presents them
herein as the best way to proceed, from a technical and operational standpoint. They are continually
updated and the revisions take into account Operator input, as well as manufacturer experience.
In addition, Operators may amend them, as needed. However, the manufacturer recommends that
Operators using the FCOM as onboard operational manual submit suggested changes to expedite
publication, and maintain consistency of the manual. The Operator should note that they may rewrite
this Chapter, at their own responsibility; this could, however, make it difficult to update the manual
and keep it consistent with the other Chapters.
The following sections contain expanded information on normal procedures.
Standard Operating Procedures consist of inspections, preparations, and normal procedures. All
items of a given procedure are listed in a sequence that follows a standardized scan of the cockpit
panels, unless that sequence goes against the action priority logic, to ensure that all actions are
performed in the most efficient way.
These procedures assume that all systems are operating normally, and that all automatic functions
are used normally.
The FCOM also contains normal procedures that are non-routine procedures in the Supplementary
Procedures chapter and in the Special Operations chapter.
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STANDARD OPERATING PROCEDURES - FLIGHT PREPARATION
TECHNICAL CONDITION OF THE AIRCRAFT
Ident.: PRO-NOR-SOP-02-00010147.0001001 / 05 AUG 10
Applicable to: ALL
The crew will verify the technical state of the aircraft (deferred defect list), with regard to
airworthiness, acceptability of malfunctions (MEL), and influence on the flight plan.
WEATHER BRIEFING
Ident.: PRO-NOR-SOP-02-00010148.0001001 / 05 AUG 10
Applicable to: ALL
‐ The crew will get a weather briefing
‐ The briefing should include:
• Actual and expected weather conditions, including runway conditions for takeoff and climb-out
• Significant weather enroute, including winds and temperatures
• Terminal forecasts for destination and alternate airports
• Actual weather for destination and alternates, for short range flights and recent past weather, if
available
• Survey of the meteorological conditions at airports along the planned route.
Weather can affect the choice of routing (for example, influence which route is quickest) and
the choice of flight level. The flight crew must also consider the possibility of runways being
contaminated at the departure and destination airfields. The flight crew must also verify ISA
deviations and enroute icing conditions, and must consider the possibility of holding due to weather
at the destination.
NOTAMS
Ident.: PRO-NOR-SOP-02-00010149.0002001 / 29 MAY 13
Applicable to: ALL
‐ The flight crew must examine NOTAMs for changes to routings, unserviceable navaids, availability
of runways and approach aids etc, all of which may affect the final fuel requirement
‐ In order to prevent the risks of projection of debris towards the trimmable horizontal stabilizer
and the elevators, it is not recommended to takeoff from runways in bad condition (loose surface,
under repair, covered with debris...)
GPS PRIMARY AVAILABILITY (IF INSTALLED)
Ident.: PRO-NOR-SOP-02-00014998.0002001 / 20 MAR 17
Applicable to: ALL
For RNP1 operations, RNAV(GNSS) approaches and RNAV (RNP) approaches:
RAIM/AIME has been demonstrated to be available 100% of the time with 24 healthy satellites.
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STANDARD OPERATING PROCEDURES - FLIGHT PREPARATION
If required by operational regulation, for specific conditions (e.g RNAV(RNP), mountainous
terrain or less than 24 satellites) an appropriate Ground-Based Prediction Program should be
used to check the RAIM/AIME for each intended procedure (arrival, departure and alternate if
required)
FLIGHT PLAN AND OPERATIONAL REQUIREMENTS
Ident.: PRO-NOR-SOP-02-00010150.0001001 / 18 MAR 11
Applicable to: ALL
‐ The crew will check the company flight plan for routing, altitudes, and flight time
‐ The Captain will check the ATC flight plan and ensure that:
• It is filled in and filed, in accordance with the prescribed procedures
• It agrees with the fuel flight plan routing.
‐ The crew will check the estimated load figures, and will calculate the maximum allowable takeoff
and landing weights.
OPTIMUM FLIGHT LEVEL
Ident.: PRO-NOR-SOP-02-00010151.0001001 / 22 MAR 17
Applicable to: ALL
The flight crew should choose a flight level that is as close to the optimum as possible. To determine
the optimum flight level, Refer to QRH/PER-M Optimum & Maximum Altitudes (Paper Only) or use
the performance application of FlySmart with Airbus.
As a general rule, an altitude that is 4 000 ft below the optimum produces a significant penalty
(approximately 5 % of fuel). Flight 8 000 ft below the optimum altitude produces a penalty of more
than 10 % against trip fuel. (The usual contingency allowance is 5 %).
FUEL REQUIREMENTS
Ident.: PRO-NOR-SOP-02-00010152.0001001 / 05 AUG 10
Applicable to: ALL
COMPUTERIZED FLIGHT PLAN CHECK
In most cases the flight crew uses a computer-derived flight plan to obtain the correct fuel
requirements. Although these computerized requirements are normally accurate, the flight crew
must check them for gross errors.
The easiest way to do this is to use the “Quick Determination of F-PLN ” tables (Refer to
PER-FPL-FLP-QFP-40 FLIGHT PLANNING M.78). Although the aircraft will fly at ECON MACH
that is based on the cost index, the M 0.78 table is accurate enough to permit the crew to check for
gross error.
Ensure that both the captain and the first officer have verified that the fuel calculations and
required fuel on board are correct and that the figure complies with the applicable regulations.
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STANDARD OPERATING PROCEDURES - FLIGHT PREPARATION
FUEL TRANSPORTATION
The flight crew must check the policy covering the “tankering” of fuel on sectors where there is a
favourable fuel price differential or operational requirement.
Remember that carrying unnecessary extra fuel increases the fuel consumption for that sector and
therefore reduces the economy of the operation (lower flex temperature, more tire and brake wear,
more time in climb phase, lower optimum flight level etc).
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STANDARD OPERATING PROCEDURES
- SAFETY EXTERIOR INSPECTION
FLIGHT CREW
OPERATING MANUAL
SAFETY EXTERIOR INSPECTION
Applicable to: ALL
Ident.: PRO-NOR-SOP-03-A-00010153.0001001 / 05 AUG 10
Items marked by (*) are the only steps to be completed during a transit stop.
This inspection ensures that the aircraft and its surroundings are safe for operations.
On arriving at the aircraft, check for obstructions in the vicinity, engineering activity, refueling, etc.
Ident.: PRO-NOR-SOP-03-A-00010154.0001001 / 04 MAR 14
* WHEEL CHOCKS.................................................................................................................. CHECK
If the wheel chocks are not in position, the flight crew must check that the parking brake is set with
sufficient accumulator pressure.
Ident.: PRO-NOR-SOP-03-A-00010155.0001001 / 18 MAR 11
* LANDING GEAR DOORS....................................................................................CHECK POSITION
WARNING
Do not pressurize the green hydraulic system without clearance from ground
personnel, if any gear door is open. Remember that the green hydraulic system is
pressurized if the yellow system is pressurized and the PTU is on AUTO.
Ident.: PRO-NOR-SOP-03-A-00010156.0001001 / 05 AUG 10
* APU AREA............................................................................................................................. CHECK
Observe that the APU inlet and outlet are clear.
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- PRELIMINARY COCKPIT PREPARATION
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OPERATING MANUAL
GENERAL
Ident.: PRO-NOR-SOP-04-00010164.0001001 / 20 MAR 17
Applicable to: ALL
Items marked by asterisks (*) are the only steps to be completed after a transit stop without flight
crew change. Otherwise, the new flight crew performs all the items.
The following procedure, performed by the PM, ensures that all the required checks are performed
before applying electrical power to avoid inadvertent operation of systems and danger to the aircraft
and personnel.
Included is APU starting and the establishment of electrical and pneumatic power.
For EFB operations, the following procedure performed by both pilots is based on the use of two
EFBs/eQRH in order to reduce the risk of erroneous inputs.
Airbus recommends operating with two EFBs.
DOCUMENTATION AND MAINTENANCE
On entering the aircraft, obtain the technical (maintenance) log and verify that the certificate of
maintenance and daily inspection (or similar) are up to date and signed. Check the deferred or
carried-forward defects. If refueling has already been completed, check the uplift.
AIRCRAFT SETUP
Applicable to: ALL
Ident.: PRO-NOR-SOP-04-A-00021906.0001001 / 30 AUG 17
WARNING
Do not pressurize the hydraulic systems until clearance is obtained from ground
personnel.
Ident.: PRO-NOR-SOP-04-A-00010165.0001001 / 03 MAR 14
ENG
ENG MASTERS 1, 2................................................................................................................... OFF
ENG MODE selector................................................................................................................NORM
Ident.: PRO-NOR-SOP-04-A-00011188.0001001 / 22 APR 16
*WEATHER RADAR
*
*
*
*
RADAR sw ..............................................................................................................................OFF
WINDSHEAR / PWS sw .................................................................................................. OFF
GAIN knob ................................................................................................................... AUTO/CAL
MODE selector ..............................................................................................................AS RQRD
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- PRELIMINARY COCKPIT PREPARATION
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OPERATING MANUAL
Ident.: PRO-NOR-SOP-04-A-00010166.0001001 / 03 MAR 14
L/G
L/G lever.................................................................................................................................. DOWN
Ident.: PRO-NOR-SOP-04-A-00010167.0001001 / 03 MAR 14
WIPERS
Both WIPER selectors................................................................................................................. OFF
BATTERY CHECK/SETUP
Ident.: PRO-NOR-SOP-04-00010168.0001001 / 30 AUG 17
Applicable to: ALL
If the aircraft has not been electrically supplied for 6 h or more, perform the following
check:
BAT 1 pb and BAT 2 pb......................................................................................... CHECK OFF
BAT 1 and 2 VOLTAGE......................................................................... CHECK ABOVE 25.5 V
Battery voltage above 25.5 V ensures a charge above 50 %.
If the battery voltage is at or below 25.5 V:
A charging cycle of about 20 min is required.
BAT 1 pb and BAT 2 pb..............................................................................................AUTO
EXT PWR pb-sw.............................................................................................................. ON
Check on ELEC SD page, that the battery contactor is closed and the batteries are
charging.
After 20 min:
BAT 1 + 2 pb........................................................................................................... OFF
BAT 1 and 2 VOLTAGE............................................................ CHECK ABOVE 25.5 V
BAT 1 + 2 pb........................................................................................................ AUTO
If the battery voltage is above 25.5 V:
BAT 1 pb and BAT 2 pb..............................................................................................AUTO
If the APU is started on batteries only, it should be started within 30 min after the selection
of batteries to AUTO (35 min after battery selection to AUTO, the battery charge is less
than 25 % of maximum capacity).
If the aircraft has been electrically supplied during the last 6 h:
BAT 1 pb and BAT 2 pb.................................................................................................... AUTO
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- PRELIMINARY COCKPIT PREPARATION
FLIGHT CREW
OPERATING MANUAL
If the AVAIL light is on:
EXT PWR pb-sw.....................................................................................................................ON
APU FIRE TEST/APU START
Applicable to: ALL
Ident.: PRO-NOR-SOP-04-B-00010170.0001001 / 07 JUN 16
APU FIRE
APU FIRE pb-sw.....................................................................................CHECK IN and GUARDED
AGENT lights ................................................................................................................CHECK OFF
APU FIRE TEST pb...................................................................................... PRESS and MAINTAIN
Check :
‐ APU FIRE warning on ECAM + CRC + MASTER WARN light (if AC Power available).
‐ APU FIRE pb-sw lighted red.
‐ SQUIB light and DISCH light on
Ident.: PRO-NOR-SOP-04-B-00010171.0015001 / 17 MAR 17
APU START
If the EXT PWR pb-sw ON light is on:
APU MASTER SW pb-sw ..................................................................................................... ON
APU START pb-sw ................................................................................................................ON
Note:
Wait at least 3 s before selecting APU START pb-sw.
For more information on the APU start, Refer to DSC-49-20 Overhead Panel - Illustration.
For more information on APU starter limitations and APU operations during refueling:
‐ Refer to LIM-APU APU Start
‐ Refer to LIM-APU APU Start/Shutdown during Refueling/Defueling.
EXT PWR pb-sw ........................................................................................................ AS RQRD
The flight crew should keep ON the external power units to reduce the APU load, particularly
in hot weather conditions.
If the EXT PWR pb-sw ON light is off:
APU MASTER SW pb-sw ..................................................................................................... ON
APU START pb-sw ................................................................................................................ON
Note:
Wait at least 3 s before selecting APU START pb-sw.
For more information on the APU start, Refer to DSC-49-20 Overhead Panel - Illustration.
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- PRELIMINARY COCKPIT PREPARATION
FLIGHT CREW
OPERATING MANUAL
For more information on APU starter limitations and APU operations during refueling:
‐ Refer to LIM-APU APU Start
‐ Refer to LIM-APU APU Start/Shutdown during Refueling/Defueling.
AIR COND
Ident.: PRO-NOR-SOP-04-00010177.0001001 / 14 OCT 15
Applicable to: ALL
AIR COND
When the APU is AVAIL:
APU BLEED pb-sw................................................................................................................. ON
Do not use APU BLEED, if the ground personnel confirms that a LP or HP ground air unit is
connected to the aircraft.
To determine if an HP ground air unit is connected, the flight crew should also check on the
BLEED SD page, if there is pressure in the bleed air system.
ALL WHITE LIGHTS............................................................................................................. OFF
X BLEED selector.............................................................................................................. AUTO
Zone temperature selectors.........................................................................................AS RQRD
Full range temperature 24 ± 6 °C (75 ± 11 °F).
CARGO HEAT
Ident.: PRO-NOR-SOP-04-00010178.0001001 / 03 MAR 14
Applicable to: ALL
CARGO HEAT
TEMPERATURE selector ................................................................................................. AS RQRD
COCKPIT LIGHTS
Ident.: PRO-NOR-SOP-04-00010172.0002001 / 23 JUN 15
Applicable to: ALL
COCKPIT LIGHTS
* COCKPIT LIGHTS..........................................................................................................AS RQRD
Set INT LT, FLOOD LT, INTEG LT (included glareshield and FCU).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to G
PRO-NOR-SOP-04 P 4/10
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES
- PRELIMINARY COCKPIT PREPARATION
FLIGHT CREW
OPERATING MANUAL
ECAM
Ident.: PRO-NOR-SOP-04-00010204.0001001 / 04 SEP 17
Applicable to: ALL
* ECAM
* RCL pb ........................................................................................................................PRESS 3 s
This action recalls all the warnings that the flight crew cleared or cancelled during the last flight.
* Check MEL if required.
On the DOOR SD page:
* OXY ....................................................................................................... CHECK PRESSURE
If the OXY pressure is half boxed in amber:
MIN FLT CREW OXY CHART............................................................. CHECK PRESSURE
Verify that the pressure is sufficient for the scheduled flight (Refer to LIM-OXY Minimum
Flight Crew Oxygen Pressure).
On the HYD SD page:
* RESERVOIR FLUID LEVEL................................................CHECK WITH NORMAL RANGE
Note:
The volume of the hydraulic fluid in the reservoirs may change with Outside Air
Temperature. As a result, the reservoir fluid level that appears on the HYD SD page
may be outside of the normal range with no HYD RSVR LO AIR PR or HYD RSVR LO
LVL warning. If the fluid level is outside of the normal range, contact maintenance to
determine if service is required.
On the ENG SD page:
* ENG OIL QUANTITY.................................................................................. CHECK NORMAL
Check that the oil quantity is at or above 9.5 qt + estimated consumption (average estimated
consumption ~ 0.5 qt/h).
FMGS PRE-INITIALIZATION
Applicable to: ALL
Ident.: PRO-NOR-SOP-04-C-00014422.0001001 / 20 MAR 17
Perform FMGS Pre-Initialization in the case of ACARS operations, or EFB operations with
SYNCHRO AVIONICS .
At electrical power-up, the FMGS s and FCU run through various internal tests. Allow enough time
(3 min) for tests’ completion, and do not start to press pushbuttons until the tests are over. If the
“PLEASE WAIT” message appears, do not press any MCDU key until the message clears.
* FLT NBR................................................................................................................................ INSERT
* FROM/TO...............................................................................................................................INSERT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H to I
PRO-NOR-SOP-04 P 5/10
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES
- PRELIMINARY COCKPIT PREPARATION
EFB
Applicable to: ALL
Ident.: PRO-NOR-SOP-04-F-00021232.0001001 / 21 MAR 17
EFB/EQRH START
ALL EFB/eQRH....................................................................................................................... START
In accordance with the Operator's policy or if required by operational regulation:
EFB/eQRH VERSION......................................................................................................CHECK
If required, the flight crew performs this check unless a specific procedure is established as
per Operator's policy to ensure that the correct version is onboard.
On the EFB STATUS page and the eQRH My aircraft page, check the EFB VERSION number
and compare it with the valid version number given as reference by the Operator (e.g. on the
company flight plan).
*OPERATION ENGINEERING BULLETINS (OEB)
* OEB in eQRH.....................................................................................................................CHECK
Go to the OEB section of the eQRH and review all OEB s (particularly red OEBs) that are
applicable to the aircraft.
Note:
If there is a transfer of duties during this flight, the flight crew must remind the incoming
flight crew of the applicable OEB(s) during the briefing that is done when transferring the
duties.
* EFB SYNCHRO AVIONICS ......................................................................................... CLICK
Each flight crewmember checks (if retrieved from FMS) or enters:
‐ Aircraft Type
‐ Aircraft Registration
‐ Flight Number
‐ The departure and arrival airports
Both flight crewmembers crosscheck all the data.
REQUIRED APPLICATIONS.................................................................................................. START
Ident.: PRO-NOR-SOP-04-F-00021234.0001001 / 20 MAR 17
*ECAM/LOGBOOK CHECK
* RCL pb......................................................................................................................... PRESS 3 s
This action recalls all the warnings that the flight crew cleared or cancelled during the last flight
* Check MEL if required.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
J→
PRO-NOR-SOP-04 P 6/10
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES
- PRELIMINARY COCKPIT PREPARATION
* LOGBOOK or EFB E-LOGBOOK ...............................................................................CHECK
‐ In the logbook or EFB e-logbook, check the technical condition of the aircraft (deferred defect
list) with regard to airworthiness, acceptability of the MEL , or the Configuration Deviation List
(CDL), and influence on the flight plan.
‐ Crosscheck with ECAM recall.
* MEL /CDL ITEMS (as appropriate)......................................... CHECK DISPATCH CONDITIONS
Access the MEL and CDL items via the Ops Library Browser.
* MEL ITEMS (as appropriate)........................................................................................ ACTIVATE
As appropriate, the activated MEL items are sent to the applicable performance applications.
* CDL ITEMS (as appropriate)................................................................ ACTIVATE & COMPLETE
Complete missing items of CDL items. As appropriate, the activated CDL items are sent to the
applicable performance applications.
* AIRCRAFT ACCEPTANCE...........................................................................................PERFORM
Ident.: PRO-NOR-SOP-04-F-00021233.0001001 / 20 MAR 17
*PRELIMINARY PERFORMANCE DATA CALCULATION
Each flight crewmember independently computes the preliminary performance data in accordance
with the technical condition of the aircraft and/or any other criteria that may impact the aircraft
performance (e.g. NOTAM, runway condition, aircraft configuration).
* AIRFIELD DATA................................................................................................................ OBTAIN
Obtain data needed for initializing the system, preparing the cockpit and for preliminary takeoff
performance computation. The airfield data should include: RUNWAY IN USE, ALTIMETER
SETTING, and WEATHER DATA.
If the LOADSHEET application is used :
PRELIMINARY LOADING.......................................................COMPUTE AND CROSSCHECK
If dispatch under MEL and in accordance with the logbook:
* MEL /CDL ITEMS (as appropriate)........................................................ CHECK ACTIVATED
As appropriate, check that the MEL and CDL items are activated in the applicable
performance application.
PRELIMINARY TAKEOFF PERF.................................................. COMPUTE AND CROSSCHECK
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←J
PRO-NOR-SOP-04 P 7/10
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES
- PRELIMINARY COCKPIT PREPARATION
FLIGHT CREW
OPERATING MANUAL
BEFORE WALKAROUND
Applicable to: ALL
Ident.: PRO-NOR-SOP-04-E-00010173.0001001 / 05 AUG 10
F/CTL
FLAPS.................................................................................................................. CHECK POSITION
Check the upper ECAM display to confirm that the FLAPS position agrees with the handle
position.
* SPEEDBRAKE lever........................................................ CHECK RETRACTED and DISARMED
WARNING
If flight control surface positions do not agree with the control handle positions,
check with the maintenance crew before applying hydraulic power.
Ident.: PRO-NOR-SOP-04-E-00010174.0001001 / 18 MAY 16
* PARKING BRAKE
ACCU PRESS indicator......................................................................................................... CHECK
The ACCU PRESS indication must be in the green band. If required use the electric pump on
yellow hydraulic system to recharge the brake accumulator.
PARKING BRAKE handle............................................................................................................. ON
When one brake temperature is above 500 °C, avoid applying the parking brake, unless
operationally necessary.
BRAKES PRESS indicator.....................................................................................................CHECK
Check for normal indications.
WARNING
Yellow and green hydraulic systems are pressurized from yellow electric pump.
Get ground crew clearance before using the electric pump.
Ident.: PRO-NOR-SOP-04-E-00010206.0001001 / 23 JUN 15
EMERGENCY EQUIPMENT
EMER EQPT.......................................................................................................................... CHECK
Check the emergency equipments as follows:
‐ Life jackets stowed
‐ Axe stowed
‐ Smoke hoods or portable oxygen equipment and full face masks stowed and
serviceable
‐ Portable fire extinguisher lockwired and pressure in the green area
‐ Smoke goggles stowed (smoke hoods )
‐ Oxygen masks stowed
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K→
PRO-NOR-SOP-04 P 8/10
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES
- PRELIMINARY COCKPIT PREPARATION
‐ Flashlights stowed
‐ Escape ropes stowed
Ident.: PRO-NOR-SOP-04-E-00010207.0001001 / 14 SEP 12
RAIN REPELLENT
RAIN RPLNT indicators.......................................................... CHECK PRESSURE and QUANTITY
CAUTION
Never use rain repellent to wash the windshield and never use it on a dry
windshield.
Ident.: PRO-NOR-SOP-04-E-00010208.0001001 / 05 AUG 10
REAR AND OVERHEAD CIRCUIT BREAKERS PANELS
REAR and OVERHEAD CIRCUIT BREAKERS panels......................................................... CHECK
Check that all circuit breakers are set. Reset as necessary.
Ident.: PRO-NOR-SOP-04-E-00010209.0001001 / 25 JAN 17
LANDING GEAR PINS AND COVERS
* GEAR PINS and COVERS..................................................... CHECK ONBOARD and STOWED
Check that three are on board and stowed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←K
PRO-NOR-SOP-04 P 9/10
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES
- PRELIMINARY COCKPIT PREPARATION
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SOP-04 P 10/10
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - EXTERIOR WALKAROUND
GENERAL
Ident.: PRO-NOR-SOP-05-00010360.0001001 / 17 MAY 17
Applicable to: ALL
The exterior walkaround ensures that the general condition of the aircraft is satisfactory and that the
visible aircraft components and equipment are safe for the flight:
‐ There is no impact damage to the structure
‐ There is no evident fuel, oil, or hydraulic leak
‐ All ground access doors are closed.
The flight crew must perform a complete walkaround before each flight.
The parking brake must be set to ON during the exterior walkaround, in order to enable the flight
crew to check brake wear indicators.
WARNING
If any landing gear door is open, do not apply hydraulic power until clearance is
obtained from ground personnel.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-NOR-SOP-05 P 1/8
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - EXTERIOR WALKAROUND
EXTERIOR WALKAROUND
Applicable to: ALL
Ident.: PRO-NOR-SOP-05-A-00010361.0001001 / 04 MAY 15
SCHEMATIC
(1)
Refer to PRO-NOR-SOP-05 Exterior Walkaround - LH FWD Fuselage
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-NOR-SOP-05 P 2/8
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - EXTERIOR WALKAROUND
(2)
Refer to PRO-NOR-SOP-05 Exterior Walkaround - Nose Section
(3)
Refer to PRO-NOR-SOP-05 Exterior Walkaround - Nose L/G
(4)
Refer to PRO-NOR-SOP-05 Exterior Walkaround - RH FWD Fuselage
(5)
Refer to PRO-NOR-SOP-05 Exterior Walkaround - Lower Center Fuselage
(6)
Refer to PRO-NOR-SOP-05 Exterior Walkaround - RH Center Wing
(7)
Refer to PRO-NOR-SOP-05 Exterior Walkaround - ENG 2 LH Side
(8)
Refer to PRO-NOR-SOP-05 Exterior Walkaround - ENG 2 RH Side
(9)
Refer to PRO-NOR-SOP-05 Exterior Walkaround - RH Wing Leading Edge
(10) Refer to PRO-NOR-SOP-05 Exterior Walkaround - RH Wing Trailing Edge
(11) Refer to PRO-NOR-SOP-05 Exterior Walkaround - RH L/G and Fuselage
(12) Refer to PRO-NOR-SOP-05 Exterior Walkaround - RH AFT Fuselage
(13) Refer to PRO-NOR-SOP-05 Exterior Walkaround - TAIL
(14) Refer to PRO-NOR-SOP-05 Exterior Walkaround - APU
(15) Refer to PRO-NOR-SOP-05 Exterior Walkaround - LH AFT Fuselage
(16) Refer to PRO-NOR-SOP-05 Exterior Walkaround - LH Landing Gear
(17) Refer to PRO-NOR-SOP-05 Exterior Walkaround - LH Wing Trailing Edge
(18) Refer to PRO-NOR-SOP-05 Exterior Walkaround - LH Wing Leading Edge
(19) Refer to PRO-NOR-SOP-05 Exterior Walkaround - ENG 1 LH Side
(20) Refer to PRO-NOR-SOP-05 Exterior Walkaround - ENG 1 RH Side
(21) Refer to PRO-NOR-SOP-05 Exterior Walkaround - LH Center Wing
Ident.: PRO-NOR-SOP-05-A-00010363.0001001 / 17 MAY 17
LH FWD FUSELAGE
AOA probes.................................................................................................................... CONDITION
F/O and CAPT static ports..................................................................................................... CLEAR
Avionics equipment vent air inlet valve.......................................................................... CONDITION
Oxygen bay.......................................................................................................................... CLOSED
Oxygen overboard discharge indicator.................................................................................. GREEN
Toilet servicing door ..................................................................................................... CLOSED
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-05 P 3/8
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - EXTERIOR WALKAROUND
Ident.: PRO-NOR-SOP-05-A-00010364.0001001 / 17 MAY 17
NOSE SECTION
Pitot probes.....................................................................................................................CONDITION
STBY static ports.................................................................................................................... CLEAR
TAT probes..................................................................................................................... CONDITION
Radome and latches..................................................................................... CONDITION/LATCHED
Forward avionics compartment door....................................................................................CLOSED
Ground electrical power door (if not required.)....................................................................CLOSED
Ident.: PRO-NOR-SOP-05-A-00010365.0001001 / 17 MAY 17
NOSE L/G
Nose wheel chocks............................................................................................................ IN PLACE
Wheels and tires.............................................................................................................CONDITION
Nose gear structure........................................................................................................ CONDITION
Taxi, TO, turn-off lights...................................................................................................CONDITION
Hydraulic lines and electrical wires................................................................................ CONDITION
Wheel well.............................................................................................................................. CHECK
Safety pin.......................................................................................................................... REMOVED
Ident.: PRO-NOR-SOP-05-A-00010366.0001001 / 17 MAY 17
RH FWD FUSELAGE
RH + AFT avionic compartment doors................................................................................ CLOSED
Avionic equipment vent air outlet valve..........................................................................CONDITION
F/O -CAPT static ports........................................................................................................... CLEAR
AOA probe...................................................................................................................... CONDITION
Forward cargo door and selector panel.................................................................................CHECK
Ident.: PRO-NOR-SOP-05-A-00010367.0001001 / 20 DEC 16
LOWER CENTER FUSELAGE
Potable water drain panel ............................................................................................ CLOSED
Antennas......................................................................................................................... CONDITION
Drain mast.......................................................................................................................CONDITION
Emergency ram air inlet flap.......................................................................................... CONDITION
LP and HP ground connection doors.................................................................................. CLOSED
Anticollision light..................................................................................................................... CHECK
CTR TK magnetic fuel level....................................................................................................FLUSH
Pack air intakes and outlets................................................................................................... CLEAR
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-05 P 4/8
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - EXTERIOR WALKAROUND
Ident.: PRO-NOR-SOP-05-A-00010368.0002001 / 17 MAY 17
RH CENTER WING
Yellow hydraulic bay door....................................................................................................CLOSED
Fuel panel.............................................................................................................................CLOSED
Inner tank magnetic fuel......................................................................................................... FLUSH
Fuel water drain valve inner tank....................................................................................... NO LEAK
Landing light....................................................................................................................CONDITION
Slat 1...............................................................................................................................CONDITION
Ident.: PRO-NOR-SOP-05-A-00010370.0015001 / 17 MAY 17
ENG 2 LH SIDE
Oil fill access door................................................................................................................CLOSED
Thrust reversers................................................................................................. CLOSED/LATCHED
Fan cowl doors................................................................................................... CLOSED/LATCHED
Drain mast......................................................................................................CONDITION/NO LEAK
Engine inlet and fan blades................................................................................................... CHECK
Ident.: PRO-NOR-SOP-05-A-00010371.0006001 / 17 MAY 17
ENG 2 RH SIDE
Vent inlet................................................................................................................................. CLEAR
Pressure-relief/Start valve handle access door................................................................... CLOSED
Thrust reversers................................................................................................. CLOSED/LATCHED
Fan cowl doors................................................................................................... CLOSED/LATCHED
Turbine exhaust ..................................................................................................................... CLEAR
Pylon/access panel......................................................................................... CONDITION/CLOSED
Ident.: PRO-NOR-SOP-05-A-00010372.0001001 / 17 MAY 17
RH WING LEADING EDGE
Slats 2, 3, 4, 5................................................................................................................ CONDITION
Inner and outer cells magnetic fuel level................................................................................FLUSH
Fuel water drain valve (outer cell, surge tank)................................................................... NO LEAK
Refuel coupling.....................................................................................................................CLOSED
Surge tank air inlet................................................................................................................. CLEAR
Fuel ventilation overpressure disc......................................................................................... INTACT
Navigation light.............................................................................................................. CONDITION
Wing tip........................................................................................................................... CONDITION
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-05 P 5/8
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - EXTERIOR WALKAROUND
Ident.: PRO-NOR-SOP-05-A-00010373.0001001 / 01 SEP 17
RH WING TRAILING EDGE
Static dischargers................................................................................................................... CHECK
Control surfaces..............................................................................................................CONDITION
Flaps and fairings........................................................................................................... CONDITION
ANTENNAS ON TOP OF FUSELAGE............................................................. CHECK CONDITION
Ident.: PRO-NOR-SOP-05-A-00010374.0001001 / 17 MAY 17
RH L/G AND FUSELAGE
Chocks.............................................................................................................................. REMOVED
Wheels and tires.............................................................................................................CONDITION
Brakes and brake wear ind............................................................................................ CONDITION
Torque link damper .................................................................................................CONDITION
Hydraulic lines........................................................................................................................ CHECK
Landing gear structure........................................................................................................... CHECK
Downlock springs................................................................................................................... CHECK
Safety pin.......................................................................................................................... REMOVED
Ground hydraulic connection yellow.................................................................................... CLOSED
Shroud fuel drain............................................................................................CONDITION/NO LEAK
Ident.: PRO-NOR-SOP-05-A-00010375.0001001 / 17 MAY 17
RH AFT FUSELAGE
RA Antennas...................................................................................................................CONDITION
Check that the RA antennas are clean.
Cargo door and selector panel.............................................................................................. CHECK
Bulk door ........................................................................................................................ CHECK
Toilet service access door................................................................................................... CLOSED
Outflow valve.................................................................................................................. CONDITION
Drain mast ..................................................................................................................... CONDITION
Flight recorder access door ................................................................................................ CLOSED
Ident.: PRO-NOR-SOP-05-A-00010376.0001001 / 17 MAY 17
TAIL
Stabilizer, elevator, fin, and rudder.................................................................................CONDITION
Static dischargers................................................................................................................... CHECK
Lower fuselage structure (tail impact on runway)...........................................................CONDITION
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-05 P 6/8
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - EXTERIOR WALKAROUND
Ident.: PRO-NOR-SOP-05-A-00010377.0001001 / 05 AUG 10
APU
Access doors........................................................................................................................CLOSED
Air intake......................................................................................................................... CONDITION
Drain...............................................................................................................CONDITION/NO LEAK
Oil cooler air outlet ................................................................................................................ CLEAR
Exhaust....................................................................................................................................CLEAR
Navigation light............................................................................................................... CONDITION
Fire extinguisher overpressure indication (red disc).......................................................... IN PLACE
Ident.: PRO-NOR-SOP-05-A-00010378.0001001 / 17 MAY 17
LH AFT FUSELAGE
Stabilizer, elevator, fin, and rudder.................................................................................CONDITION
Potable water service door.................................................................................................. CLOSED
Ground hydraulic connection blue door............................................................................... CLOSED
Ground hydraulic connection green and reservoir filling door............................................. CLOSED
Ident.: PRO-NOR-SOP-05-A-00010379.0001001 / 17 MAY 17
LH LANDING GEAR
Chocks.............................................................................................................................. REMOVED
Wheels and tires.............................................................................................................CONDITION
Brakes and brake wear indicator....................................................................................CONDITION
Torque link damper .................................................................................................CONDITION
Hydraulic lines........................................................................................................................ CHECK
Landing gear structure........................................................................................................... CHECK
Downlock springs................................................................................................................... CHECK
Safety pin.......................................................................................................................... REMOVED
Ident.: PRO-NOR-SOP-05-A-00010380.0001001 / 01 SEP 17
LH WING TRAILING EDGE
Flaps and fairing............................................................................................................. CONDITION
Control surfaces..............................................................................................................CONDITION
Static dischargers................................................................................................................... CHECK
ANTENNAS ON TOP OF FUSELAGE............................................................. CHECK CONDITION
Ident.: PRO-NOR-SOP-05-A-00010381.0001001 / 17 MAY 17
LH WING LEADING EDGE
Wing tip........................................................................................................................... CONDITION
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-05 P 7/8
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - EXTERIOR WALKAROUND
Navigation light............................................................................................................... CONDITION
Surge tank air inlet................................................................................................................. CLEAR
Fuel ventilation overpressure disc......................................................................................... INTACT
Fuel water drain valve........................................................................................................ NO LEAK
Inner and outer cell magnetic fuel level..................................................................................FLUSH
Slats 2, 3, 4, 5................................................................................................................ CONDITION
Ident.: PRO-NOR-SOP-05-A-00010384.0007001 / 17 MAY 17
ENG 1 LH SIDE
Oil fill access door................................................................................................................CLOSED
Thrust reversers................................................................................................. CLOSED/LATCHED
Fan cowl doors................................................................................................... CLOSED/LATCHED
Drain mast......................................................................................................CONDITION/NO LEAK
Engine inlet and fan blades................................................................................................... CHECK
Pylon/access panel......................................................................................... CONDITION/CLOSED
Ident.: PRO-NOR-SOP-05-A-00010386.0007001 / 17 MAY 17
ENG 1 RH SIDE
Vent inlet................................................................................................................................. CLEAR
Pressure relief/Start valve handle access door................................................................... CLOSED
Thrust reversers................................................................................................. CLOSED/LATCHED
Fan cowl doors................................................................................................... CLOSED/LATCHED
Turbine exhaust...................................................................................................................... CLEAR
Ident.: PRO-NOR-SOP-05-A-00010387.0001001 / 17 MAY 17
LH CENTER WING
Slat 1...............................................................................................................................CONDITION
Wing leading edge ventilation intake .............................................................................. CLEAR
Fuel water drain valves.......................................................................................................NO LEAK
Inner tank magnetic fuel......................................................................................................... FLUSH
Landing lights..................................................................................................................CONDITION
Hydraulic reservoir pressurization door............................................................................... CLOSED
RAT doors............................................................................................................................ CLOSED
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-NOR-SOP-05 P 8/8
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
INTRODUCTION
Ident.: PRO-NOR-SOP-06-00011153.0001001 / 20 MAR 17
Applicable to: ALL
Items marked by asterisks (*) are the only steps to be completed after a transit stop without flight
crew change. Otherwise, the new flight crew performs all the items.
The PF and PM should perform the cockpit preparation according to the panel scan sequence
defined below (Refer to Panel Scan Sequence), and the task sharing defined in the QRH (Refer to
QRH/Normal Procedures - Cockpit Preparation).
OVERHEAD PANEL
Applicable to: ALL
Ident.: PRO-NOR-SOP-06-A-00011155.0001001 / 31 JUL 13
WHITE LIGHTS ON THE OVERHEAD PANEL
During the scan sequence of the overhead panel:
* ALL WHITE LIGHTS.......................................................................................... EXTINGUISH
It is a general rule to turn off all the white lights during the scan sequence; therefore, these
actions are not listed here.
Ident.: PRO-NOR-SOP-06-A-00015476.0001001 / 12 APR 16
RCDR
* RCDR GND CTL pb-sw............................................................................................................ ON
In order to perform the test, ensure that the PARK BRK is on.
LOUDSPEAKER VOLUME knob....................................................................... OFF (BOTH SIDES)
ACP INT/RAD sw (CAPT and F/O)..................................................................................SET to INT
INTERPHONE VOLUME RECEPTION KNOB (CAPT and F/O)....................................... RELEASE
Turn down the volume to the minimum.
CVR TEST pb..............................................................................................PRESS AND MAINTAIN
The CVR test is successful when an audio test signal is heard through the loudspeakers and the
CVR TEST pb is pressed and maintained.
Depending on the CVR model, the audio test signal is:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
PRO-NOR-SOP-06 P 1/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
‐ For CVR 30 minutes:
‐ A continuous tone, or
‐ A short tone.
‐ For CVR 120 minutes:
‐ A short tone, or
‐ A short tone and a beep every 4 s, or
‐ Two short tones and a beep every 4 s.
The audio test signal stops when the CVR TEST pb is released.
Note:
‐ The flight crew may also hear an acoustic feedback (i.e. Larsen effect) during the test.
The test is still valid even if this acoustic feedback (i.e. Larsen effect) is heard.
‐ If the flight crew cannot hear the audio test signal through the loudspeakers, and if the
CVR maintenance headset (22RK headset) is available, the flight crew can perform
the CVR TEST through the CVR maintenance headset.
‐ If an acoustic feedback (i.e. Larsen effect) is still heard, the flight crew can perform
the CVR TEST using the 22RK headset and with the parking brake set to off. Before
setting the parking brake to off, the flight crew must ensure that chocks are in place or
brakes are applied. Set the parking brake to on when the CVR TEST is achieved.
Ident.: PRO-NOR-SOP-06-A-00011158.0001001 / 06 MAR 17
EVAC
CAPT & PURS/CAPT sw ..................................................................................................AS RQRD
Set the CAPT & PURS/CAPT sw on the EVAC panel as per Company Policy.
Ident.: PRO-NOR-SOP-06-A-00011159.0009001 / 17 MAR 17
*ADIRS
All IR MODE selector................................................................................................................. NAV
Align or realign IRS as appropriate. Refer to FCTM/PR-NP-SOP-60 ADIRS Operations.
L2
A complete IRS alignment must be performed in the following cases:
‐ Before the first flight of the day, or
‐ When there is a crew change, or
‐ When the GPS is not available and the NAVAIDS coverage is poor on the expected route, or
‐ When the GPS is not available and the expected flight time is more than 3 h.
A fast IRS alignment must be performed if a complete IRS alignment is not necessary.
To perform an alignment, the aircraft must be stopped on ground. Any aircraft movement will
automatically restart the IRS alignment.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-06 P 2/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
Do not align IRS during engine start, or while the engines are running.
Ident.: PRO-NOR-SOP-06-A-00011160.0001001 / 05 JAN 15
EXTERIOR LIGHTS
STROBE sw.............................................................................................................................. AUTO
BEACON sw................................................................................................................................ OFF
REMAINING EXTERIOR LIGHTS......................................................................................AS RQRD
Ident.: PRO-NOR-SOP-06-A-00011161.0001001 / 14 SEP 12
*SIGNS
* SIGNS sw....................................................................................................................... ON/AUTO
* EMER EXIT LT selector......................................................................................................... ARM
Note:
Leaving the EXIT selector or NO SMOKING selector or NO PORTABLE/ELEC DEVICE
selector ON prevents the emergency batteries from charging.
If the CIDS has been programmed (option) for a non-smoking flight, NO SMOKING or
NO PORTABLE/ELEC DEVICE signs are permanently on, with the EXIT sw or NO
SMOKING sw or NO PORTABLE/ELEC DEVICE sw at AUTO (with permanent
charge of emergency batteries).
Ident.: PRO-NOR-SOP-06-A-00010176.0001001 / 03 MAR 14
PROBE/WINDOW HEAT
PROBE/WINDOW HEAT pb....................................................................................... CHECK AUTO
Ident.: PRO-NOR-SOP-06-A-00011162.0001001 / 13 AUG 10
CABIN PRESS
LDG ELEV knob....................................................................................................................... AUTO
Ident.: PRO-NOR-SOP-06-A-00011163.0010001 / 20 SEP 16
*AIR COND
* PACK FLOW selector.................................................................................................... AS RQRD
Select:
LO
: If the number of occupants is below 141.
HI
: For abnormally hot and humid conditions.
NORM : For all other normal operating cases.
If the APU is supplying, pack controllers select HI flow automatically, independent of the selector
position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-06 P 3/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
Ident.: PRO-NOR-SOP-06-A-00011164.0001001 / 09 APR 15
ELEC
Scan and check that there are no amber lights, except GEN FAULT lights.
ELEC pb (on the ECAM Control Panel).................................................................................PRESS
BAT 1 pb-sw and BAT 2 pb-sw....................................................................................OFF then ON
This action initiates a charging cycle of the batteries.
10 s after setting all BAT pb-sw ON, check on the ELEC SD page that the current charge of the
battery is below 60 A, and is decreasing.
If the charge of at least one battery is not below 60 A:
Wait until the end of the charging cycle of the batteries and perform this check again.
Ident.: PRO-NOR-SOP-06-A-00011166.0002001 / 23 JUN 15
*FUEL
If the center tank is less than 200 kg (440 lb) for the flight:
Apply the following procedure, if your airline is affected by FUEL CTR TK PUMPS LO PR
cautions on ground or in flight when the center tank is less than 200 kg (440 lb):
FUEL MODE SEL pb-sw......................................................................................................MAN
CTR TK PUMP 1 pb-sw and CTR TK PUMP 2 pb-sw......................................................... OFF
If the center tank is NOT less than 200 kg (440 lb) for the flight:
CAUTION
If the FUEL MODE SEL pb is unduly left in the MAN position on ground, when
the CTR TK PUMP 1 pb & CTR TK PUMP 2 pb are not in the OFF position:
There is a possibility of fuel spillage, if there are any hidden failures.
FUEL MODE SEL pb........................................................................................... CHECK AUTO
Ident.: PRO-NOR-SOP-06-A-00011167.0001001 / 21 MAR 17
ENG 1 - ENG 2 FIRE
ENG 1 FIRE pb-sw and ENG 2 FIRE pb-sw ..........................................CHECK IN and GUARDED
AGENT 1 light and AGENT 2 light ...............................................................................CHECK OFF
ENG 1 TEST pb and ENG 2 TEST pb ........................................................ PRESS and MAINTAIN
For ENG FIRE TEST description,Refer to DSC-26-20-20 FIRE Panel
Ident.: PRO-NOR-SOP-06-A-00011169.0001001 / 14 SEP 12
AUDIO SWITCHING PANEL
AUDIO SWITCHING selector ................................................................................................. NORM
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-06 P 4/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
Ident.: PRO-NOR-SOP-06-A-00010185.0001001 / 26 MAY 14
VENT
ALL LIGHTS...................................................................................................................CHECK OFF
Ident.: PRO-NOR-SOP-06-A-00011174.0001001 / 14 SEP 12
THIRD OCCUPANT AUDIO CONTROL PANEL
PA knob ...............................................................................................................................RECEPT
‐ This allows cabin attendant announcements to be recorded on the CVR.
‐ For proper recording, set volume at or above medium range.
Ident.: PRO-NOR-SOP-06-A-00011176.0001001 / 14 SEP 12
MAINTENANCE PANEL
ALL LIGHTS...................................................................................................................CHECK OFF
CTR INSTRUMENT PANEL
Applicable to: ALL
Ident.: PRO-NOR-SOP-06-B-00011184.0001001 / 21 MAR 16
CTR INSTRUMENT PANEL - ISIS
* ISIS..................................................................................................................................... CHECK
‐ Adjust brightness, check IAS, altimeter readings, altimeter settings and attitude display.
‐ Check no flags - Reset attitude, if necessary.
Note:
Use of the ISIS bugs function is not recommended (Refer to DSC-34-NAV-20 Bugs
Function)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-NOR-SOP-06 P 5/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
Ident.: PRO-NOR-SOP-06-B-00011185.0009001 / 20 SEP 16
*CLOCK
CLOCK............................................................................................................................CHECK/SET
Note:
1. If the date is incorrect, set the date manually then set and keep the clock mode to
internal (INT) mode for the whole flight.
2. To comply with the time precision requirement (+/-1 s UTC) for ATC datalink
communication, the flight crew must either:
‐ Use the clock in GPS mode, or
‐ Use the clock in INT mode and synchronize the clock with the GPS at least one time
per day. This synchonization ensures that the UTC time drift is below +/- 1 s UTC.
For more information on the setting of the clock, Refer to DSC-31-55-10 General.
For more information on the use of the internal (INT) mode, Refer to DSC-31-55-20
Operation in Internal Mode.
Ident.: PRO-NOR-SOP-06-B-00011186.0001001 / 13 AUG 10
NOSEWHEEL STEERING
* A/SKID & N/W STRG sw.......................................................................................................... ON
PEDESTAL
Applicable to: ALL
Ident.: PRO-NOR-SOP-06-C-00011187.0001001 / 13 AUG 10
ACP
INT knob ..................................................................................... PRESS OUT / VOLUME CHECK
Make sure that INT volume is turned up to permit contact with the ground crew.
VHF ....................................................................................................................................... CHECK
Check transmission and reception.
HF (if required for flight).........................................................................................................CHECK
‐ Check transmission and reception.
‐ Do not transmit on HF during refueling.
Ident.: PRO-NOR-SOP-06-C-00011191.0001001 / 23 JUN 15
COCKPIT DOOR
If required by local Airworthiness Authorities:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
PRO-NOR-SOP-06 P 6/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
ANN LT selector........................................................................................................................ TEST
Check that the OPEN and FAULT lights (on the pedestal), and the three LED lights (on the
overhead panel) come on.
ANN LT selector.......................................................................................................................... BRT
Check that all lights go off.
CKPT DOOR.................................................................................CHECK CORRECT OPERATION
‐ Set the COCKPIT DOOR sw to the UNLOCK position. Check that the door opens, and that the
OPEN light comes on
‐ Then, with the door fully open, release the COCKPIT DOOR sw (check that it returns to NORM
position). Close the door. Check that it is locked, and that the OPEN Indication goes off.
CKPT DOOR MECHANICAL OVERRIDE............................................................................. CHECK
Check that the door opens normally, and that it closes when the mechanical override is used.
Ident.: PRO-NOR-SOP-06-C-00011189.0001001 / 14 SEP 12
SWITCHING PANEL
All selectors................................................................................................................CHECK NORM
Ident.: PRO-NOR-SOP-06-C-00011192.0001001 / 12 JUL 13
*ENG
* THRUST lever ....................................................................................................................... IDLE
* ENG MASTER sw .................................................................................................................. OFF
* ENG MODE selector............................................................................................................NORM
Ident.: PRO-NOR-SOP-06-C-00011195.0001001 / 06 SEP 16
*PARKING BRK
ACCU PRESS indicator......................................................................................................... CHECK
The ACCU PRESS indication must be in the green band. If required, use the electric pump on
yellow hydraulic system to recharge the brake accumulator.
WARNING
Yellow and green hydraulic systems are pressurized from yellow electric pump.
Get ground crew clearance before using the electric pump.
* PARK BRK handle..................................................................................................... CHECK ON
* BRAKES PRESS indicator................................................................................................. CHECK
Check for normal indications.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
PRO-NOR-SOP-06 P 7/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
If brakes are hot and chocks are in place:
PARK BRK handle ...............................................................................................................OFF
This action increases the brake cooling.
Ident.: PRO-NOR-SOP-06-C-00011198.0001001 / 07 FEB 11
GRAVITY GEAR EXTN
GRAVITY GEAR EXTN....................................................................................... CHECK STOWED
Ident.: PRO-NOR-SOP-06-C-00011199.0001001 / 21 MAR 17
ATC
* ATC ..................................................................................................................................... STBY
ATC and TCAS are on standby. To prevent possible interference to radar surveillance systems,
TCAS should not be selected before the holding point/lining up.
ALT RPTG ....................................................................................................................................ON
ATC SYS 1........................................................................................................................... SELECT
For RVSM operations (Refer to PRO-SPO-50 General), select SYS 1 if AP 1 is used, and SYS 2 if
AP 2 is used.
Only system 1 is available, in emergency electrical configuration.
RMP
Ident.: PRO-NOR-SOP-06-00011202.0001001 / 30 JUN 14
Applicable to: ALL
RMP..................................................................................................................................... CHECK ON
Green NAV light.................................................................................................................CHECK OFF
SEL light.............................................................................................................................CHECK OFF
COM FREQUENCIES................................................................................................................... TUNE
Use VHF 1 for ATC (only VHF 1 is available in emergency electrical configuration), VHF 2 for ATIS
and company frequencies. VHF 3 is normally devoted to ACARS.
ACARS
Ident.: PRO-NOR-SOP-06-00011224.0001001 / 24 SEP 14
Applicable to: ALL
* Initialize ACARS at that point or after FMGS PREPARATION, as per company policy.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to F
PRO-NOR-SOP-06 P 8/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
FMGS PREPARATION
Applicable to: ALL
Ident.: PRO-NOR-SOP-06-D-00011226.0001001 / 13 AUG 10
At electrical power-up, the FMGS s and FCU run through various internal tests. Allow enough time
(3 min) for tests’ completion, and do not start to press pushbuttons until the tests are over. If the
“PLEASE WAIT” message appears, do not press any MCDU key until the message clears.
Ident.: PRO-NOR-SOP-06-D-00011227.0001001 / 03 MAR 14
* ENGINE & AIRCRAFT TYPE................................................................................................ CHECK
Press the DATA key, and display the STATUS page (if not displayed).
Ident.: PRO-NOR-SOP-06-D-00011228.0001001 / 17 JUN 14
* FM database validity.............................................................................................................. CHECK
‐ Check DATA BASE validity and stored WPT /NAVAID S/RWY/ROUTES, if any.
If applicable, review the stored data for deletion decision.
‐ On Honeywell FMS , the double AIRAC cycle of the NDB has one day in common (AIRAC#1 day
28 / AIRAC#2 day1) (Refer to DSC-22_20-50-10-25 Aircraft Status Page).
If the CHECK DATA BASE CYCLE message triggers, the active database is no longer valid.
Therefore, on Day 28 of AIRAC Cycle #1, select AIRAC Cycle#2 prior to the first flight of the day.
Ident.: PRO-NOR-SOP-06-D-00011229.0001001 / 28 MAR 11
* NAVAID DESELECTION....................................................................................................AS RQRD
If NOTAMs warn of any unreliable DME or VOR /DME , display DATA, then POSITION MONITOR.
Access the SEL NAVAID page, and deselect the related NAVAID.
Ident.: PRO-NOR-SOP-06-D-00011231.0003001 / 20 AUG 12
* FLIGHT PLAN INITIALIZATION......................................................................................COMPLETE
‐ Press the INIT key
‐ Insert CO RTE or city pair, and check FROM/TO
‐ Check/modify ALTN /CO RTE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G→
PRO-NOR-SOP-06 P 9/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
‐ Enter flight number
Note:
For ATC needs, the crew should enter exactly the entire flight number, as shown on the
ICAO flight plan, without inserting any space, on the MCDU INIT page.
‐ Enter (and/or check) cost index
‐ Enter intended initial CRZ FL, or check if it was already supplied by the database.
Modify it, if necessary, taking into account ATC constraints or expected gross weight
‐ Check and modify CRZ FL TEMP and tropopause level to agree with forecast
‐ Enter (and/or check) the expected ground temperature for take off (GND TEMP)
‐ PRESS IRS INIT prompt
‐ Check alignment latitude/longitude.
Ident.: PRO-NOR-SOP-06-D-00011232.0001001 / 17 MAR 17
* ADIRS POSITION INITIALIZATION.................................................................... AS APPROPRIATE
Confirm or insert position coordinates for the IRS alignment. Refer to FCTM/PR-NP-SOP-60 FMGS
Preparation.
L2
IRS Alignment Based on GPS Position available:
The position initialization is automatic. The position for the initialization of the IRS is the GPS
position. However, the flight crew can manually override the automatic position initialization. The
IRS crosschecks the flight crew's manual entry with the GPS position.
IRS Alignment Based on GPS Position not available:
Apply the manual position initialization procedure.
Ident.: PRO-NOR-SOP-06-D-00011233.0015001 / 20 JUL 15
* F-PLN A page...........................................................................................COMPLETE AND CHECK
If CO RTE has been inserted, the F-PLN should automatically include the preferential or probable
takeoff runway approach and landing runway, associated SID s, STAR s, transition and en-route
waypoints. However some databases will only include departure and arrival airport IDENTs and
en-route waypoints.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
PRO-NOR-SOP-06 P 10/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
The flight crew must check, modify, or insert (as applicable) the F-PLN in the following order,
according to the data given by ATIS , ATC, or MET:
‐ Lateral revision at departure airport. Select RWY , then SID , then TRANS using scroll keys.
Note:
On the MCDU departure page, select only a runway associated with an ILS or NO
NAVAIDS.
‐ Lateral revision at WPT for ROUTE modification if needed. (Refer to DSC-22_20-30-10-05 Lateral
Revisions).
‐ Vertical revision. Check or enter climb speed limit, constraints according to ATC clearance. Enter
step altitude as appropriate.
* WINDS.................................................................................................................AS APPROPRIATE
Choose between using trip wind and the forecast wind for CLB , CRZ and DES phases.(Refer to
DSC-22_20-30-20-05 Flight Phases).
* F-PLN .................................................................................................................................... CHECK
‐ Check the F-PLN using F-PLN page and ND PLAN mode versus the computer (paper) flight plan
or navigation chart.
‐ Check DIST TO DEST along the F-PLN. Compare it with the total distance computed for the flight
with the computer (paper) flight plan.
Ident.: PRO-NOR-SOP-06-D-00011234.0001001 / 18 MAR 11
* SECONDARY FLIGHT PLAN............................................................................. AS APPROPRIATE
This is routinely a copy of the active flight plan. However, consideration may be given to the
following:
a. Copy the active F-PLN , but modify it at a suitable WPT for an immediate return to the departure
airfield in the event of, for example, engine failure
b. If weather is below landings minima at the departure airfield, the secondary flight plan should be
that required for a diversion immediately after takeoff
c. If there is a chance of a change in runway or SID during taxi, prepare for it by copying the active
flight plan and making the necessary modifications.
Ident.: PRO-NOR-SOP-06-D-00011235.0001001 / 10 JUN 16
* RADIO NAV............................................................................................................................CHECK
‐ Check the VOR , ILS / GLS / MLS , and ADF tuned by the FMGC
‐ Modify them if required, and check that the correct identifier is displayed on the ND and PFD (VOR
, ILS / GLS / MLS ). If unsatisfactory, go through the audio check. For GLS / MLS
, no audio check is necessary.
CAUTION
Do not enter an IDENT or channel associated with a GLS / MLS .
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
PRO-NOR-SOP-06 P 11/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
Ident.: PRO-NOR-SOP-06-D-00011238.0003001 / 20 MAR 17
GROSS WEIGHT INSERTION (INIT B PAGE);
* ZFW/ZFWCG..................................................................................................................... INSERT
* BLOCK FUEL.....................................................................................................................INSERT
If the LOADSHEET application is used, the PF enters the ZFWCG and ZFW as computed on his
EFB.
CAUTION
The characteristic speeds displayed on the MCDU (green dot, F, S, VLS )
are computed from the ZFW and ZFWCG entered by the crew on the MCDU.
Therefore, this data must be carefully checked (Captain’s responsibility).
‐ The flight crew should insert the weights after completing all other insertions. This is to avoid
cycles of prediction computations at each change in flight plan, constraints, etc.
‐ If ZFW and ZFWCG are unavailable, it is acceptable to enter the expected values in order to
obtain predictions. Similarly, the flight crew may enter the expected fuel on board, if refueling
has not been completed at that time.
‐ If ZFW , ZFWCG, and BLOCK FUEL are inserted, the FM will provide all predictions, as well as
the EXTRA fuel, if any.
Ident.: PRO-NOR-SOP-06-D-00011240.0001001 / 20 MAR 17
TAKEOFF DATA INSERTION (PERF TAKEOFF PAGE):
The PF inserts the takeoff data (computed on his EFB ) in the PERF TAKEOFF page of the
MCDU.
* V1 , VR , V2...................................................................................................................... INSERT
* FLX TO TEMP................................................................................................................... INSERT
* THR RED/ACC altitude......................................................................................... SET or CHECK
* ENG OUT ACC altitude.........................................................................................SET or CHECK
* FLAPS/THS reminder........................................................................................................ INSERT
* TO SHIFT....................................................................................................................... AS RQRD
Enter the takeoff SHIFT distance, if takeoff is to be from an intersection. This is essential for
position updating at takeoff and, consequently, for navigation accuracy.
* EFB / MCDU GREEN DOT.......................................................................................... COMPARE
Ident.: PRO-NOR-SOP-06-D-00011243.0001001 / 13 AUG 10
CLIMB, CRUISE, DESCENT, SPEED PRESELECTION
* PRESET SPEEDS..........................................................................................................AS RQRD
If the flight is cleared for a close-in turn or close-in altitude constraint, the flight crew may preselect
green dot speed on the PERF CLB page. Once the CLB phase is active, the preselected speed
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
PRO-NOR-SOP-06 P 12/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
will be displayed in the FCU speed window and on the PFD (blue symbol). Once the turn is
completed or the altitude cleared, the pilot will resume the managed speed profile by pressing the
SPD selector on the FCU.
Similarly the pilot may select a CRZ MACH number on the PERF CRZ page (constant CRZ Mach
segment, for example). When the CRZ phase is active, the preselected CRZ MACH number will
be displayed in the FCU speed window and on the PFD . When ECON MACH number may be
resumed, the crew presses the FCU SPD selector.
In either of the above cases, the pilot may cancel the CLB or CRZ preselected SPD /MACH prior
to activating the related phase, by selecting ECON on the PERF CLB or CRZ pages.
SPD LIM is defaulted to 250 kt below 10 000 ft in the managed speed profile. This may be either
cleared or modified on the VERT REV page at the origin (or a climb waypoint).
Ident.: PRO-NOR-SOP-06-D-00015496.0001001 / 20 MAR 17
CHECK OF FMGS PREPARATION:
* FMS PREPARATION......................................................................................................... CHECK
After the PF prepared the FMS , the PM checks:
‐ The airfield data.
‐ All FMS entered data.
‐ The takeoff performance data with the data computed on his EFB.
GROSS WEIGHT INSERTION.................................................................... CHECK/CROSSCHECK
If the LOADSHEET application is used, the PM checks the ZFWCG and ZFW that the PF has
entered in the FMGS with the loadsheet data computed on PM 's EFB.
TAKEOFF DATA INSERTION...................................................................................CROSSCHECK
The PM crosschecks the takeoff data that the PF has entered in the FMGS , with the takeoff data
computed on PM 's EFB using the TAKEOFF application.
EFB /MCDU GREEN DOT............................................................................................... COMPARE
The PM compares Green Dot speed computed by the FMGS and the Green Dot speed computed
using the TAKEOFF application. A discrepancy indicates a difference in the TOW used in both
systems (EFB /FMGS).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-NOR-SOP-06 P 13/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
GLARESHIELD
Applicable to: ALL
Ident.: PRO-NOR-SOP-06-E-00020832.0001001 / 17 MAR 17
*EFIS CONTROL PANEL
* BAROMETRIC REFERENCE.................................................................................................. SET
‐ Set QNH (or QFE ) on the EFIS control panel and on the standby altimeter
‐ Check the barometric reference and altitude indications on the PFDs and on the standby
altimeter.
The maximum difference is:
±20 ft between both PFDs
And depending on the aircraft configuration:
±60 ft between ISIS and PFDs, or
±300 ft between mechanical standby altimeter and PFDs.
* FD................................................................................................................................ CHECK ON
* ILS/LS............................................................................................................................. AS RQRD
* ND MODE and RANGE ................................................................................................AS RQRD
* ADF/VOR sw .................................................................................................................AS RQRD
Display VOR and ADF pointers as needed.
Ident.: PRO-NOR-SOP-06-E-00011248.0001001 / 24 SEP 14
*FCU
* SPD MACH window......................................................................................................... DASHED
* HDG V/S -TRK FPA pb................................................................................................... HDG V/S
* ALT window..................................................................... INITIAL EXPECTED CLEARANCE ALT
Note:
Do not engage the autothrust on ground, as it may generate the AUTO FLT A/THR OFF
warning at engine start.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
PRO-NOR-SOP-06 P 14/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
LATERAL CONSOLES
Ident.: PRO-NOR-SOP-06-00011249.0002001 / 23 JUN 15
Applicable to: ALL
OXYGEN MASK TEST
WARNING
To prevent hearing damage to ground mechanics connected to the intercom
system, inform them that a loud noise may be heard in the headset when
performing this test.
On the OXYGEN panel:
CREW SUPPLY pb......................................................................................................... CHECK ON
On the glareshield:
LOUDSPEAKERS..........................................................................................................................ON
On the audio control panel:
INT reception knob......................................................................................... PRESS OUT-ADJUST
INT/RAD sw...................................................................................................................................INT
On the mask stowage box:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I→
PRO-NOR-SOP-06 P 15/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
‐ Press and hold the reset/test button in the direction of the arrow.
• Check that the blinker turns yellow for a short time, and then goes black.
‐ Hold the reset/test button down, and press the emergency pressure selector.
• Check that the blinker turns yellow and remains yellow, as long as the emergency pressure
selector is pressed.
• Listen for oxygen flow through the loudspeakers. Warn any engineer, whose headset may be
connected to the nose intercom, that a loud noise may be heard when performing this check.
‐ Check that the reset/test button returns to the up position and the N 100 % selector is in the
100 % position.
‐ Press the emergency pressure selector again, and check that the blinker does not turn yellow.
This ensures that the mask is not supplied.
On the ECAM DOOR/OXY page:
REGUL LO PR message...............................................................................................CHECK OFF
The crew must perform this check after having checked all masks. It ensures that the LP valve is
open, (due to residual pressure between the LP valve and the oxygen masks, an LP valve failed in
the closed position may not be detected during the oxygen mask test).
INSTRUMENT PANELS
Ident.: PRO-NOR-SOP-06-00011252.0001001 / 17 MAR 16
Applicable to: ALL
PFD and ND brightness knob................................................................................................AS RQRD
Check the ND outer ring is set to maximum brightness (radar/terrain display).
LOUDSPEAKER knob .................................................................................................................... SET
Set the LOUDSPEAKER knob around the 1 o’clock position.
* PFD.........................................................................................................................................CHECK
‐ Check PFD /ND not transferred.
‐ Check for correct display, when ATT and HDG are available.
‐ Check IAS , FMA , initial target ALT , altimeter readings, VSI, altimeter settings, heading and
attitude display.
* ND...........................................................................................................................................CHECK
‐ Check for correct display.
‐ Crosscheck compass indication on the ND and DDRMI.
‐ Check heading, initial waypoint, VOR ADF indications.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← I to J
PRO-NOR-SOP-06 P 16/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
ECAM CONTROL PANEL
Ident.: PRO-NOR-SOP-06-00011190.0001001 / 24 FEB 15
Applicable to: ALL
*ECAM CONTROL PANEL
* PRESS pb ......................................................................................................................... PRESS
Check that the CAB PRESS page displays LDG ELEV AUTO, to confirm the correct position of the
LDG ELEV knob.
* STS pb ...............................................................................................................................PRESS
Check that INOP SYS display is compatible with MEL.
If a message is displayed in MAINTENANCE STATUS, Refer to MMEL/MI-00-08 ECAM and
MAINTENANCE STATUS.
ADIRS
Ident.: PRO-NOR-SOP-06-00011253.0002001 / 20 MAR 17
Applicable to: ALL
* IRS ALIGN..............................................................................................................................CHECK
On the POSITION MONITOR page, check that the IRS are in NAV mode, and check that the
distance between each IRS and the FMS position is lower than 5 NM. Select ND in ROSE-NAV or
ARC mode, and confirm that the aircraft position is consistent with the position of the airport, the SID
and the surrounding NAVAIDs.
NAV CHARTS CLIPBOARD..................................................................................................PREPARE
TAKEOFF BRIEFING
Ident.: PRO-NOR-SOP-06-00011256.0001001 / 20 MAR 17
Applicable to: ALL
* TAKEOFF BRIEFING........................................................................................................PERFORM
PC DEDICATED TO MAINTENANCE
Ident.: PRO-NOR-SOP-06-00011258.0001001 / 07 FEB 11
Applicable to: ALL
Check that the Personal Computer (PC) dedicated to maintenance use and located in front of lower
stowage at RH rear corner is stowed.
Check that the light of its manual switch is off. If not, switch it off.
Check that its associated printer located in front of RH rear of the cockpit is stowed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
K to N
PRO-NOR-SOP-06 P 17/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - COCKPIT PREPARATION
FLOW PATTERN
Ident.: PRO-NOR-SOP-06-00020280.0001001 / 17 MAR 17
Applicable to: ALL
COCKPIT PREPARATION - FLOW PATTERN
The scan pattern varies, depending on the pilot status, i.e PF , PM , CM1 , or CM2, and the areas
of responsibility:
1. Overhead panel
2. Center instrument panel
3. Pedestal
4. FMGS preparation, and when both pilots are seated:
5. Glareshield
6. Lateral consoles and CM1/CM2 panels.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
O
PRO-NOR-SOP-06 P 18/18
12 APR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES
- BEFORE PUSHBACK OR START
FLIGHT CREW
OPERATING MANUAL
BEFORE START CLEARANCE
Applicable to: ALL
Ident.: PRO-NOR-SOP-07-A-00021624.0001001 / 19 APR 17
LOADSHEET
FINAL LOADSHEET...............................................................................................................CHECK
Both crew members carefully check the Load and Trim Sheet (LTS), particularly for gross errors.
Make sure that the load sheet data is correct (e.g correct flight, correct aircraft, dry operating
index, configuration, Fuel on Board,etc.).
ZFW /ZFWCG.......................................................................................................... CHECK/REVISE
The PF compares the ZFW and the ZFWCG with the previously-entered data, and adjust if
necessary.
ZFW /ZFWCG............................................................................................................CROSSCHECK
The PM crosschecks the ZFW and the ZFWCG entered in the FMS
Check that the takeoff CG is within LTS operational limits.
FINAL LOADSHEET (CM1)................................................................................ SIGN and EXPORT
If the loadsheet is modified, or if required by the authorities or by the airline policy, the CM1 sends
the loadsheet to the ground via the EXPORT function on the LOADSHEET application.
Ident.: PRO-NOR-SOP-07-A-00011255.0009001 / 09 JUN 15
FOB............................................................................................................................................ CHECK
‐ Check that ECAM fuel on board corresponds to the F-PLN.
‐ Check that fuel imbalance is within limits.
‐ Crosscheck that the sum of the Fuel On Board (FOB ) recorded at the end of the last flight and
the fuel uplift (if any) is consistent with the current FOB. If an abnormal discrepancy is found, a
maintenance action is due.
FOB after refuelling:
Up to 6 tons (13200 lb)
Between 6 tons (13200 lb) and 12 tons (26500 lb)
More than 12 tons (26500 lb)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
Abnormal discrepancy above:
400 kg (900 lb)
500 kg (1100 lb)
600 kg (1300 lb)
PRO-NOR-SOP-07 P 1/6
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES
- BEFORE PUSHBACK OR START
Ident.: PRO-NOR-SOP-07-A-00010189.0002001 / 20 MAR 17
TAKEOFF DATA
FINAL TAKEOFF DATA........................................................................ CONFIRM or RECOMPUTE
‐ If takeoff conditions did not change, verify and confirm that the preliminary takeoff data are still
valid
‐ If takeoff conditions have changed, calculate the final takeoff performance, using the T.O. PERF
application on the EFB.
FMS TAKEOFF DATA............................................................................CHECK/REVISE AS RQRD
The PF checks (or revises) the takeoff data on the INIT B and PERF pages of the MCDU.
REVISED FMS TAKEOFF DATA..............................................................................CROSSCHECK
The PM crosschecks the takeoff data on the MCDU (i.e. weights, speeds, flexible temperature,
takeoff configuration), with the PM 's EFB takeoff data.
EFB /MCDU GREEN DOT............................................................................................... COMPARE
The PM compares Green Dot speed computed by the FMGS and the Green Dot speed computed
using the TAKEOFF application. A discrepancy indicates a difference in the TOW used in both
systems (EFB /FMGS).
Ident.: PRO-NOR-SOP-07-A-00010190.0001001 / 04 MAR 14
SEATING POSITION
SEATING POSITION............................................................................................................ ADJUST
The seat is correctly adjusted, when the pilot’s eyes are in line with the red and white balls.
Ident.: PRO-NOR-SOP-07-A-00010192.0001001 / 23 DEC 14
MCDU
FMS PERF TO page............................................................................................................ SELECT
It is recommended to display the PERF TO page on the PF side.
FMS F-PLN page..................................................................................................................SELECT
It is recommended to display the F-PLN page on the PM side
Ident.: PRO-NOR-SOP-07-A-00010193.0001001 / 17 MAR 16
ELEC
EXT PWR....................................................................................................................CHECK AVAIL
WARNING
Disconnection of the external power with the EXT PWR pb-sw ON may cause
injury to the ground engineer. Request disconnection of the external power only
with the EXT PWR pb-sw AVAIL.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-07 P 2/6
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES
- BEFORE PUSHBACK OR START
FLIGHT CREW
OPERATING MANUAL
EXT PWR DISCONNECTION........................................................................................... REQUEST
Ident.: PRO-NOR-SOP-07-A-00021505.0001001 / 20 MAR 17
EFB/eQRH transmitting mode............................................................................................. CONSIDER
In accordance with the Operator's policy or, as required by operational regulations.
Ident.: PRO-NOR-SOP-07-A-00010194.0001001 / 12 FEB 13
BEFORE START CHECKLIST DOWN TO THE LINE
BEFORE START CHECKLIST down to the line.............................................................COMPLETE
AT START CLEARANCE
Applicable to: ALL
Ident.: PRO-NOR-SOP-07-B-00010197.0001001 / 04 MAR 14
PUSHBACK/START UP CLEARANCE
PUSHBACK/START CLEARANCE....................................................................................... OBTAIN
Obtain ATC pushback/startup clearance.
Obtain ground crew clearance.
Ident.: PRO-NOR-SOP-07-B-00015568.0001001 / 20 JAN 15
ATC...................................................................................................................SET FOR OPERATION
ATC is set in accordance with airport requirements.
Ident.: PRO-NOR-SOP-07-B-00010199.0002001 / 04 MAR 14
WINDOWS AND DOORS
WINDOWS and DOORS........................................................................................ CHECK CLOSED
‐ To ensure that the sliding window is correctly closed and locked, push the handle of the sliding
window fully forward to the closed position, and check that the red indicator is visible
‐ Check, on the ECAM lower display, that all the aircraft doors are closed
‐ When required by local airworthiness authorities, check that the cockpit door is closed and
locked (no cockpit door open/fault indication).
If entry is requested, identify the person requesting entry before unlocking the door. With the
cockpit door sw on NORM, the cockpit door is closed and locked. If entry is requested from the
cabin, and if no further action is performed by the pilot, the cabin crew will be able to unlock the
door by using the emergency access procedure. Except for crew entry/exit, the cockpit door
should remain closed until engine shutdown.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
PRO-NOR-SOP-07 P 3/6
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES
- BEFORE PUSHBACK OR START
SLIDES.....................................................................................................................CHECK ARMED
‐ Check, on the ECAM lower display, that all slides are armed.
Ident.: PRO-NOR-SOP-07-B-00010200.0001001 / 04 MAR 14
EXTERIOR LIGHTS
BEACON sw.................................................................................................................................. ON
Ident.: PRO-NOR-SOP-07-B-00010201.0001001 / 04 MAR 14
THRUST LEVERS
THRUST LEVERS...................................................................................................................... IDLE
CAUTION
Engines will start, regardless of the thrust lever position; thrust will rapidly
increase to the corresponding thrust lever position, causing a hazardous situation,
if thrust levers are not at IDLE.
Ident.: PRO-NOR-SOP-07-B-00016807.0001001 / 06 SEP 16
ACCU PRESSURE
ACCU PRESS indicator......................................................................................................... CHECK
The ACCU PRESS indication must be in the green band. If required, use the electric pump on
yellow hydraulic system to recharge the brake accumulator.
WARNING
Yellow and green hydraulic systems are pressurized from yellow electric pump.
Get ground crew clearance before using the electric pump.
Ident.: PRO-NOR-SOP-07-B-00010202.0002001 / 24 NOV 15
PARKING BRAKE AND NOSEWHEEL STEERING
If pushback is not required:
PARK BRK handle................................................................................................... CHECK ON
BRAKES PRESS indicator.............................................................................................. CHECK
Check for normal indications.
BEFORE START CHECKLIST below the line..........................................................COMPLETE
Ident.: PRO-NOR-SOP-07-B-00010198.0002001 / 21 MAR 17
If pushback is required:
N/W STRG DISC MEMO............................................................................... CHECK DISPLAYED
In case of pushback (conventional or towbarless), the nosewheel steering selector bypass pin
must be in the tow position. The ECAM’s NW STRG DISC, or N WHEEL STEERG DISC memos
indicate this to the flight crew.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-07 P 4/6
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CAUTION
STANDARD OPERATING PROCEDURES
- BEFORE PUSHBACK OR START
If the ECAM does not display the N WHEEL STEERG DISC memo, but the
ground crew confirms that the tow pin is in the towing position, the flight crew
should not start the engine during pushback. This is to avoid possible nose
landing gear damage upon yellow hydraulic pressurization.
To dispatch the aircraft in such a case, Refer to MMEL/MI-32-51 NWS Electrical
Deactivation Box.
In case of a powerpush by the main landing gear, the nosewheel steering selector should remain
in the normal position to steer the aircraft (Refer to PRO-NOR-SUP-MISC-D Pushback with
Power Push Unit via the Main Landing Gear - Procedure 1/2).
BEFORE START CHECKLIST below the line............................................................. COMPLETE
PARK BRK handle ...................................................................................................................OFF
CAUTION
Do not use the brakes during pushback, unless required due to an emergency.
When pushback is completed:
PARK BRK handle ..............................................................................................................ON
BRAKE PRESS indicator.............................................................................................. CHECK
Check for normal indications.
Ask the ground crew for towbar disconnection.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-NOR-SOP-07 P 5/6
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES
- BEFORE PUSHBACK OR START
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SOP-07 P 6/6
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - ENGINE START
AUTOMATIC ENGINE START
Ident.: PRO-NOR-SOP-08-00010162.0060001 / 31 AUG 17
Applicable to: ALL
Use the automatic engine start procedure in most circumstances. However, if the start aborts due
to insufficient starter inlet air pressure (e.g. on high airfields, or in case of low pressure from an
external pneumatic power group), it is recommended to use the manual start procedure, instead the
automatic procedure.
If, during the engine start, the ground crew reports a fuel leak from the engine drain mast, run the
engine at idle for 5 min. If the leak disappears during these 5 min, the aircraft can be dispatched
without maintenance action. If the leak is still present after 5 min, shut down the engine and request
the maintenance personnel to investigate the leakage source.
ENG MODE selector .......................................................................................................... IGN/START
The lower ECAM displays the ENG SD page.
ENGINE 2 START..............................................................................................................ANNOUNCE
Engine 2 is usually started first. It powers the yellow hydraulic system, that pressurizes the parking
brake.
ENG MASTER 2................................................................................................................................ON
‐ Do not set the ENG MASTER 2 lever to ON before all amber crosses and messages have
disappeared on the engine parameters (upper ECAM display).
‐ Parameter callouts are not mandatory.
‐ In case the electrical power supply is interrupted during the start sequence (indicated by the loss
of ECAM DUs), abort the start by setting to OFF the ENG MASTER 2 lever. Then, perform a 30 s
dry crank.
N2 increases
ON ECAM UPPER DISPLAY
At 16 % N2
ON ECAM LOWER DISPLAY
Corresponding start valve in line.
Bleed pressure indication green.
Oil pressure increases.
Indication of the active igniter (A or B).
At 22 % N2
‐ FF increases
15 s (maximum) after fuel is on
‐ EGT increases
‐ N1 increases
At 50 % N2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Start valve starts closing. (It is fully closed between 50 %
and 56 % N2).
Igniter indication off.
A→
PRO-NOR-SOP-08 P 1/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - ENGINE START
When idle is reached (AVAIL indication is displayed):
ENG IDLE PARAMETERS.................................................................................................. CHECK
At ISA sea level : N1 about 19.5 %
N2 about 58.5 %
EGT about 390 °C
FF about 275 kg/h (600 lb/h)
Grey background on N2 indication disappears.
ENGINE 1 START....................................................................................................... ANNOUNCE
ENG MASTER 1......................................................................................................................... ON
Same procedure as for engine 2.
Both pack valves reopen with 30 s delay after the second engine N2 is above 50 %.
Note:
A PTU FAULT is triggered, if the last engine is started within 40 s following the end of
the cargo doors operation. Refer to PRO-ABN-HYD HYD PTU FAULT.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SOP-08 P 2/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - ENGINE START
GROUND RUN UP - DANGER AREAS
Ident.: PRO-NOR-SOP-08-00010163.0006001 / 06 JAN 16
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PRO-NOR-SOP-08 P 3/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - ENGINE START
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SOP-08 P 4/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - AFTER START
AFTER START
Applicable to: ALL
Ident.: PRO-NOR-SOP-09-A-00010210.0002001 / 21 MAR 17
ENG MODE
ENG MODE selector .............................................................................................................. NORM
For additional information on the automatic starting sequence, Refer to DSC-70-80-40 Sequence
of the Automatic Start.
After start, to avoid thermal shock, the pilot should operate the engine at idle or near idle for at
least 2 min before advancing the thrust lever to high power. Taxi time at idle may be included in
the warm-up period.
The last engine started must run for at least 2 min before takeoff initiation, to ensure that takeoff
is not initiated before the center tank pumps test is finished, since takeoff on center tank is
prohibited.
Ident.: PRO-NOR-SOP-09-A-00010211.0001001 / 26 OCT 12
APU BLEED
APU BLEED pb-sw......................................................................................................................OFF
‐ This action enables to avoid ingestion of engine exhaust gases.
‐ APU BLEED valve closes, ENG BLEED valves open.
Ident.: PRO-NOR-SOP-09-A-00010212.0005001 / 17 MAR 17
ANTI-ICE
CAUTION
In icing conditions (Refer to LIM-ICE_RAIN Definition of Icing Conditions), the
flight crew must turn on the engine anti-ice and should not wait until seeing ice
building up.
ENG ANTI-ICE pb-sw ....................................................................................................... AS RQRD
Engine anti-ice must be set to ON during all ground operation, when icing conditions exist or are
anticipated.
During ground operation, when in icing conditions for more than 30 min, the following procedure
should be applied for ice shedding :
CAUTION
If, during thrust increase, the aircraft starts to move, immediately retard the thrust
levers to IDLE.
If ground surface conditions and the environment permit, the flight crew should accelerate the
engines to approximately 70 % of N1 for 30 s at intervals not greater than 30 min.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SOP-09 P 1/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - AFTER START
In addition, this engine acceleration should also be performed just before take-off, with particular
attention to engine parameters to ensure normal engine operation. If ground surface or
environment do not permit to accelerate the engine to 70 % N1, then power setting and dwell time
should be as high as practical.
When operating in conditions of freezing rain, freezing drizzle, freezing fog or heavy snow, ice
shedding may be enhanced, by additional run ups at intervals, to not exceed 10 min, advancing
throttles to 70 % N1 momentarily (no hold time).
Ident.: PRO-NOR-SOP-09-A-00010213.0001001 / 21 MAR 17
WING ANTI-ICE pb-sw.......................................................................................................... AS RQRD
When icing conditions are encountered:
‐ The flight crew may turn on the wing anti-ice to prevent ice accretion on the wing leading edge.
‐ The flight crew must turn on the wing anti-ice if there is evidence of ice accretion, such as ice on
the visual indicator, or on the wipers, or with the SEVERE ICE DETECTED alert. This is to
remove any ice accumulation from the wing leading edge.
Ident.: PRO-NOR-SOP-09-A-00010214.0001001 / 04 MAR 14
APU
If the APU is not required:
APU MASTER SW................................................................................................................OFF
Ident.: PRO-NOR-SOP-09-A-00010215.0001001 / 26 OCT 12
GROUND SPOILERS
GROUND SPOILERS................................................................................................................. ARM
Ident.: PRO-NOR-SOP-09-A-00010216.0001001 / 26 OCT 12
RUDDER TRIM
RUD TRIM position indication.....................................................................................CHECK ZERO
If the RUD TRIM position indication is not at zero:
RESET pb........................................................................................................................ PRESS
Note:
After the reset, the flight crew may observe an indication of up to 0.3 ° (L or R) in the
RUD TRIM position indication.
Ident.: PRO-NOR-SOP-09-A-00010217.0001001 / 26 OCT 12
FLAPS
FLAPS lever...................................................................................................... SET FOR TAKEOFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-09 P 2/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - AFTER START
FLAPS.................................................................................................................. CHECK POSITION
Check the position of the flaps on the ECAM upper display.
If taxiing in icing conditions with rain, slush or snow:
Maintain the flaps retracted until the aircraft reaches the holding point of the takeoff runway.
This action prevents contamination of the slats/flaps mechanism.
Ident.: PRO-NOR-SOP-09-A-00010218.0001001 / 26 OCT 12
PITCH TRIM
PITCH TRIM handwheel..............................................................................................................SET
Set takeoff CG on pitch trim handwheel.
Ident.: PRO-NOR-SOP-09-A-00010220.0001001 / 01 DEC 14
ECAM STATUS
STATUS REMINDER............................................................................... CHECK NOT DISPLAYED
If STS reminder is displayed:
STS pb............................................................................................................................. PRESS
Review the ECAM Status page.
Ident.: PRO-NOR-SOP-09-A-00015495.0001001 / 23 JUN 15
N/W STEER DISC MEMO
N/W STEER DISC MEMO....................................................................... CHECK NOT DISPLAYED
Ident.: PRO-NOR-SOP-09-A-00010221.0001001 / 05 NOV 15
GROUND CREW
CLEAR TO DISCONNECT.............................................................................................ANNOUNCE
The ground crew:
‐ Removes the chocks
‐ Disconnects the interphone
‐ Makes the hand signal on the left or right side.
Ident.: PRO-NOR-SOP-09-A-00010222.0001001 / 26 OCT 12
AFTER START CHECKLIST
AFTER START CHECKLIST.......................................................................................... COMPLETE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-09 P 3/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - AFTER START
Ident.: PRO-NOR-SOP-09-A-00020074.0001001 / 17 MAR 17
AFTER START - FLOW PATTERN
When the engines have started, the PF sets the ENG MODE selector to NORM to permit normal
pack operation. At this time, the After Start Flow Pattern begins.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SOP-09 P 4/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - TAXI
TAXI
Applicable to: ALL
Ident.: PRO-NOR-SOP-10-A-00010226.0001001 / 15 MAY 13
TAXI CLEARANCE
TAXI clearance...................................................................................................................... OBTAIN
Ident.: PRO-NOR-SOP-10-A-00010227.0001001 / 21 MAR 17
EXTERIOR LIGHTS
NOSE sw.....................................................................................................................................TAXI
When crossing a runway:
STROBE sw............................................................................................................................ ON
L2
RWY TURN OFF & CAMERA sw ......................................................................................... ON
The PF may ask the PM to set the exterior lights.
Ident.: PRO-NOR-SOP-10-A-00010228.0001001 / 15 MAY 13
PARK BRK
PARK BRK handle.......................................................................................................................OFF
BRAKES PRESSURE........................................................................................... CHECK AT ZERO
The flight crew may observe slight residual pressure on the triple indicator for a short period of
time.
Ident.: PRO-NOR-SOP-10-A-00010230.0001001 / 19 APR 17
THRUST LEVER
THRUST lever ...................................................................................................................AS RQRD
The flight crew will need a little power above idle thrust to move the aircraft.
L2
For additional information on the thrust use during taxi, Refer to FCTM/PR-NP-SOP-100 Taxi Roll
and Steering.
Ident.: PRO-NOR-SOP-10-A-00010231.0002001 / 17 MAR 17
BRAKES
CAUTION
If the aircraft was parked in wet conditions for a long time, the first brake
application at low speed is less effective.
BRAKE PEDALS.....................................................................................................................PRESS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SOP-10 P 1/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - TAXI
BRAKES ................................................................................................................................ CHECK
If an arc is displayed above the brake temperature on the WHEEL SD page, set the brake fans
to ON.
L2
For more information, Refer to FCTM/PR-NP-SOP-100 Brake Check.
Ident.: PRO-NOR-SOP-10-A-00016023.0001001 / 17 MAR 17
NOSEWHEEL STEERING
L2
TILLER or RUDDER PEDALS.................................................................................. USE AS RQRD
For information on the nosewheel steering limitation, Refer to FCTM/PR-NP-SOP-100 Taxi Roll
and Steering.
Ident.: PRO-NOR-SOP-10-A-00010243.0001001 / 22 MAR 17
FLIGHT CONTROLS
L2
FLIGHT CONTROLS..............................................................................................................CHECK
For additional information on the flight controls check, Refer to FCTM/PR-NP-SOP-100 Flight
Controls.
Ident.: PRO-NOR-SOP-10-A-00010244.0001001 / 15 MAY 13
ATC CLEARANCE
ATC clearance....................................................................................................................CONFIRM
Ident.: PRO-NOR-SOP-10-A-00010248.0001001 / 20 MAR 17
TAKEOFF DATA/CONDITIONS
If the takeoff data has changed, or in the case of a runway change, prepare updated takeoff:
FINAL TAKEOFF DATA........................................................................ CONFIRM or RECOMPUTE
If takeoff conditions changed, the PF and the PM independently compute again the takeoff data.
FMS TAKEOFF DATA............................................................................CHECK/REVISE AS RQRD
If takeoff conditions changed, the PF revises the takeoff data in the FMS.
REVISED FMS TAKEOFF DATA..............................................................................CROSSCHECK
The PM crosschecks the takeoff data entered by the PF on the MCDU (i.e. weights, speeds,
flexible temperature, takeoff configuration), with the PM 's EFB takeoff data.
EFB/MCDU GREEN DOT.................................................................................................COMPARE
The PM compares Green Dot speed computed by the FMGS and the Green Dot speed computed
using the TAKEOFF application. A discrepancy indicates a difference in the TOW used in both
systems (EFB /FMGS).
F-PLN (Runway).................................................................................................................... REVISE
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OPERATING MANUAL
STANDARD OPERATING PROCEDURES - TAXI
FLAPS lever ....................................................................................................... AS APPROPRIATE
Select takeoff position.
V1 , VR , V2..................................................................................................................... REINSERT
FLX TO temperature.........................................................................................................REINSERT
Ident.: PRO-NOR-SOP-10-A-00015301.0001001 / 17 MAR 17
AFS/FLIGHT INSTRUMENTS
L2
F-PLN (SID ,TRANS).......................................................................................... REVISE or CHECK
Carefully confirm that the ATC clearance agrees with the FMS , if NAV mode is to be used.
INITIAL CLIMB SPEED AND SPEED LIMIT...................................................... MODIFY or CHECK
Use VERT REV at departure, or at a CLB waypoint.
CLEARED ALTITUDE ON FCU ................................................................................................. SET
HDG ON FCU ............................................................................................IF REQUIRED, PRESET
If a heading is required by the ATC after takeoff, in case of a radar vector departure, preset the
heading on the FCU . NAV mode will be disarmed.
RWY TRK mode will keep the aircraft on the runway track.
BOTH FD ........................................................................................................................CHECK ON
PFD /ND ................................................................................................................................CHECK
TAKEOFF BRIEFING.........................................................................................................CONFIRM
For additional information on the takeoff briefing confirmation, Refer to FCTM/PR-NP-SOP-100
Takeoff Briefing Confirmation.
Ident.: TDU / PRO-NOR-SOP-10-A-00015299.0002001 / 03 AUG 17
Impacted DU: 00015298 Taxi - Radar
RADAR.............................................................................................................................................. ON
To check the radar and the departure path, set the MULTISCAN sw to MAN. The flight crew can then
set the radar to the AUTO position.
Gain must be manually set to +4, when MULTISCAN selector is set to AUTO and when flying below
FL 200.
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FLIGHT CREW
OPERATING MANUAL
Note:
STANDARD OPERATING PROCEDURES - TAXI
1. If the weather is good, or not significant, in order to check that the radar is operating
correctly: down tilt until displaying ground echoes
2. If the weather display is ambiguous or unexpected, in order to better analyze the weather
situation, use manual tilt according to standard technique.
3. In particular below FL 200, for situations with low-level weather, weather with low
reflectivity or in front of suspected active cells, the flight crew should switch to Manual
mode and adjust the tilt setting downward until the weather is detected or the ground
clutter appears on the upper part of the display.
4. In addition, the flight crew may increase the manual gain control to display lower
reflectivity targets. The manual gain control can be increased in both AUTO and Manual
modes to display lower levels of weather. In both cases, ground clutter may also be
displayed as a result of low settings and/or increased gain.
PREDICTIVE WINDSHEAR SYSTEM ..................................................................................AUTO
Ident.: PRO-NOR-SOP-10-A-00015298.0002001 / 03 AUG 17
Impacted by TDU: 00015299 Taxi - Radar
RADAR.............................................................................................................................................. ON
To check the radar and the departure path, set the MULTISCAN sw to MAN. The flight crew can then
set the radar to the AUTO position.
PREDICTIVE WINDSHEAR SYSTEM ..................................................................................AUTO
Ident.: PRO-NOR-SOP-10-A-00010252.0001001 / 20 JAN 15
ATC
ATC code/mode...............................................................................CONFIRM/SET FOR TAKEOFF
Ident.: PRO-NOR-SOP-10-A-00010254.0001001 / 03 AUG 17
TERR ON ND
TERR ON ND .............................................................................................................AS RQRD
Consider selecting the radar display on the PF side, and TERR ON ND on the PM side only.
Ident.: PRO-NOR-SOP-10-A-00010264.0001001 / 15 MAY 13
AUTO BRK
AUTO BRK MAX pb-sw................................................................................................................ ON
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PROCEDURES
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FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - TAXI
Ident.: PRO-NOR-SOP-10-A-00010268.0001001 / 04 MAR 14
FINAL CHECK
T.O CONFIG pb.........................................................................................................................TEST
Check that ECAM upper display shows “T.O CONFIG NORMAL”.
T.O MEMO............................................................................................................ CHECK NO BLUE
CABIN REPORT................................................................................................................. RECEIVE
Obtain cabin report from the purser, as a minimum : “CABIN SECURED FOR TAKEOFF”
Ident.: PRO-NOR-SOP-10-A-00010271.0001001 / 15 MAY 13
BEFORE TAKEOFF CHECKLIST
BEFORE TAKEOFF CHECKLIST down to the line........................................................COMPLETE
Ident.: PRO-NOR-SOP-10-A-00020075.0001001 / 17 MAR 17
TAXI FLOW PATTERN
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STANDARD OPERATING PROCEDURES - TAXI
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05 SEP 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - BEFORE TAKEOFF
BEFORE TAKEOFF
Applicable to: ALL
Ident.: PRO-NOR-SOP-11-A-00010396.0001001 / 05 AUG 10
If the brake fans are running:
BRAKE TEMP......................................................................................................................CHECK
‐ If brake temperature is above 150 °C, delay takeoff.
‐ If brake temperature is below 150 °C, select brake fans off.
Ident.: PRO-NOR-SOP-11-A-00010388.0001001 / 05 AUG 10
TAKEOFF OR LINE UP CLEARANCE..................................................................................... OBTAIN
Ident.: PRO-NOR-SOP-11-A-00010392.0002001 / 29 SEP 15
EXTERIOR LIGHTS
L2
L1
L2
RWY TURN OFF sw..................................................................................................................... ON
NOSE sw.......................................................................................................................................T.O
STROBE sw...................................................................................................................................ON
Set the STROBE sw to ON when entering the runway.
LAND LIGHTS sw......................................................................................................................... ON
Set the LAND LIGHTS sw to ON when entering the runway and takeoff clearance is received.
The PF may ask the PM to set the exterior lights.
Note:
Setting the RWY TURN OFF sw, the LAND LIGHTS sw and the NOSE sw to ON/T.O
minimizes bird strike hazard during takeoff.
Ident.: PRO-NOR-SOP-11-A-00010389.0001001 / 04 MAR 14
TCAS
L2
TCAS Mode selector.............................................................................................TA or TA /RA
The flight crew should use the TA /RA mode as the default mode of the TCAS.
The flight crew may use the TA ONLY mode in specific airports, and for specific procedures
(identified by Operators) that may provide resolution advisories that are neither wanted nor
appropriate (e.g. closely-spaced parallel or converging runways).
Ident.: PRO-NOR-SOP-11-A-00010390.0001001 / 04 MAR 14
APPROACH PATH CLEARED OF TRAFFIC
APPROACH PATH......................................................................................CLEARED OF TRAFFIC
Check that the approach path is clear of traffic, visually and using TCAS display on ND.
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - BEFORE TAKEOFF
Ident.: PRO-NOR-SOP-11-A-00010399.0001001 / 16 MAR 11
CABIN CREW............................................................................................................................ADVISE
Advise the cabin crew that takeoff is imminent.
Ident.: PRO-NOR-SOP-11-A-00010397.0004001 / 16 MAR 11
ENG MODE selector..............................................................................................................AS RQRD
Select IGN, if:
‐ The runway has standing water, or
‐ Heavy rain is falling, or
‐ Heavy rain or severe turbulence is expected after takeoff.
Ident.: PRO-NOR-SOP-11-A-00010394.0001001 / 20 MAR 17
SLIDING TABLE/EFB
SLIDING TABLE.......................................................................................................................STOW
EFB/eQRH transmitting mode......................................................................................... CONSIDER
In accordance with the Operator's policy or, as required by operational regulations.
EFB/eQRH (with no mounted equipment)............................................................................... STOW
In flight, both flight crewmembers should not use at the same time Flysmart with Airbus
applications.
Ident.: PRO-NOR-SOP-11-A-00010393.0001001 / 21 MAR 17
TAKEOFF RUNWAY..............................................................................................................CONFIRM
Confirm that the line up is performed on the intended runway. Useful aids are:
‐ The runway markings,
‐ The runway lights,
Be careful that in low visibility, edge lights could be mixed up with the center line lights.
‐ The ILS signal,
If the runway is ILS equipped, the flight crew can press the ILS pb (or LS pb): The LOC deviation
should be centered after line up.
‐ The runway symbol on the ND,
‐ The Runway Awareness and Advisory System .
Ident.: PRO-NOR-SOP-11-A-00010391.0001001 / 05 AUG 10
PACK 1 and 2........................................................................................................................AS RQRD
Consider selecting packs OFF, or APU bleed ON.
This will improve performance when using TOGA thrust.
In case of a FLEX takeoff, selecting packs OFF or APU bleed ON will reduce takeoff EGT, and thus
reduce maintenance costs.
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FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - BEFORE TAKEOFF
The use of flex thrust may reduce maintenance costs. The effect is particularly significant with the
first degrees of FLEX.
Use of APU bleed is not authorized, if wing anti-ice is to be used.
Ident.: PRO-NOR-SOP-11-A-00010400.0001001 / 16 MAR 11
BEFORE TAKEOFF CHECKLIST below the line............................................................... COMPLETE
Read the checklist below the line, when line-up clearance is obtained.
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STANDARD OPERATING PROCEDURES - BEFORE TAKEOFF
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22 MAR 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - TAKEOFF
TAKEOFF
Applicable to: ALL
Ident.: PRO-NOR-SOP-12-A-00011559.0001001 / 28 JUL 14
The below procedure is the standard takeoff procedure. However, rolling takeoff is permitted.
TAKEOFF........................................................................................................................... ANNOUNCE
Ident.: PRO-NOR-SOP-12-A-00011560.0006001 / 23 JUN 15
THRUST SETTING
THRUST LEVERS.............................................................................................50 % N1 (1.05 EPR)
If the crosswind is at or below 20 kt and there is no tailwind:
To counter the nose-up effect of setting engine takeoff thrust, apply half forward sidestick until
the airspeed reaches 80 kt. Release the sidestick gradually to reach neutral at 100 kt.
BRAKES.......................................................................................................................RELEASE
THRUST LEVERS................................................................................................. FLX or TOGA
Once the thrust levers are set to FLX or TOGA detent, the Captain keeps his hand on the
thrust levers until the aircraft reaches V1.
In case of tailwind, or if crosswind is greater than 20 kt:
The PF applies full forward sidestick.
BRAKES.......................................................................................................................RELEASE
THRUST LEVERS................................................................................................. FLX or TOGA
‐ The PF rapidly increases thrust to about 70 % N1 (1.15 EPR) then progressively to reach
takeoff thrust by 40 kt ground speed, while maintaining sidestick full forward up to 80 kt.
Release the sidestick gradually to reach neutral at 100 kt.
‐ Once the thrust levers are set to FLX or TOGA detent, the Captain keeps his hand on the
thrust levers until the aircraft reaches V1.
Note:
ENG SD page replaces WHEEL SD page on the ECAM lower display.
DIRECTIONAL CONTROL......................................................................................... USE RUDDER
At 130 kt (wheel speed), the connection between nosewheel steering and the rudder pedals
is removed. Therefore, in strong crosswinds, more rudder input will be required at this point to
prevent the aircraft from turning into the wind.
CHRONO.................................................................................................................................START
PFD /ND.............................................................................................................................MONITOR
1. Check the FMA on the PFD . The following modes are displayed: MAN TOGA (or MAN FLX xx)
/SRS /RWY (or blank) / A/THR (in blue).
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FLIGHT CREW
OPERATING MANUAL
Note:
STANDARD OPERATING PROCEDURES - TAKEOFF
If an ILS that corresponds to the departure runway is tuned, RWY mode appears. If
not, no lateral mode appears until the aircraft lifts off.
2. Check the FMS position on the ND (aircraft on runway centerline).
Note:
If GPS PRIMARY is not available, check the FMS position update.
FMA................................................................................................................................ ANNOUNCE
Ident.: PRO-NOR-SOP-12-A-00011561.0001001 / 04 MAR 14
BELOW 80 KT
TAKEOFF N1......................................................................................................................... CHECK
Check that the actual N1 of the individual engines has reached the N1 rating limit, before the
aircraft reaches 80 kt. Check EGT.
THRUST SET................................................................................................................. ANNOUNCE
PFD and ENG indications..................................................................................................MONITOR
Scan airspeed, N1 , and EGT throughout the takeoff.
Ident.: PRO-NOR-SOP-12-A-00011562.0001001 / 13 AUG 10
REACHING 100 KT
ONE HUNDRED KNOTS............................................................................................... ANNOUNCE
‐ The PF crosschecks and confirms the speed indicated on the PFD
‐ Below 100 kt the Captain may decide to abort the takeoff, depending on the circumstances
‐ Above 100 kt, rejecting the takeoff is a more serious matter.
Ident.: PRO-NOR-SOP-12-A-00011563.0001001 / 13 AUG 10
AT V1
V1....................................................................................................................................ANNOUNCE
Ident.: PRO-NOR-SOP-12-A-00011564.0001001 / 13 AUG 10
AT VR
ROTATION ............................................................................................................................ORDER
ROTATION........................................................................................................................ PERFORM
‐ At VR, initiate the rotation to achieve a continuous rotation with a rate of about 3 °/s, towards a
pitch attitude 15 ° (12.5 °, one engine is failed)
‐ Minimize the lateral inputs on ground and during the rotation, to avoid spoiler extension
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PROCEDURES
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FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - TAKEOFF
‐ In strong crosswind conditions, small lateral stick inputs may be used, if necessary, to aim at
maintaining wings level
‐ After lift-off, follow the SRS pitch command bar.
CAUTION
If a tailstrike occurs, avoid flying at an altitude requiring a pressurized cabin, and
return to the originating airport for damage assessment.
Ident.: PRO-NOR-SOP-12-A-00011565.0001001 / 04 MAR 14
WHEN POSITIVE CLIMB
POSITIVE CLIMB........................................................................................................... ANNOUNCE
L/G UP................................................................................................................................... ORDER
L/G.................................................................................................................................. SELECT UP
AP.......................................................................................................................................AS RQRD
Above 100 ft AGL , AP 1 or 2 may be engaged.
Ident.: PRO-NOR-SOP-12-A-00011566.0002001 / 28 JUL 15
AT THRUST REDUCTION ALTITUDE
THRUST LEVERS..........................................................................................................................CL
Move the thrust levers to the CL detent, when the flashing LVR CLB prompt appears on the FMA .
A/THR is now active.
In manual flight, the pilot must anticipate the change in pitch attitude in order to prevent the speed
from decaying when thrust is reduced.
PACK 1 and 2 (if applicable)........................................................................................................ ON
Select PACK 1 on after CLB thrust reduction.
Select PACK 2, at least 10 s after PACK 1 is selected on, for passenger comfort.
Note:
1. Selecting pack on before reducing takeoff thrust would result in an EGT increase.
2. If packs are not switched on after the takeoff phase, an ECAM caution will be
triggered.
Ident.: PRO-NOR-SOP-12-A-00011567.0002001 / 04 MAR 14
AT ACCELERATION ALTITUDE
Check the target speed change from V2 + 10 to the first CLB speed (either preselected or
managed).
Note:
1. When THR RED and ACC ALT are equal, the FMA will change from MAN FLX/SRS
/NAV to THR CLB /CLB /NAV.
2. If FCU -selected altitude is equal to or close to the acceleration altitude, then the FMA
will switch from SRS to ALT*.
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FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - TAKEOFF
Ident.: PRO-NOR-SOP-12-A-00011568.0001001 / 23 JUN 15
ABOVE ACCELERATION ALTITUDE (OR ONCE IN CLIMB PHASE)
The following procedure ensures that the aircraft is effectively accelerating toward climb speed.
At F speed:
Note:
For takeoff in CONF 1 + F, “F” speed does not appear.
FLAPS 1.......................................................................................................................... ORDER
FLAPS 1......................................................................................................................... SELECT
At S speed:
FLAPS 0.......................................................................................................................... ORDER
FLAPS 0......................................................................................................................... SELECT
GND SPLRS...................................................................................................................DISARM
NOSE sw...............................................................................................................................OFF
RWY TURN OFF sw.............................................................................................................OFF
OTHER EXTERIOR LIGHTS.......................................................................................AS RQRD
The flight crew can maintain the LAND LIGHTS selector set to ON, according to airline policy
or regulatory recommendations.
Note:
The CRUISE SD page replaces the ENG SD page.
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STANDARD OPERATING PROCEDURES - TAKEOFF
Ident.: PRO-NOR-SOP-12-A-00011570.0001001 / 18 DEC 12
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FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - TAKEOFF
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FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - AFTER TAKEOFF
AFTER TAKEOFF
Applicable to: ALL
Ident.: PRO-NOR-SOP-13-A-00010157.0001001 / 21 MAR 17
APU BLEED pb .................................................................................................................... AS RQRD
If the APU has been used to supply air conditioning during takeoff, set the APU BLEED pb to OFF.
For use of the APU BLEED, Refer to LIM-APU Operational Envelope.
APU MASTER SW pb .......................................................................................................... AS RQRD
Ident.: PRO-NOR-SOP-13-A-00010158.0001001 / 05 AUG 10
ENG MODE selector..............................................................................................................AS RQRD
Select IGN, if severe turbulence or heavy rain is encountered.
Ident.: PRO-NOR-SOP-13-A-00010159.0001001 / 05 AUG 10
TCAS Mode selector ...........................................................................................................TA/RA
Select TA/RA, if the takeoff has been performed with TA only.
Ident.: PRO-NOR-SOP-13-A-00010160.0002001 / 21 MAR 17
ENG ANTI-ICE pb-sw ........................................................................................................... AS RQRD
Engine anti-ice must be set to ON when icing conditions (Refer to LIM-ICE_RAIN Definition of Icing
Conditions) exist or are anticipated, except during climb when the SAT is below -40 °C (-40 °F).
WING ANTI-ICE pb-sw ......................................................................................................... AS RQRD
When icing conditions are encountered:
‐ The flight crew may turn on the wing anti-ice to prevent ice accretion on the wing leading edge.
‐ The flight crew must turn on the wing anti-ice if there is evidence of ice accretion, such as ice on
the visual indicator, or on the wipers, or with the SEVERE ICE DETECTED alert. This is to
remove any ice accumulation from the wing leading edge.
Ident.: PRO-NOR-SOP-13-A-00010161.0001001 / 05 AUG 10
AFTER TAKEOFF/CLIMB CHECKLIST down to the line................................................... COMPLETE
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A
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NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - AFTER TAKEOFF
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OPERATING MANUAL
STANDARD OPERATING PROCEDURES - CLIMB
CLIMB
Applicable to: ALL
Ident.: PRO-NOR-SOP-14-A-00010245.0002001 / 09 JUN 15
Impacted by TDU: 00013057 Climb - Initial Climb
Normal vertical mode is CLB or OP CLB with managed speed active.
PF MCDU..............................................................................................................................PERF CLB
‐ PF MCDU should be showing the PERF CLB page (allowing PF to monitor when the aircraft will
reach the FCU selected altitude) but he may select other pages such as F-PLN page as may be
tactically necessary.
With the AP engaged, the PF may revise the flight plan.
‐ The MCDU PROG page displays OPT FL and MAX REC FL . It is worth noting that this OPT FL is
a function of the cost index (CI).
‐ The displayed MAX REC FL gives the aircraft at least a 0.3 g buffet margin. The pilot may enter a
cruise flight level above this level into the MCDU and the FMGS will accept it, provided that it does
not exceed the level at which the margin is reduced to 0.2 g.
PM MCDU.................................................................................................................................... F-PLN
PM MCDU should be showing the F-PLN page (allowing him to enter any ATC long-term revisions to
the lateral or vertical flight plan).
CLIMB SPEED MODIFICATIONS
If ATC, turbulence or operational considerations lead to a speed change:
Select the new speed with FCU SPD knob and pull.
Speed target is now “selected”.
To return to managed speed mode, push FCU SPD knob.
The speed target is now “managed”.
Note:
The best speed (and rate of climb) for long-term situations lies between green dot
speed and ECON speed. At high altitude, acceleration from green dot to ECON
speed can take a long time.
EXPEDITE CLIMB
If ATC requires a rapid climb through a particular level:
Push the EXP pb on the FCU.
The target speed is now green dot speed. FMA :THR CLB /EXP CLB/NAV
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OPERATING MANUAL
Note:
STANDARD OPERATING PROCEDURES - CLIMB
Use EXP only for short-term tactical situations. For the best overall economy fly
at ECON IAS.
To return to ECON CLB speed:
Push ALT knob.
Check FMA : THR CLB /CLB /NAV
BAROMETRIC REFERENCE................................................................... SET STD/CROSSCHECK
At transition altitude (baro setting flashing on PFD ) set STD on the EFIS control panel and
standby altimeter.
Cross-check baro settings and altitude readings.
CRZ FL...................................................................................................................... SET AS RQRD
‐ If ATC clears the aircraft to its intended CRZ FL or above, there is no need to modify the CRZ
FL entered in the INIT A page during cockpit preparation. The MCDU will automatically take into
account a higher CRZ FL selected with the FCU ALT knob.
‐ If ATC limits CRZ FL to a lower level than the one entered in the INIT A page (or present on the
PROG page) the flight crew must insert this lower CRZ FL in the PROG page.
Otherwise there is no transition into CRZ phase : the managed speed targets and Mach are not
modified, and SOFT ALT mode is not available. In that case FMA will display: MACH/ALT /NAV
instead of MACH/ALT CRZ /NAV.
Ident.: TDU / PRO-NOR-SOP-14-A-00013057.0006001 / 29 JUN 16
Impacted DU: 00010245 Climb - Initial Climb
Normal vertical mode is CLB or OP CLB with managed speed active.
PF MCDU..............................................................................................................................PERF CLB
‐ PF MCDU should be showing the PERF CLB page (allowing PF to monitor when the aircraft will
reach the FCU selected altitude) but he may select other pages such as F-PLN page as may be
tactically necessary.
With the AP engaged, the PF may revise the flight plan.
‐ The MCDU PROG page displays OPT FL and MAX REC FL . It is worth noting that this OPT FL is
a function of the cost index (CI).
‐ The displayed MAX REC FL gives the aircraft at least a 0.3 g buffet margin. The pilot may enter a
cruise flight level above this level into the MCDU and the FMGS will accept it, provided that it does
not exceed the level at which the margin is reduced to 0.2 g.
PM MCDU.................................................................................................................................... F-PLN
PM MCDU should be showing the F-PLN page (allowing him to enter any ATC long-term revisions to
the lateral or vertical flight plan).
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OPERATING MANUAL
STANDARD OPERATING PROCEDURES - CLIMB
CLIMB SPEED MODIFICATIONS
If ATC, turbulence or operational considerations lead to a speed change:
Select the new speed with FCU SPD knob and pull.
Speed target is now “selected”.
To return to managed speed mode, push FCU SPD knob.
The speed target is now “managed”.
Note:
The best speed (and rate of climb) for long-term situations lies between green dot
speed and ECON speed. At high altitude, acceleration from green dot to ECON
speed can take a long time.
EXPEDITE CLIMB
If ATC requires a rapid climb through a particular level:
Push the EXP pb on the FCU.
The target speed is now green dot speed. FMA :THR CLB /EXP CLB/NAV
Note:
Use EXP only for short-term tactical situations. For the best overall economy fly
at ECON IAS.
To return to ECON CLB speed:
Push ALT knob.
Check FMA : THR CLB /CLB /NAV
BAROMETRIC REFERENCE................................................................... SET STD/CROSSCHECK
At transition altitude (baro setting flashing on PFD ) set STD on the EFIS control panel and
standby altimeter.
Cross-check baro settings and altitude readings.
Note:
When STD is set on the EFIS control panel, the transponder does not transmit to the
Air Traffic Control (ATC ) the standard barometric reference but the last QNH or QFE
previously selected. The transmitted aircraft altitude is not affected. Only the FCU
selected altitude, if used by the ATC, may be misinterpreted.
Upon ATC notification of an incorrect barometric reference value, the flight crew can
select manually a barometric reference of 1 013 hPa and set again STD on the EFIS
control panel.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-14 P 3/6
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - CLIMB
CRZ FL...................................................................................................................... SET AS RQRD
‐ If ATC clears the aircraft to its intended CRZ FL or above, there is no need to modify the CRZ
FL entered in the INIT A page during cockpit preparation. The MCDU will automatically take into
account a higher CRZ FL selected with the FCU ALT knob.
‐ If ATC limits CRZ FL to a lower level than the one entered in the INIT A page (or present on the
PROG page) the flight crew must insert this lower CRZ FL in the PROG page.
Otherwise there is no transition into CRZ phase : the managed speed targets and Mach are not
modified, and SOFT ALT mode is not available. In that case FMA will display: MACH/ALT /NAV
instead of MACH/ALT CRZ /NAV.
Ident.: PRO-NOR-SOP-14-A-00010257.0001001 / 05 AUG 10
AFTER TAKEOFF/CLIMB CHECKLIST below the line...................................................... COMPLETE
Ident.: PRO-NOR-SOP-14-A-00010258.0001001 / 17 MAR 17
ENG ANTI-ICE pb-sw ........................................................................................................... AS RQRD
Engine anti-ice must be set to ON when icing conditions (Refer to LIM-ICE_RAIN Definition of Icing
Conditions) exist or are anticipated, except during climb when the SAT is below - 40 °C (-40 °F).
Ident.: TDU / PRO-NOR-SOP-14-A-00013047.0003001 / 03 MAR 14
Impacted DU: 00010259 Climb - Radar
RADAR.................................................................................................................... AS APPROPRIATE
Gain must be manually set to +4, when MULTISCAN selector is set to AUTO and when flying below
FL 200.
Note:
1. If the weather is good, or not significant, in order to check that the radar is operating
correctly: down tilt until displaying ground echoes.
2. If the weather display is ambiguous or unexpected, in order to better analyze the weather
situation, use manual tilt according to standard technique.
3. In particular below FL 200, for situations with low-level weather, weather with low
reflectivity or in front of suspected active cells, the flight crew should switch to Manual
mode and adjust the tilt setting downward until the weather is detected or the ground
clutter appears on the upper part of the display.
4. In addition, the flight crew may increase the manual gain control to display lower
reflectivity targets. The manual gain control can be increased in both AUTO and Manual
modes to display lower levels of weather. In both cases, ground clutter may also be
displayed as a result of low settings and/or increased gain.
Ident.: PRO-NOR-SOP-14-A-00010259.0002001 / 16 MAR 11
Impacted by TDU: 00013047 Climb - Radar
RADAR.................................................................................................................... AS APPROPRIATE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-14 P 4/6
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - CLIMB
Ident.: PRO-NOR-SOP-14-A-00010260.0001001 / 04 MAR 14
AT 10.000FT
LAND LIGHTS selector......................................................................................................RETRACT
SEAT BELTS sw................................................................................................................AS RQRD
EFIS option.........................................................................................................................AS RQRD
Select CSTR on one side, for grid MORA (if available), and ARPT on the other side.
ECAM MEMO....................................................................................................................... REVIEW
NAVAIDS.................................................................................................................................CLEAR
Clear manually tuned VOR s from MCDU RAD NAV page.
SEC F-PLN page............................................................................................................... AS RQRD
Recopy the active flight plan in the secondary if an immediate return flight plan has been
constructed previously.
OPT/MAX ALT........................................................................................................................CHECK
Ident.: PRO-NOR-SOP-14-A-00020076.0001001 / 17 MAR 17
10 000 ft FLOW PATTERN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-14 P 5/6
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - CLIMB
EFIS Option:
The PF will select CSTR for grid MORA
The PM will select ARPT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SOP-14 P 6/6
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - CRUISE
CRUISE
Applicable to: ALL
Ident.: PRO-NOR-SOP-15-A-00010287.0001001 / 25 AUG 16
ECAM MEMO........................................................................................................................... REVIEW
ECAM SD PAGES....................................................................................................................REVIEW
Periodically review system display pages and, in particular:
ENG
: Oil pressure and temperature
BLEED : BLEED parameters
ELEC : Parameters, GEN loads
HYD
: A slight decrease in quantity is normal.
Fluid contraction during cold soak can be expected.
Green system is lower than on ground, following landing gear retraction.
FUEL : Fuel distribution.
COND : Duct temperature, compared with zone temperature.
Avoid large differences for passenger comfort.
FLT CTL : Note any unusual control surface position.
DOOR : Oxygen pressure.
Ident.: PRO-NOR-SOP-15-A-00010288.0001001 / 17 MAR 17
FLIGHT PROGRESS................................................................................................................. CHECK
Monitor flight progress in the conventional way.
When overflying a waypoint:
‐ Check track and distance to the next waypoint.
When overflying the waypoint, or at least every 30 min:
‐ Check FUEL : Check FOB (ECAM ), and fuel prediction (FMGC), and compare with the computer
flight plan or the in-cruise quick-check table (Refer to QRH/PER-M In Cruise Quick Check at a
Given Mach Number (Paper Only) or use the performance application of FlySmart with Airbus).
Check that the sum of the fuel on board and the fuel used is consistent with the fuel on board
at departure. If the sum is unusually greater than the fuel on board at departure, suspect a fuel
quantity over read. If the sum is unusually smaller than the fuel on board at departure, or if it
decreases, suspect a fuel leak.
For more information about fuel leak, Refer to FCTM/PR-AEP-FUEL Fuel Leak.
CAUTION
This check must also be performed each time a FUEL IMBALANCE procedure is
necessary. Perform the check before applying the FUEL IMBALANCE procedure.
If a fuel leak is confirmed, apply the FUEL LEAK procedure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SOP-15 P 1/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - CRUISE
Ident.: PRO-NOR-SOP-15-A-00010289.0001001 / 01 DEC 14
STEP FLIGHT LEVEL.............................................................................................AS APPROPRIATE
Ident.: PRO-NOR-SOP-15-A-00010290.0001001 / 21 MAR 17
NAV ACCURACY...................................................................................................................MONITOR
On aircraft equipped with GPS primary, no navigation accuracy check is required, as long as GPS
PRIMARY is available.
Otherwise, a navigation accuracy check must be performed especially when any of the following
occurs:
‐ GPS PRIMARY LOST appears on the ND (GPS )
‐ IRS only navigation
‐ The PROG page displays LOW accuracy
‐ “NAV ACCUR DOWNGRAD” appears on the MCDU.
Refer to DSC-22_20-20-20 Estimated Position Uncertainty.
Note:
Methods for checking accuracy:
If the check is positive (error ≤ 3 N.m): FM position is reliable.
Use ND (ARC or NAV) and managed lateral guidance.
If the check is negative (error > 3 N.m): FM position is not reliable.
Use raw data for navigation and monitor it.
If there is a significant mismatch between the display and the real position:
Disengage MANAGED NAV mode and use raw data navigation (possibly switching
to ROSE VOR, so as not to be misled by FM data).
Ident.: TDU / PRO-NOR-SOP-15-A-00013068.0006001 / 20 SEP 16
Impacted DU: 00010291 Cruise - Radar Tilt
RADAR ...................................................................................................................AS APPROPRIATE
Gain must be manually set to +4, when MULTISCAN selector is set to AUTO and when flying below
FL 200.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-15 P 2/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
STANDARD OPERATING PROCEDURES - CRUISE
1. If the weather is good, or not significant, in order to check that the radar is operating
correctly: down tilt until displaying ground echoes.
2. If the weather display is ambiguous or unexpected, in order to better analyze the weather
situation, use manual tilt according to standard technique.
3. In particular below FL 200, for situations with low-level weather, weather with low
reflectivity or in front of suspected active cells, the flight crew should switch to Manual
mode and adjust the tilt setting downward until the weather is detected or the ground
clutter appears on the upper part of the display.
4. In addition, the flight crew may increase the manual gain control to display lower
reflectivity targets. The manual gain control can be increased in both AUTO and Manual
modes to display lower levels of weather. In both cases, ground clutter may also be
displayed as a result of low settings and/or increased gain.
Ident.: PRO-NOR-SOP-15-A-00010291.0002001 / 07 MAR 13
Impacted by TDU: 00013068 Cruise - Radar Tilt
RADAR ...................................................................................................................AS APPROPRIATE
Ident.: PRO-NOR-SOP-15-A-00010296.0001001 / 21 MAR 16
If the oxygen mask has been used:
OXYGEN MASK ................................................................................................................. CHECK
Check that the oxygen mask has been properly stowed, Refer to DSC-35-20-10 General.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SOP-15 P 3/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - CRUISE
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SOP-15 P 4/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT PREPARATION
DESCENT PREPARATION
Applicable to: ALL
Ident.: PRO-NOR-SOP-16-A-00011551.0001001 / 30 JUN 14
Descent preparation and approach briefing should be completed before top of descent.
Ident.: PRO-NOR-SOP-16-A-00011552.0006001 / 20 MAR 17
WEATHER AND LANDING INFORMATION.............................................................................OBTAIN
Check weather reports at ALTERNATE and DESTINATION airports. Airfield data should include
runway in use for arrival.
Note:
When operating in cold weather conditions, consider altitude correction. Refer to
PER-OPD-GEN ALTITUDE TEMPERATURE CORRECTION.
NAV CHARTS CLIPBOARD..................................................................................................PREPARE
Ident.: PRO-NOR-SOP-16-A-00014394.0001001 / 27 APR 17
EFB LDG PERFORMANCE.......................................................................................................CHECK
Perform an in-flight landing performance assessment if the landing conditions changed compared
with the landing computation at dispatch, or with a previous computation (e.g. runway, weather
conditions, in-flight failure affecting performance, diversion).
Note:
1. If the weather conditions are expected to change at the landing airport, or in the event
of significant precipitation, the flight crew should consider a second calculation of the
in-flight landing distance with the worst possible runway condition.
2. The selection of REV MAX is the standard practice for landing.
However, on dry runways the flight crew may select REV IDLE.
On WET runways (runway surface condition GOOD), the flight crew may select REV
IDLE, if all the following conditions are satisfied:
‐ A landing distance assessment has been made with the following parameters:
• MEDIUM TO POOR landing performance level for the in-flight landing distance
computation
• No reverser credit
‐ The result of this landing distance assessment is within the LDA.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SOP-16 P 1/8
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT PREPARATION
If landing conditions changed:
LDG PERFORMANCE............................................................................................(RE)COMPUTE
In the LDG PERF application, modify the selections in accordance with the estimated arrival
conditions:
‐ In the AIRPORT/RUNWAY part, select the applicable runway
‐ In the CONDITIONS part, enter the estimated landing conditions
‐ In the AIRCRAFT STATUS part, check the selected items, if any
‐ Launch the computation and check the results versus Airline policy or applicable regulations.
LDG PERFORMANCE............................................................................................CROSSCHECK
Ident.: PRO-NOR-SOP-16-A-00020100.0001001 / 17 MAY 17
ARRIVAL page...................................................................................................... COMPLETE/CHECK
Insert APPR , STAR , APPR VIA and TRANS if applicable. (Access by lateral revision at destination.)
F-PLN A page............................................................................................................................ CHECK
‐ Ensure that the inserted F-PLN agrees with planned approach and missed approach.
‐ Use the scroll key to check the F-PLN thoroughly, using ND in PLAN mode as necessary.
Tracks and distances between waypoints are displayed on the second line from the top of the
MCDU. Approach and Missed Approach tracks and distances must be checked from the appropriate
navigation charts.
‐ Check speed constraints. Add new speed constraints if required.
‐ Check altitude constraints. Add new altitude constraints if required.
Note:
The FMS may have deleted the altitude constraints that are at or above the CRZ
FL , or at or above any previous lower CRZ FL in the case of step climbs (Refer to
DSC-22_20-30-20-05 Vertical Constraints (Speed, Altitude, Time)).
In that case,
‐ Insert again the affected procedures (STAR , APPR VIA or TRANS)
The FMS keeps the altitude constraints that are below the CRZ FL , and deletes again
the altitude constraints that are above current CRZ FL . The FMS may also delete the
altitude constraints that are at current CRZ FL , and the altitude constraint windows
that have a constraint at or above current CRZ FL.
‐ Manually enter the altitude constraints that are below current CRZ FL using the MCDU
Vertical Revision pages.
It is not possible to enter an altitude constraint at the CRZ FL.
In the case of an "AT" or "AT OR ABOVE" altitude constraint at the CRZ FL , the flight
crew must select the DES mode only after the aircraft reaches the position of the
altitude constraint to prevent an early descent..
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-16 P 2/8
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT PREPARATION
‐ In all cases, do not modify the final approach (FAF to runway or MAP), including altitude
constraints.
‐ Identify the position and the altitude of Final Descent Point (FDP ) and check the value of the FPA
after this FDP,
‐ If a TOO STEEP PATH message is displayed after the FDP, do not use FINAL APP guidance for
approach.
‐ Identify the Missed Approach Point.
Ident.: PRO-NOR-SOP-16-A-00020101.0001001 / 20 SEP 16
DES WIND page........................................................................................................................ CHECK
Enter winds for descent before T/D.
Note:
With DPO , as the idle thrust margins are reduced, accurate winds have to be entered
to be able to follow the computed vertical profile and thus maximize the benefits of DPO
. Refer to DSC-22_20-60-150 Descent Profile Optimization (if installed).
PERF CRUISE page.................................................................................................................. CHECK
Modify the cabin descent rate if different pressure rate is required.
PERF DES page........................................................................................................................ CHECK
Prior to descent, access PERF DES page and check ECON MACH/SPD . If a speed other than
ECON is required, insert that MACH or SPD into the ECON field. This new MACH or SPD is now the
one for the descent path and T/D computation, and it will be used for the managed speed descent
profile (instead of ECON).
A speed limit of 250 kt below 10 000 ft is the defaulted speed, in the managed speed descent profile.
The flight crew may delete or modify it if necessary on the VERT REV at DEST page.
Ident.: PRO-NOR-SOP-16-A-00020102.0002001 / 21 MAR 17
PERF APPR page................................................................................................. COMPLETE/CHECK
Enter the QNH, temperature, and wind at destination.
L13
Note:
Insert the average wind given by the ATC or ATIS. Do not insert the gust value. During
approach, the Ground Speed Mini function (manage speed mode) takes into account the
instantaneous gust.
For more information: Refer to Ground Speed Mini Function.
For example, if the wind is 15020G35KT, insert 150/20.
Insert the minimum.
Note:
To avoid undershooting the published minimum during go-around, due to aircraft inertia
during pull-up, some Authorities may require Operators to add a specific number of feet to
the published minimum.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-16 P 3/8
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CAUTION
STANDARD OPERATING PROCEDURES - DESCENT PREPARATION
If the QNH altimeter setting is used for an aircraft with the QFE option , Refer to
PRO-NOR-SUP-NAV QNH use for aircraft equipped with QFE option.
Note:
Changing the RWY or the type of approach automatically erases the previous minimum.
Note:
After the activation of the SEC F-PLN , check the VAPP, and modify if necessary.
Check or modify the landing configuration. Always select the landing configuration on the PERF APP
page: CONF FULL in the normal landing configuration. CONF 3 should be considered, depending
on the available runway length and go-around performance, or if windshear/severe turbulence is
considered possible during approach.
If the forecasted tailwind at landing is greater than 10 kt , refer to "LIM-12-Airport Operations and
Wind Limitations" for the recommended/required landing configuration.
Check or modify the transition altitude.
PERF GO-AROUND page.......................................................................................... CHECK/MODIFY
Check THR RED ALT and ACC ALT, and modify, if necessary.
Ident.: PRO-NOR-SOP-16-A-00020103.0001001 / 20 SEP 16
RAD NAV page.......................................................................................................................... CHECK
‐ Set navaids, as required, and check idents on the ND s (VOR -ADF ) and PFD s (ILS , GLS ,
MLS ). If a VOR /DME exists close to the airfield, select it and enter its ident in the BRG /DIST
field of the PROG page, for NAV ACCY monitoring during descent.
‐ When the flight plan calls for an NDB approach, the system automatically tunes the ADF , only
when the aircraft is passing the first fix of the approach. Therefore, it is convenient to manually
tune the ADF earlier (before activating the approach phase).
Ident.: PRO-NOR-SOP-16-A-00020104.0001001 / 20 SEP 16
SEC F-PLN page................................................................................................................... AS RQRD
Before the top of descent, the SEC F-PLN should either be set to an alternate runway for destination,
or to the landing runway in case of circling. In all cases, routing to the alternate should be available.
If there is a last-minute runway change, then the flight crew only needs to activate the secondary
F-PLN , without forgetting to check/set the new minimum and navaids.
Ident.: PRO-NOR-SOP-16-A-00011554.0001001 / 03 MAR 14
GPWS LDG FLAP 3 pb-sw....................................................................................................AS RQRD
If the pilot plans on landing in FLAPS 3 configuration, the GPWS LDG FLAP 3 pb-sw should be set to
ON.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-16 P 4/8
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT PREPARATION
Ident.: PRO-NOR-SOP-16-A-00015490.0001001 / 03 MAR 14
LDG ELEV..................................................................................................................................CHECK
Check that the LDG ELEV AUTO green is displayed on the ECAM CRUISE page, and check the
associated value.
Ident.: PRO-NOR-SOP-16-A-00011556.0001001 / 17 MAR 17
AUTO BRK ............................................................................................................................AS RQRD
Use of autobrake is preferable.
Use of MAX mode is not recommended at landing.
On short or contaminated runways, use MED mode.
On long runways, LO mode is recommended.
L2 For more information, Refer to FCTM/PR-NP-SOP-160 Brakes Oxidation.
L1
Note:
If, on very long runways, the flight crew anticipates that braking will not be needed, use of
the autobrake is not necessary.
Firmly press the appropriate pushbutton, according to the runway length and condition, and check
that the related ON light comes on.
Ident.: PRO-NOR-SOP-16-A-00011555.0001001 / 10 JUL 14
APPROACH BRIEFING........................................................................................................ PERFORM
Ident.: PRO-NOR-SOP-16-A-00011547.0001001 / 23 JUN 15
TERR ON ND .................................................................................................................AS RQRD
‐ In mountainous areas, consider displaying terrain on ND.
‐ If use of radar is required, consider selecting the radar display on the PF side, and TERR ON ND
on the PM side only.
‐ If NAV ACCURACY is LOW, do not use TERR on ND.
Ident.: TDU / PRO-NOR-SOP-16-A-00013353.0003001 / 03 MAR 14
Impacted DU: 00011545 Descent Preparation - Radar
RADAR.....................................................................................................ADJUST AS APPROPRIATE
Gain must be manually set to +4, when MULTISCAN selector is set to AUTO and when flying below
FL 200.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-16 P 5/8
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
STANDARD OPERATING PROCEDURES - DESCENT PREPARATION
1. If the weather is good, or not significant, in order to check that the radar is operating
correctly: down tilt until displaying ground echoes.
2. If the weather display is ambiguous or unexpected, in order to better analyze the weather
situation, use manual tilt according to standard technique.
3. In particular below FL 200, for situations with low-level weather, weather with low
reflectivity or in front of suspected active cells, the flight crew should switch to Manual
mode and adjust the tilt setting downward until the weather is detected or the ground
clutter appears on the upper part of the display.
4. In addition, the flight crew may increase the manual gain control to display lower
reflectivity targets. The manual gain control can be increased in both AUTO and Manual
modes to display lower levels of weather. In both cases, ground clutter may also be
displayed as a result of low settings and/or increased gain.
Ident.: PRO-NOR-SOP-16-A-00011545.0001001 / 03 MAR 14
Impacted by TDU: 00013353 Descent Preparation - Radar
RADAR.....................................................................................................ADJUST AS APPROPRIATE
Ident.: PRO-NOR-SOP-16-A-00011558.0004001 / 02 MAY 17
CAUTION
In icing conditions (Refer to LIM-ICE_RAIN Definition of Icing Conditions), the flight
crew must turn on the engine anti-ice and should not wait until seeing ice building
up.
ENG ANTI-ICE pb-sw ........................................................................................................... AS RQRD
Engine anti-ice must be set to ON before and during descent, event if the SAT is below -40 °C (-40
°F).
When ENG ANTI ICE is ON, the FADEC selects a higher idle thrust which gives better protection
against flame-out.
WING ANTI ICE pb-sw .........................................................................................................AS RQRD
When icing conditions are encountered:
‐ The flight crew may turn on the wing anti-ice to prevent ice accretion on the wing leading edge.
‐ The flight crew must turn on the wing anti-ice if there is evidence of ice accretion, such as ice on
the visual indicators, or on the wipers, or with the SEVERE ICE DETECTED alert. This is to
remove any ice accumulation from the wing leading edge.
ANTI ICE ON reduces the descent path angle (when the engines are at idle). The pilot can
compensate for this by increasing the descent speed, or by extending up to half speedbrakes.
Ident.: PRO-NOR-SOP-16-A-00011557.0001001 / 03 MAR 14
DESCENT CLEARANCE...........................................................................................................OBTAIN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-16 P 6/8
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT PREPARATION
CLEARED ALTITUDE ON FCU...................................................................................................... SET
When clearance is obtained, set the ATC -cleared altitude (FL ) on the FCU (also considering what is
the safe altitude).
If the lowest safe altitude is higher than the ATC -cleared altitude, check with the ATC that this
constraint applies.
If it is confirmed, set the FCU altitude to the safe altitude, until it is safe to go to the ATC-cleared
altitude.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SOP-16 P 7/8
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT PREPARATION
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SOP-16 P 8/8
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT
DESCENT INITIATION
Ident.: PRO-NOR-SOP-17-00011541.0001001 / 03 NOV 14
Applicable to: ALL
DESCENT................................................................................................................................ INITIATE
The normal method of initiating the descent is to select DES mode at the FMGS calculated top of
descent (T/D).
If ATC requires an early descent:
Use DES mode which will guide the aircraft down at a lower vertical speed in order to converge
on the required descent path. (The pilot may use a V/S of -1 000 ft/min).
If ATC delays the descent:
Beyond T/D, the PFD and the MCDU display either "DECELERATE" or "T/D REACHED"
message. This suggests to the crew that it starts reducing speed towards green dot speed (with
ATC permission). When cleared to descend, select DES mode with managed speed active.
DESCENT MONITORING
Ident.: PRO-NOR-SOP-17-00011542.0003001 / 23 DEC 14
Applicable to: ALL
PF MCDU .............................................................................................................. PROG /PERF DES
PF MCDU should be set to PROG or PERF DES page:
‐ PROG page in order to get VDEV or RQD DIST TO LAND/DIRECT DIST TO DEST information
‐ PERF DES in order to get predictions down to any inserted altitude in DES /OP DES modes and
EXP mode .
PM MCDU .................................................................................................................................. F-PLN
DESCENT............................................................................................................... MONITOR/ADJUST
Refer to PRO-NOR-SRP-01-60 Descent Monitoring - DES Mode Engaged
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
PRO-NOR-SOP-17 P 1/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT
‐ When flying in NAV mode, use DES mode.
The aircraft descends along the descent flight path: the PFD and PROG page display VDEV, and
so it can be monitored. All constraints of the flight plan are taken into account for the guidance.
‐ When the aircraft is flying in HDG or TRK mode, and thus out of the lateral F-PLN , DES mode is
not available.
The ND s show a level-off symbol along the flight path. Its position is based on the current
active modes .AP /FD and A/THR
The flight crew can use this symbol to monitor the descent.
MCDU predictions assume a return to the lateral F-PLN and descent flight path.
Note that whenever the lateral mode is changed from NAV to HDG /TRK the vertical mode reverts
to V/S at the value pertaining at the time of the mode change.
‐ From time to time during stabilized descent, the flight crew may select FPA to check that the
remaining distance to destination is approximately the altitude change required divided by the FPA
in degrees.
FPA (°) = ΔFL/DIST (NM)
DESCENT ADJUSTMENT
Applicable to: ALL
Ident.: PRO-NOR-SOP-17-A-00011543.0002001 / 09 MAR 15
To increase the rate of descent:
‐ Increase descent speed (by use of selected speed) if comfort and ATC permit. It is economically
better (Time/Fuel) than the following procedures.
‐ Maintain high speed as long as possible. (SPD LIM may be suspended, subject to ATC
clearance).
‐ If the aircraft is high and at high speed, it is more efficient to keep the high speed to ALT* and
decelerate, rather than to mix descent and deceleration.
‐ If the aircraft goes below the desired profile, use SPEED and the V/S mode to adjust the rate of
descent.
Note:
EXPEDITE DESCENT.
If a high rate of descent is required, push the EXPED pushbutton on the FCU . The
target speed for the descent now becomes M 0.8 or 340 kt, whichever is lower. The FMA
will display THRIDLE/EXP DES/NAV.
To return to DES mode, push the FCU ALT knob.
To return to SPEED/V/S modes, pull the FCU V/S knob.
In all cases, monitor the FMA to ensure that the mode engages properly.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-NOR-SOP-17 P 2/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT
Ident.: PRO-NOR-SOP-17-A-00011544.0001001 / 03 MAR 14
If engine anti-ice is selected in descent, the flight idle is increased. So, to maintain the rate of
descent that the airplane had before engine anti-ice selection it may be necessary to use up to half
speedbrakes to maintain the required rate of descent, in OPEN DES vertical mode. If the rate of
descent has to be increased, full speedbrakes may be used.
In DES mode: If the aircraft is on, or below, the flight path and the ATC requires a higher rate of
descent, do not use speedbrakes because the rate of descent is dictated by the planned flight path.
Thus, the A/THR may increase thrust to compensate for the increase in drag. In this case, use OPEN
DES with speedbrakes.
Note:
1. If speedbrakes are used above 315 kt/M .75, with the AP engaged, their rate of retraction
is low (total time for retraction from full extension is approximately 25 s). The ECAM
memo page displays SPD BRAKES in amber until retraction is complete.
2. In order to avoid overshooting the altitude, due to speedbrake retraction in ALT* mode,
retract the speedbrakes at least 2 000 ft before the selected altitude.
Ident.: PRO-NOR-SOP-17-A-00011546.0001001 / 14 JAN 16
BAROMETRIC REFERENCE.......................................................................................................... SET
Set QNH on the EFIS control panel and on the standby altimeter, when approaching the transition
level and when cleared for an altitude.
Crosscheck BARO settings and altitude readings.
Ident.: PRO-NOR-SOP-17-A-00011548.0001001 / 13 AUG 10
ECAM STATUS..........................................................................................................................CHECK
‐ Check that there is no status reminder on the upper ECAM display.
‐ If there is a status reminder, check the aircraft STATUS.
‐ Check the ECAM status page before completing the approach checks. Take particular note of any
degradation in landing capability, or any other aspect affecting the approach and landing.
Ident.: PRO-NOR-SOP-17-A-00021715.0001001 / 04 SEP 17
AT 10 000 FT
LAND lights selector.................................................................................................................... SET
LAND lights may be switched ON, according to the airline policy/regulatory recommendations.
SEAT BELTS sw........................................................................................................................... ON
EFIS option pb.......................................................................................................................... CSTR
Select CSTR on both sides.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PRO-NOR-SOP-17 P 3/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT
ILS/LS pb............................................................................................................................AS RQRD
Press the ILS/LS pb, if one of the following approaches is planned:
‐ ILS, GLS , MLS
‐ ILS G/S out, LOC only or LOC B/C
‐ Approach with the FLS function
The flight crew checks that:
‐ Deviation scales are displayed on the PFD
‐ The IDENT is properly displayed on the PFD
RAD NAVAIDS............................................................................................SELECTED/IDENTIFIED
Ensure that appropriate radio NAVAIDS are tuned and identified.
For NDB approaches, manually select the reference NAVAID.
Ident.: PRO-NOR-SOP-17-A-00015500.0001001 / 03 MAR 14
ENG MODE selector..............................................................................................................AS RQRD
‐ Select IGN if the runway is covered with standing water, or if heavy rain or severe turbulence is
expected during approach or go-around area.
Ident.: PRO-NOR-SOP-17-A-00015501.0001001 / 03 MAR 14
NAV ACCURACY....................................................................................................................... CHECK
On aircraft equipped with GPS primary, no navigation accuracy check is required, as long as GPS
PRIMARY function is available.
Otherwise, crosscheck NAV ACCURACY using the PROG page (BRG /DIST computed data), and
the ND (VOR /DME raw data).
APPROACH CHECKLIST
Ident.: PRO-NOR-SOP-17-00014491.0001001 / 03 MAR 14
Applicable to: ALL
APPROACH CHECKLIST
APPROACH CHECKLIST............................................................................................PERFORMED
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
PRO-NOR-SOP-17 P 4/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT
10 000 FT FLOW PATTERN
Ident.: PRO-NOR-SOP-17-00020073.0001001 / 17 MAR 17
Applicable to: ALL
10 000 ft FLOW PATTERN
GLG A318/A319/A320/A321 For A/C: HC-CRU
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E
PRO-NOR-SOP-17 P 5/6
05 SEP 17
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FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - DESCENT
Intentionally left blank
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PRO-NOR-SOP-17 P 6/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES - APPROACH
FLIGHT CREW
OPERATING MANUAL
Approach General
INTRODUCTION
Ident.: PRO-NOR-SOP-18-A-00014490.0001001 / 29 MAY 13
Applicable to: ALL
The APPROACH section provides the standard operating procedures for the following approach
types:
‐ ILS / MLS / GLS approaches
‐ Conventional approaches: VOR , VOR -DME , NDB , NDB -DME
‐ Approaches based on a LOC signal without any G/S signal: LOC ONLY, ILS G/S OUT, LOC B/C
‐ RNAV approaches including:
• RNAV (GNSS) approaches with LNAV minimum or LNAV/VNAV minimum
• RNAV (RNP ) approaches for which Authorization is Required (AR) - If capability installed.
Note:
In relation to the names in the ICAO Performance-Based Navigation (PBN) Manual:
‐ "RNP APCH operations" corresponds to RNAV (GNSS) approaches
‐ "RNP AR APCH operations" corresponds to RNAV (RNP) approaches.
CROSS-REFERENCE TABLE
Ident.: PRO-NOR-SOP-18-A-00014489.0001001 / 29 MAY 13
Applicable to: ALL
This table provides Guidance Modes that may be used depending on the Approach Types.
LOC G/S
Guidance Modes per Approach Types
FINAL APP
LOC FPA
NAV FPA
TRK FPA
ILS / MLS
/ GLS
Refer to APPR
using LOC G/S
N/A
N/A
N/A
N/A
LOC ONLY
ILS G/S OUT
N/A
N/A
Refer to APPR
using FPA
Guidance
N/A
N/A
LOC B/C
N/A
N/A
N/A
N/A
RNAV (GNSS)
with LNAV/VNAV
minima
Refer to APPR
using FPA
Guidance
N/A
Refer to APPR
using FINAL APP
N/A
Not Authorized
Not Authorized
RNAV (GNSS)
with LNAV minima
N/A
Refer to
APPR using
FINAL APP (1)
N/A
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
Refer to APPR
using FPA
Not Authorized
Guidance
Continued on the following page
PRO-NOR-SOP-18-A P 1/6
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES - APPROACH
FLIGHT CREW
OPERATING MANUAL
Continued from the previous page
RNAV (GNSS)
with LPV minima
VOR
VOR -DME
NDB
NDB -DME
(1)
LOC G/S
Guidance Modes per Approach Types
FINAL APP
LOC FPA
NAV FPA
TRK FPA
N/A
Not Authorized
N/A
Not Authorized
Not Authorized
N/A
Refer to
APPR using
FINAL APP (1)
N/A
Refer to APPR
using FPA
Guidance
Refer to APPR
using FPA
Guidance
The FINAL APP is the recommended guidance mode for this type of approach.
For Visual Approach, Refer to Visual Approach
For Circling Approach, Refer to Circling Approach
FLYING REFERENCE
Ident.: PRO-NOR-SOP-18-A-00014488.0001001 / 29 MAY 13
Applicable to: ALL
Use the following recommended flying reference:
‐ In vertical managed modes: HDG -V/S reference associated with the FD crossbars
‐ In vertical selected modes: TRK -FPA reference associated with FPD.
STABILIZATION CRITERIA
Ident.: PRO-NOR-SOP-18-A-00014487.0002001 / 06 DEC 16
Applicable to: ALL
The stabilization height is defined as one of the following:
‐ 1 000 ft above airfield elevation (AAL )in Instrument Meteorological Conditions (IMC), or
‐ 500 ft above airfield elevation (AAL ) in Visual Meteorological Conditions (VMC), or
‐ Any other height defined in Operator policies or regulations.
In order for the approach to be stabilized, all of the following conditions must be satisfied before, or at
the stabilization height:
‐ The aircraft is on the correct lateral and vertical flight path
‐ The aircraft is in the desired landing configuration
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to D →
PRO-NOR-SOP-18-A P 2/6
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES - APPROACH
FLIGHT CREW
OPERATING MANUAL
‐ The thrust is stabilized, usually above idle, and the aircraft is at target speed for approach
Note:
In IMC , if the ATC requests a speed constraint that is not compatible with the speed
and thrust stabilization at 1 000 ft AAL, a later speed and thrust stabilization can be
acceptable provided that:
‐ The aircraft is in deceleration toward the target approach speed
‐ The flight crew stabilizes speed and thrust as soon as possible and not later than
500 ft AAL.
‐ The flight crew does not detect any excessive flight parameter deviation.
If one of the above-mentioned conditions is not satisfied, the flight crew must initiate a go-around,
unless they estimate that only small corrections are required to recover stabilized approach
conditions.
Note:
If the predicted tailwind at landing is greater than 10 kt, decelerated approach is not
permitted, and the aircraft speed should be stabilized at around VREF + 5 kt in final.
APPROACH SPEED TECHNIQUE
Ident.: PRO-NOR-SOP-18-A-00014485.0001001 / 29 MAY 13
Applicable to: ALL
DECELERATED APPROACH
The decelerated approach with FD or AP /FD guidance is the standard flying technique for ILS /
MLS / GLS approaches and approaches using FLS or FINAL APP guidance.
EARLY STABILIZED APPROACH
Under certain circumstances, the flight crew may decide to reduce the speed down to VAPP in the
landing configuration at the Final Descent Point (i.e. approach via selected guidance, high glide
path angle, low altitude intermediate approach, etc.). In order to obtain a valuable deceleration
pseudo waypoint and to ensure a timely deceleration, the flight crew should enter VAPP as a
speed constraint at the Final Descent Point.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E
PRO-NOR-SOP-18-A P 3/6
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
DISCONTINUED APPROACH
Ident.: PRO-NOR-SOP-18-A-00015226.0001001 / 03 DEC 13
Applicable to: ALL
In order to discontinue an approach when the aircraft is at or above the altitude selected on the
FCU, the flight crew can either:
‐ Apply the GO AROUND procedure, or
‐ Apply the discontinued approach technique.
When the aircraft is below the FCU altitude, the flight crew must apply the GO AROUND
procedure.
If at or above the FCU altitude:
Announce "CANCEL APPROACH".
To disarm any AP/FD approach mode, press APPR pb or LOC pb.
Note:
Valid only for ILS / MLS / GLS / FLS or FINAL APP guidance.
Select lateral mode as required (NAV or HDG mode).
Select vertical mode as required (level off or adjust V/S).
Select SPEED and adjust.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PRO-NOR-SOP-18-A P 4/6
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
If F-PLN has no destination anymore:
Perform a LAT REV at the last waypoint and redefine the destination in the NEW DEST field.
Note:
1. The FMS does not automatically string the previous flown approach in the active F-PLN
when the aircraft overflies the last waypoint. The FMS has no more destination in the
F-PLN.
2. Because the thrust levers are not set to TOGA detent, the FMS remains in approach
phase.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
PRO-NOR-SOP-18-A P 5/6
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Intentionally left blank
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PRO-NOR-SOP-18-A P 6/6
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Aircraft Configuration Management
INITIAL APPROACH
Applicable to: ALL
Ident.: PRO-NOR-SOP-18-B-A-00014494.0001001 / 29 MAY 13
GENERAL
The initial approach procedure described here is a general guidance whatever the type of
approach expected.
Ident.: PRO-NOR-SOP-18-B-A-00014493.0001001 / 03 MAR 14
INITIAL APPROACH
F-PLN SEQUENCING...........................................................................................................ADJUST
‐ The NAV mode will be available after GO AROUND if the F-PLN is properly sequenced. A good
cue to monitor the proper F-PLN sequencing is the TO waypoint on the upper right side of the
ND, which should remain meaningful.
‐ In NAV mode, the F-PLN will sequence automatically.
‐ In HDG /TRK mode, the F-PLN will sequence automatically only if the aircraft flies close to the
F-PLN route.
APPROACH PHASE............................................................................................CHECK/ACTIVATE
‐ If the aircraft overflies the DECEL pseudo waypoint in NAV mode, the APPR phase activates
automatically.
‐ If the aircraft is in HDG /TRK mode, approximately 15 NM from touchdown, activate and confirm
APPROACH phase on the MCDU (PERF DES page).
MANAGED SPEED................................................................................................................ CHECK
‐ If ATC requires a particular speed, use selected speed. When the ATC speed constraint no
longer applies, return to managed speed.
FLIGHT PATH....................................................................................................................MONITOR
‐ In NAV mode, use VDEV information on the PFD and PROG page.
‐ In HDG /TRK mode, use the energy circle on ND representing the required distance to land.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A→
PRO-NOR-SOP-18-B P 1/8
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
SPEED BRAKES lever.......................................................................................................AS RQRD
‐ If the flight crew uses the speed brakes to increase the rate of deceleration or to increase the
rate of descent, the VLS will increase as well:
• The flight crew should ensure that appropriate speed margin exists before the extension of
the speed brakes
• If the speed brakes are extended, the flight crew should ensure that appropriate speed
margin exists before the beginning of a turn.
This will avoid the activation of the Alpha-Floor protection.
Note:
In clean configuration, the VLS with speed brakes fully extended may be higher than
green dot speed or VFE FLAP 1.
Ident.: TDU / PRO-NOR-SOP-18-B-A-00014648.0003001 / 03 MAR 14
Impacted DU: 00014647 Initial Approach - Radar
RADAR
RADAR................................................................................................. ADJUST AS APPROPRIATE
‐ Gain must be manually set to +4 when MULTISCAN selector is set to AUTO and when flying
below FL 200.
‐ If the weather is good, or not significant, in order to check that the radar is operating correctly:
down tilt under displaying ground echoes.
‐ If the weather display is ambiguous or unexpected, in order to better analyze the weather
situation, use manual tilt according to standard technique.
‐ In particular below FL 200, for situations with low level weather, weather with low reflectivity or
in front of suspected active cells, the flight crew should switch to manual mode and adjust the tilt
setting downward until the weather is detected or the ground clutter appears on the upper part
of the display.
‐ In addition, the flight crew may increase the manual gain control to display lower reflectivity
targets. The manual gain control can be increased in both AUTO and manual modes to display
lower levels of weather. In both cases, ground clutter may also be displayed as a result of low
settings and/or increased gain.
Ident.: PRO-NOR-SOP-18-B-A-00014647.0001001 / 29 MAY 13
Impacted by TDU: 00014648 Initial Approach - Radar
RADAR
RADAR................................................................................................. ADJUST AS APPROPRIATE
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-NOR-SOP-18-B P 2/8
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Ident.: PRO-NOR-SOP-18-B-A-00014492.0001001 / 29 MAY 13
NAVIGATION ACCURACY
NAV ACCURACY...............................................................................................................MONITOR
‐ When GPS PRIMARY is available, no NAV ACCURACY monitoring is required.
‐ If GPS PRIMARY is lost, or GPS not installed, check on PROG page that the required
navigation accuracy is appropriate to the phase of flight.
‐ If NAV ACCURACY is LOW, at least one ND must be in ROSE LS /VOR depending on the
approach.
INTERMEDIATE/FINAL APPROACH
Applicable to: ALL
Ident.: PRO-NOR-SOP-18-B-B-00014501.0001001 / 29 MAY 13
GENERAL
The intermediate and final approach procedure described here is general guidance whatever the
type of approach expected.
Ident.: PRO-NOR-SOP-18-B-B-00014500.0001001 / 17 MAR 17
AT GREEN DOT SPEED
CAUTION
The flight crew should avoid extended flight in icing conditions with the slats
extended.
FLAPS 1............................................................................................................................... ORDER
FLAPS 1................................................................................................................................SELECT
‐ FLAPS 1 should be selected more than 3 NM before the Final Descent Point.
‐ Check deceleration toward "S" speed.
‐ For decelerated approaches, the aircraft must reach or be established on the final descent with
FLAPS 1 and "S" speed at or above 2 000 ft AGL.
‐ If the aircraft does not decelerate on the flight path or aircraft speed is significantly higher than
"S" speed, extend the landing gear in order to slow down. The use of speedbrakes is possible.
The flight crew should be aware that the use of speedbrakes causes an increase in VLS.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
PRO-NOR-SOP-18-B P 3/8
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
TCAS Mode selector.................................................................................................... TA or TA /RA
‐ FAA recommends to select TA only mode:
• In case of known nearby traffic which is in visual contact
• At particular airports and during particular procedures identified by an Operator as having
a significant potential for unwanted or inappropriate resolution advisories (closely spaced
parallel runways, converging runway, low terrain along the final approach, etc.).
Ident.: PRO-NOR-SOP-18-B-B-00014499.0001001 / 09 MAR 15
AT 2 000 FT AGL MINIMUM
FLAPS 2............................................................................................................................... ORDER
FLAPS 2................................................................................................................................SELECT
‐ Check deceleration toward "F" speed.
‐ For ILS / MLS / GLS and approaches using FLS , if the aircraft intercepts the flight
path below 2 000 ft AGL, select FLAPS 2 at one dot below the flight path.
‐ If the aircraft speed is significantly higher than "F" speed on the flight path, or the aircraft does
not decelerate on the flight path, extend the landing gear in order to slow down the aircraft. The
use of speed brakes is not recommended.
‐ When the speed brakes are deployed, extending the flaps beyond FLAPS 1 may induce a
slight roll movement, and in calm conditions a small lateral control asymmetry may remain until
disturbed by a control input or by an atmospheric disturbance.
Ident.: PRO-NOR-SOP-18-B-B-00014498.0001001 / 05 JAN 15
WHEN FLAPS ARE AT 2
L/G DOWN ............................................................................................................................ORDER
L/G lever...................................................................................................................SELECT DOWN
AUTO BRK ........................................................................................................................CONFIRM
‐ If the runway conditions have changed from the approach briefing, consider another braking
mode.
GROUND SPOILERS ................................................................................................................ARM
NOSE sw.....................................................................................................................................TAXI
RWY TURN OFF sw..................................................................................................................... ON
Ident.: PRO-NOR-SOP-18-B-B-00014497.0002001 / 20 MAR 17
WHEN LANDING GEAR IS DOWN
FLAPS 3.................................................................................................................................ORDER
FLAPS 3................................................................................................................................SELECT
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PROCEDURES
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
ECAM WHEEL SD page ...................................................................................................... CHECK
‐ WHEEL SD page appears below 15 500 ft when landing gear is extended.
‐ Check for three green indications on the landing gear indicator panel. At least one green triangle
on each landing gear strut on the WHEEL SD page is sufficient to indicate that the landing gear
is downlocked. Rely also on the “LDG GEAR DN ” green LDG MEMO message to confirm that
the landing gear is downlocked.
If residual pressure is indicated on the triple indicator:
RESIDUAL BRAKING PROC........................................................................................... APPLY
‐ Due to the accomplishment of the alternate braking functional test after the landing gear is
downlocked, brief brake pressure indications may be observed on BRAKES PRESS.
FLAPS FULL.......................................................................................................................... ORDER
FLAPS FULL......................................................................................................................... SELECT
‐ Retract the speed brakes before selecting FLAPS FULL to prevent a pitch down when the
speed brakes automatically retract.
‐ Check deceleration towards VAPP.
‐ Check correct TO waypoint on the ND.
A/THR........................................................................................CHECK IN SPEED MODE OR OFF
WING ANTI-ICE pb-sw................................................................................................................OFF
‐ Switch the WING ANTI ICE pb-sw to ON, only in severe icing conditions.
SLIDING TABLE ...............................................................................................................STOW
EFB/eQRH (with no mounted equipment)............................................................................... STOW
LDG MEMO...........................................................................................................CHECK NO BLUE
CABIN REPORT................................................................................................................. RECEIVE
CABIN CREW........................................................................................................................ ADVISE
LANDING CHECKLIST................................................................................................... COMPLETE
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22 MAR 17
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
FLIGHT PARAMETERS.....................................................................................................MONITOR
‐ The PF announces any FMA modification.
‐ The PM calls out, if:
• The speed goes lower than the speed target -5 kt , or greater than the speed target +10 kt
• The pitch attitude goes lower than -2.5 °, or greater than +10 ° nose up
• The bank angle becomes greater than 7 °
• The descent rate becomes greater than 1 000 ft/min
‐ Following PM flight parameter exceedance callout, the suitable PF response will be:
• Acknowledge the PM callout, for proper crew coordination purposes
• Take immediate corrective action to control the exceeded parameter back into the defined
stabilized conditions
• Assess whether stabilized conditions will be recovered early enough prior to landing,
otherwise initiate a go-around.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-18-B P 6/8
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Ident.: PRO-NOR-SOP-18-B-B-00014495.0001001 / 29 MAY 13
PATTERN (DECELERATED)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-NOR-SOP-18-B P 7/8
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SOP-18-B P 8/8
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES - APPROACH
FLIGHT CREW
OPERATING MANUAL
Aircraft Guidance Management
APPROACH USING LOC G/S GUIDANCE
Applicable to: ALL
Ident.: PRO-NOR-SOP-18-C-A-00014508.0001001 / 29 MAY 13
GENERAL
The following items are to be performed in addition to previous SOP chapters for ILS / MLS /
GLS approach.
Ident.: PRO-NOR-SOP-18-C-A-00020896.0001001 / 20 MAR 17
DESCENT PREPARATION
APPROACH MINIMUM..................................................................................................DETERMINE
‐ For CATII, CATIII approaches, always choose the lowest achievable minimum. The approach
minimum is limited by:
•
•
•
•
Crew qualification
Airline Operating Manual requirement
Aircraft technical status
Airport status
‐ For CATIII with no DH, the flight crew should enter "NO" in the DH field of the MCDU to avoid
false "HUNDRED ABOVE" or "MINIMUM" auto callouts which would not be applicable.
APPROACH BRIEFING.................................................................................................... PERFORM
For CATII, CATIII approaches, review the following items on top of the usual briefing:
‐ Task sharing and callouts
‐ Management of degraded guidance
‐ Low visibility procedures at the airport
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SOP-18-C P 1/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Ident.: PRO-NOR-SOP-18-C-A-00014509.0001001 / 09 FEB 16
INITIAL/INTERMEDIATE APPROACH
APPR pb on FCU................................................................................................................... PRESS
‐ Press the APPR pb when:
• Cleared for the approach
• On the intercept trajectory for the final approach course
• LOC deviation is available.
This arms the LOC and G/S modes.
Note:
In NAV mode, the aircraft may leave the F-PLN to capture the LOC.
‐ LOC and/or G/S capture modes will engage no sooner than 3 s after being armed.
‐ ICAO defines the envelope where the quality of the G/S signal ensures a normal capture. This
envelope is within 10 NM, ±8 ° of the centerline of the ILS glide path and up to 1.75 θ and down
to 0.3 θ (θ = nominal glide path angle). When arming the approach well outside of the normal
G/S capture envelope, a spurious G/S * engagement may occur due to a wrong G/S deviation
signal. Whenever the pilot notices the pitch movement, or the spurious G/S *, or the trajectory
deviation, he will immediately disconnect the AP , if engaged, to re-establish a normal attitude
and will disengage APPR mode. It is then recommended to arm/rearm APPR (ILS) mode within
the normal capture zone.
BOTH APs........................................................................................................................... ENGAGE
‐ When APPR mode is selected, AP 1 and AP2 should be engaged.
‐ Above 5 000 ft AGL , the FMA displays CAT 1.
‐ Below 5 000 ft AGL , the FMA displays the correct approach capability for the intended
approach.
LOC.......................................................................................................................... CHECK ARMED
G/S........................................................................................................................... CHECK ARMED
LOC CAPTURE..................................................................................................................MONITOR
G/S CAPTURE...................................................................................................................MONITOR
GO AROUND ALTITUDE............................................................................................................ SET
Ident.: PRO-NOR-SOP-18-C-A-00014510.0002001 / 03 MAR 14
GLIDE INTERCEPTION FROM ABOVE
The following procedure should only be applied when established on the localizer. The flight crew
must react without delay to meet the stabilization criteria.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-18-C P 2/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
In order to get the best rate of descent when cleared by ATC and below the limiting speeds, the
flight crew should lower the landing gear and select flaps as required (at least CONF 2 should be
selected to ensure that the aircraft speed will not increase).
If above the glideslope:
APPR mode .......................................................................................... ARM / CHECK ARMED
FCU ALTITUDE............................................................................. SET ABOVE A/C ALTITUDE
V/S MODE...................................................................................................................... SELECT
‐ Select V/S 1 500 ft/min initially. V/S in excess of 2 000 ft/min will result in the speed
increasing towards VFE.
‐ When reaching VFE , the AP maintains VFE and reduces the V/S without MODE
REVERSION.
Ident.: PRO-NOR-SOP-18-C-A-00014511.0001001 / 04 JUL 17
FINAL APPROACH
FLIGHT PARAMETERS.....................................................................................................MONITOR
‐ The PM calls out if excessive deviation occurs:
• LOC: ½ dot
• GLIDE: ½ dot
Refer to PRO-NOR-SOP-90 Approach
AT 350 ft RA
LAND mode................................................................................... CHECK ENGAGED/ANNOUNCE
If no LAND mode, autoland is not authorized.
FOR CAT I, CAT II, CAT III WITH DH APPROACH
AT ENTERED MINIMUM +100 ft
ONE HUNDRED ABOVE...............................................................MONITOR OR ANNOUNCE
AT ENTERED MINIMUM
MINIMUM....................................................................................... MONITOR OR ANNOUNCE
Below minimum, the visual references must be the primary reference until landing.
For more information regarding transition to visual references, Refer to
FCTM/PR-NP-SOP-250 Transition to Visual References.
If visual references are sufficient:
CONTINUE.......................................................................................................ANNOUNCE
AP.........................................................................................................................AS RQRD
For Minimum Use Height of the AP Refer to LIM-AFS-10 Flight Management Function
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-18-C P 3/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
For Manual Landing and Autoland procedure Refer to PRO-NOR-SOP-19 Landing - Flare
If visual references are not sufficient:
GO AROUND................................................................................................... ANNOUNCE
Initiate a go around.
FOR CAT III WITHOUT DH APPROACH
At 100 ft (Alert Height) if no failure
CONTINUE............................................................................................................. ANNOUNCE
Ident.: PRO-NOR-SOP-18-C-A-00021062.0002001 / 31 AUG 17
MANAGEMENT OF DEGRADED GUIDANCE
EARLY/UNTIMELY FLARE MODE ENGAGEMENT
‐ Perform a go around (thrust levers set to TOGA), or
‐ Disconnect AP , set both FDs to OFF and continue the approach using raw data or external
visual references.
In association to an early/untimely FLARE mode engagement on the FMA, the following effects
may occur:
‐ On the Primary Flight Display (PFD):
• The RA height indication may be frozen at a positive or negative value,
• Discrepancies between both PFDs may happen on the following indications:
▪ RA heights,
▪ FD orders,
▪ FMA indications when both APs are engaged.
‐ Warnings and/or Callouts:
• Untimely activation of the AUTOLAND warning light. Refer to DSC-22_30-30 Autoland
Warning,
• Untimely Terrain Awareness and Warning System (TAWS) alerts,
• Untimely or absence of “RETARD" callout,
• Untimely L/G GEAR NOT DOWN ECAM warning,
• Absence or interruption of RA automatic callout (height announcement),
‐ On the System Display (SD): A pulsing cabin differential pressure advisory may appear on
the ECAM - CAB PRESS PAGE
Note:
This ECAM advisory has no consequence on the real cabin pressure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-18-C P 4/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
FOR CAT II, CAT III OPERATIONS
In the case of:
‐ Amber caution (single chime), or
‐ Landing capability degradation.
Above 1000 ft:
ECAM / QRH PROCEDURE................................................................................ COMPLETE
REQUIRED EQUIPMENT............................................................................................CHECK
Refer to QRH/OPS Required Equipment for CAT2 and CAT3
APPROACH AND LANDING CAPABILITY................................................................. CHECK
If required:
RVR..............................................................................................................................CHECK
DH...............................................................................................................................ADJUST
BRIEFING................................................................................................................ CONFIRM
If the flight crew does not complete all the above actions at 1 000 ft:
GO AROUND................................................................................................... PERFORM
Below 1000 ft:
If external visual references are not sufficient:
GO AROUND................................................................................................... PERFORM
Below 100 ft (Alert Height) for CAT 3 DUAL:
Approach may be continued unless autoland light comes on.
In the case of Autoland warning light:
Visual references not sufficient:
GO AROUND................................................................................................... PERFORM
Visual references sufficient:
Approach may be continued manually
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SOP-18-C P 5/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
APPROACH USING FINAL APP GUIDANCE
Applicable to: ALL
Ident.: PRO-NOR-SOP-18-C-C-00014521.0002001 / 29 MAY 13
GENERAL
The following items are to be performed in addition to previous SOP chapters in the following
cases:
‐ RNAV (GNSS) approaches with LNAV and LNAV/VNAV minima
‐ Conventional approaches based on VOR or NDB using FINAL APP guidance.
Ident.: PRO-NOR-SOP-18-C-C-00014522.0003001 / 09 SEP 14
AIRCRAFT EQUIPMENT
For RNAV (GNSS) approaches, Refer to PRO-SPO-51 RNP APCH / RNAV(GNSS) - Required
RNP APCH Equipment
Ident.: PRO-NOR-SOP-18-C-C-00015860.0001001 / 09 SEP 14
FLIGHT PREPARATION
For RNAV (GNSS ) approaches, GPS PRIMARY availability should be confirmed.
Refer to PRO-NOR-SOP-02 GPS PRIMARY Availability (If Installed)
Ident.: PRO-NOR-SOP-18-C-C-00014524.0002001 / 08 AUG 17
DESCENT PREPARATION
WEATHER AND LANDING INFORMATION.........................................................................OBTAIN
‐ The FMS vertical profile does not take into account the effect of low OAT. Therefore, vertical
managed guidance:
• Must not be used when the actual OAT is below the minimum temperature indicated on the
approach chart or defined by the Operator, or
• May not be used when temperature corrections are required (FINAL APP mode may not
engage).
‐ For RNAV (GNSS ) approach with LNAV VNAV minima, use of QNH from a remote station is
prohibited.
F-PLN A page........................................................................................................................ CHECK
‐ If a TOO STEEP PATH is displayed after the Final Descent Point (FDP ), do not use FINAL
APP guidance for approach. Use NAV FPA , TRK FPA or FLS for approach.
‐ 0.1 degree of difference between the MCDU and the charted final vertical path is acceptable
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-NOR-SOP-18-C P 6/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
‐ 1 degree of difference between the MCDU and the charted final lateral track is acceptable
Note:
A higher lateral track value can be acceptable if the navigation database has been
validated to exclude potential coding error.
‐ 3 degree of difference between the MCDU and the charted final lateral track is acceptable for
conventional radio NAVAID approach.
PROG page.....................................................................................................................COMPLETE
‐ Insert the reference RWY threshold in the BRG /DIST field for position monitoring during
approach.
GO AROUND STRATEGY................................................................................................... REVIEW
‐ The briefing should include a review of the "Management of Degraded Navigation" chapter.
Ident.: PRO-NOR-SOP-18-C-C-00014525.0003001 / 23 JUN 15
DESCENT
At 10 000 ft:
NAV ACCURACY................................................................................................................... CHECK
‐ If NAV accuracy is LOW, use TRK FPA mode for approach (Refer to APPR using FPA
guidance).
For RNAV(GNSS) approach:
GPS PRIMARY................................................................................................................ CHECK
‐ GPS PRIMARY must be available on at least 1 FMS.
BARO REF...................................................................................................................................SET
‐ The vertical guidance requires a precise baro setting. The maximum acceptable discrepancy
between altimeters is 100 ft.
Ident.: PRO-NOR-SOP-18-C-C-00014526.0002001 / 08 AUG 17
INITIAL/INTERMEDIATE/FINAL APPROACH
POSITION.......................................................................................................................... MONITOR
‐ Check that ATC clearances allow the aircraft to fly through the capture area of vertical profile.
After a radar vectoring, consider a DIR TO RDL IN to sequence the F-PLN.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-18-C P 7/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
APPR pb on FCU ..................................................................................................................PRESS
Press the APPR pb when all of the following conditions are satisfied:
‐ The aircraft is cleared for approach
‐ TO waypoint is the Final Descent Point.
APP NAV.......................................................................................... CHECK ARMED or ENGAGED
FINAL....................................................................................................................... CHECK ARMED
‐ Check that the V/DEV scale is displayed on the PFD.
‐ At the Final Descent Point, a blue arrow on ND indicates that FINAL APP engagement
conditions are met.
At the Final Descent Point :
FINAL APP..........................................................................................................CHECK ENGAGED
GO AROUND ALTITUDE............................................................................................................ SET
FLIGHT PARAMETERS.....................................................................................................MONITOR
‐
‐
‐
‐
L2
L1
Monitor XTK error on ND.
Monitor V/DEV on PFD.
Crosscheck distances versus altitudes as published on the charts.
If approaching on a conventional radio NAVAID procedure, monitor the lateral and vertical
guidance using raw data.
‐ The PM calls out if excessive deviation occurs:
• XTK > 0.1 NM
• V/DEV > ½ dot
On the vertical scale, one dot corresponds to 100 ft. Thus ½ dot is 50 ft.
Refer to PRO-NOR-SOP-90 Approach
Ident.: PRO-NOR-SOP-18-C-C-00015015.0001001 / 29 MAY 13
AT ENTERED MINIMUM +100 FT
ONE HUNDRED ABOVE.......................................................................MONITOR OR ANNOUNCE
Ident.: PRO-NOR-SOP-18-C-C-00014527.0003001 / 04 JUL 17
AT ENTERED MINIMUM
MINIMUM...............................................................................................MONITOR OR ANNOUNCE
Below minimum, the visual references must be the primary references until landing.
For more information regarding transition to visual references, Refer to FCTM/PR-NP-SOP-250
Transition to Visual References.
If visual references are sufficient:
CONTINUE...............................................................................................................ANNOUNCE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-18-C P 8/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
At the latest at the MAP or Minimum Use Height of the AP (whichever occurs first):
AP .........................................................................................................................................OFF
‐ For Minimum Use Height of the AP, Refer to LIM-AFS-10 Autopilot Function
‐ The AP will automatically disengage at the MAP.
FD ............................................................................................................................... AS RQRD
CAUTION
‐ From minima down to the MAP the FD provides an additional guidance.
The FD must be switched off if the guidance is not relevant or not followed.
‐ After the MAP , disregard the FD as it reverts to HDG V/S.
If visual references are not sufficient:
GO AROUND...........................................................................................................ANNOUNCE
‐ Initiate a go around.
Ident.: PRO-NOR-SOP-18-C-C-00014528.0002001 / 23 JUN 15
MANAGEMENT OF DEGRADED NAVIGATION
For VOR and NDB approaches, be prepared to continue the approach with reference to
appropriate raw data by reverting to:
‐ NAV FPA, if the vertical guidance is not satisfactory
‐ TRK FPA, if the lateral guidance is not satisfactory.
For RNAV(GNSS) approaches with LNAV minima and LNAV/VNAV minima:
‐ Use the appropriate remaining AP /FDin the following cases:
• GPS PRIMARY LOST on one ND
• NAV ACCUR DOWNGRAD on one FMGS.
‐ Discontinue the approach in the following cases, if external visual references are not
sufficient to proceed visually:
• GPS PRIMARY LOST on both NDs
• XTK > 0.3 NM
• NAV FM /GPS POS DISAGREE on ECAM
• NAV ACCUR DOWNGRAD on both FMGS.
For RNAV(GNSS) approaches with LNAV/VNAV minima:
‐ Discontinue the approach in the case of deviation of 75 ft below the vertical path (V/DEV>¾
dot).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-NOR-SOP-18-C P 9/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
APPROACH USING FPA GUIDANCE
Applicable to: ALL
Ident.: PRO-NOR-SOP-18-C-E-00014561.0002001 / 29 MAY 13
GENERAL
The following items are to be performed in addition to previous SOP chapters in the following
cases:
‐ RNAV (GNSS ) approaches using mixed NAV FPA guidance with LNAV minima only
‐ Conventional approaches based on VOR and NDB using selected TRK FPA or mixed NAV FPA
guidance
‐ ILS G/S OUT, LOC ONLY and back course localizer approaches.
The approach is flown in TRK FPA when:
‐ The approach is not stored in the database or
‐ NAV accuracy is LOW.
Ident.: PRO-NOR-SOP-18-C-E-00014560.0003001 / 09 SEP 14
AIRCRAFT EQUIPMENT
For RNAV (GNSS) approaches, Refer to PRO-SPO-51 RNP APCH / RNAV(GNSS) - Required
RNP APCH Equipment
Ident.: PRO-NOR-SOP-18-C-E-00015861.0001001 / 09 SEP 14
FLIGHT PREPARATION
For RNAV (GNSS ) approaches, GPS PRIMARY availability should be confirmed.
Refer to PRO-NOR-SOP-02 GPS PRIMARY Availability (If Installed)
Ident.: PRO-NOR-SOP-18-C-E-00014558.0002001 / 20 SEP 16
DESCENT PREPARATION
F-PLN A page........................................................................................................................ CHECK
‐ If a TOO STEEP PATH message is displayed after the Final Descent Point (FDP ), disregard
the V/DEV or yoyo information on the PFD.
‐ For approaches using NAV FPA:
• 1 degree of difference between the MCDU and the charted final lateral track is acceptable.
• 3 degree of difference between the MCDU and the charted final lateral track is acceptable for
conventional radio NAVAID approach.
‐ In all other cases, use TRK FPA mode for approach.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PRO-NOR-SOP-18-C P 10/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
PROG page.....................................................................................................................COMPLETE
‐ Insert the reference RWY threshold in the BRG /DIST field for position monitoring during
approach.
GO AROUND STRATEGY................................................................................................... REVIEW
‐ The briefing should include a review of the "Management of Degraded Navigation" chapter.
Ident.: PRO-NOR-SOP-18-C-E-00014557.0003001 / 03 MAR 14
DESCENT
At 10 000 ft:
NAV ACCURACY................................................................................................................... CHECK
‐ If NAV accuracy is LOW, use TRK mode for approach.
For RNAV(GNSS) approach:
GPS PRIMARY................................................................................................................ CHECK
‐ GPS PRIMARY must be available on at least 1 FMS.
Ident.: PRO-NOR-SOP-18-C-E-00014556.0002001 / 21 MAR 17
INITIAL/INTERMEDIATE/FINAL APPROACH
LATERAL GUIDANCE MODE....................................................................... SET FOR APPROACH
‐ Arm NAV or LOC mode as appropriate.
For LOC ONLY and ILS G/S OUT:
LOC pb-sw ...................................................................................................................... PRESS
‐ Press the LOC pb-sw when cleared for approach and on the intercept trajectory for the final
approach course.
Note:
In NAV mode, the aircraft may leave the F-PLN to capture the LOC.
LOC .................................................................................................................. CHECK ARMED
CAUTION
Do not press the APPR pb
For back course localizer approaches:
TRK FPA MODE.....................................................................................USE FOR APPROACH
‐ Refer to FCTM/PR-NP-SOP-190-GUI Back Course Localizer Approach.
LATERAL PATH............................................................................................................. INTERCEPT
‐ Monitor NAV or LOC engagement as appropriate.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PRO-NOR-SOP-18-C P 11/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
TRK FPA pb (Bird)................................................................................................................SELECT
FPA FOR FINAL APPROACH.....................................................................................................SET
At 0.3 nm from the Final Descent Point:
FPA selector ............................................................................................................................. PULL
FPA MODE..........................................................................................................CHECK ENGAGED
‐ Check NAV FPA , TRK FPA or LOC FPA is engaged.
POSITION/FLIGHT PATH ................................................................................. MONITOR/ADJUST
GO AROUND ALTITUDE............................................................................................................ SET
‐ Set when below the go around altitude to avoid unexpected altitude capture.
FLIGHT PARAMETERS.....................................................................................................MONITOR
‐ Crosscheck distances versus altitudes as published on the charts.
‐ If approaching on a conventional radio NAVAID procedure, monitor the lateral and vertical
guidance using raw data.
‐ For approaches using NAV FPA , monitor XTK error on ND to check the lateral guidance.
‐ The PM calls out if excessive lateral deviation occurs:
• Approach using NAV MODE: XTK > 0.1 NM
• Approach using LOC MODE: LOC ½ dot
• Approach using TRK MODE:
▪ VOR: ½ dot or 2.5 °
▪ NDB: 5 °
Refer to PRO-NOR-SOP-90 Flight Parameters in Approach
Ident.: PRO-NOR-SOP-18-C-E-00015017.0001001 / 29 MAY 13
AT ENTERED MINIMUM +100 FT
ONE HUNDRED ABOVE.......................................................................MONITOR OR ANNOUNCE
Ident.: PRO-NOR-SOP-18-C-E-00014555.0002001 / 04 JUL 17
AT ENTERED MINIMUM
MINIMUM...............................................................................................MONITOR OR ANNOUNCE
Below minimum, the visual references must be the primary references until landing.
For more information regarding transition to visual references, Refer to FCTM/PR-NP-SOP-250
Transition to Visual References.
If visual references are sufficient:
CONTINUE...............................................................................................................ANNOUNCE
AP .........................................................................................................................................OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PRO-NOR-SOP-18-C P 12/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
FD .........................................................................................................................................OFF
‐ The PF orders the PM to set both FDs OFF.
RUNWAY TRACK....................................................................................................CHECK/SET
‐ If needed, the PF orders the PM to set the runway track.
If visual references are not sufficient:
GO AROUND...........................................................................................................ANNOUNCE
‐ Initiate a go around.
Ident.: PRO-NOR-SOP-18-C-E-00014554.0002001 / 23 JUN 15
MANAGEMENT OF DEGRADED NAVIGATION
For VOR and NDB approaches in NAV FPA, if lateral guidance is not satisfactory:
‐ Be prepared to continue the approach with reference to appropriate raw data by reverting to
TRK FPA.
For RNAV(GNSS) approaches, with LNAV minima:
‐ Use the appropriate remaining AP FD in the following cases:
• GPS PRIMARY LOST on one ND
• NAV ACCUR DOWNGRAD on one FMGS
‐ Discontinue the approach in the following cases, if external visual references are not
sufficient to proceed visually:
• GPS PRIMARY LOST on both NDs
• XTK > 0.3 NM
• NAV FM /GPS POS DISAGREE on ECAM
• NAV ACCUR DOWNGRAD on both FMGS
CIRCLING APPROACH
Applicable to: ALL
Ident.: PRO-NOR-SOP-18-C-F-00014570.0001001 / 29 MAY 13
GENERAL
The circling approach is the visual phase of an instrument approach to bring an aircraft into
position for landing on a runway which is not suitably located for a straight-in approach.
CAUTION
The flight crew must conduct the flight within the circling area, while maintaining
required visual references at all times.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
PRO-NOR-SOP-18-C P 13/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Ident.: PRO-NOR-SOP-18-C-F-00014569.0001001 / 29 MAY 13
APPROACH PREPARATION
For a circling approach, the approach preparation should include the following additional items in
the FMS programming.
F-PLN
Introduce the instrument approach procedure, including the missed approach procedure for
instrument approach.
SEC F-PLN
The landing runway must be inserted into the SEC F-PLN.
Update the SEC F-PLN as follows:
‐ Copy the active F-PLN
‐ Revise the landing runway.
Ident.: PRO-NOR-SOP-18-C-F-00014568.0001001 / 29 MAY 13
INSTRUMENT APPROACH
The flight crew flies a stabilized approach at "F" speed, configuration 3 and landing gear down.
Ident.: PRO-NOR-SOP-18-C-F-00014567.0001001 / 29 MAY 13
CIRCLING APPROACH
At the Circling MDA(H) at the latest:
Perform a level off
At MAP, if the flight crew finds no visual reference:
Initiate a go around
When required conditions for circling are satisfied:
Select TRK FPA
Proceed to downwind leg
At any time in the downwind leg, activate the SEC F-PLN
Disconnect the AP and remove the FDs at the latest before starting the descent toward the
runway
Set the landing configuration when appropriate, but ensure early stabilization in final.
If, at any time during the circling procedure, the required visual references are lost, initiate a
go around following the missed approach of the initial instrument approach (unless otherwise
specified).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
PRO-NOR-SOP-18-C P 14/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
STANDARD OPERATING PROCEDURES - APPROACH
FLIGHT CREW
OPERATING MANUAL
Ident.: PRO-NOR-SOP-18-C-F-00014566.0001001 / 30 JUN 16
CIRCLING APPROACH PATTERN
RNAV VISUAL APPROACH
Applicable to: ALL
Ident.: PRO-NOR-SOP-18-C-G-00016048.0001001 / 23 DEC 14
GENERAL
The aircraft navigates using the RNAV system, but the position is monitored by visual reference to
the ground, obstacles and other traffic.
RNAV visual approach must be stored and retrievable from the Navigation Database.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
PRO-NOR-SOP-18-C P 15/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Ident.: PRO-NOR-SOP-18-C-G-00016049.0001001 / 23 DEC 14
EQUIPMENT REQUIRED
‐ 1 FMS
‐ 1 GPS or 2 DME to update FM position
‐ Additional requirement if indicated on the approach chart.
Ident.: PRO-NOR-SOP-18-C-G-00016050.0001001 / 17 MAR 17
FMGC GUIDANCE MODE
If no required accuracy is published:
The use of FMGC guidance mode is at flight crew discretion.
If RNAV 1 or RNP 1 is required on the published approach chart:
The flight crew should use adequate FMGC guidance modes.
Note:
The use of lateral and vertical managed guidance modes reduces the crew workload and
improves energy management.
For RNAV VISUAL approach including RF legs, Refer to FCTM/PR-NP-SP-30 Generalfor RF leg
flying technic.
Ident.: PRO-NOR-SOP-18-C-G-00016051.0001001 / 23 DEC 14
DESCENT PREPARATION
For approach data insertion in the FMS , keep the BARO /MDA field empty on the PERF APPR
Page.
Ident.: PRO-NOR-SOP-18-C-G-00016052.0001001 / 23 DEC 14
DESCENT
For RNAV VISUAL approaches requiring GPS , check that GPS PRIMARY is available on at least
1 FMS.
Ident.: PRO-NOR-SOP-18-C-G-00016053.0001001 / 21 MAR 17
FINAL APPROACH
The flight crew must disconnect the AP at the latest at the Minimum Use Height of the AP.
Refer to LIM-AFS-10 Autopilot Function
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-NOR-SOP-18-C P 16/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
VISUAL APPROACH
Applicable to: ALL
Ident.: PRO-NOR-SOP-18-C-H-00014574.0002001 / 29 MAY 13
GENERAL
Perform the approach on a nominal 3 ° glideslope using visual references. Approach to be
stabilized by 500 ft AGL on the correct approach path, in the landing configuration, at VAPP.
Method:
‐ The AP is not used
‐ Both FDs are OFF
‐ FPV use is recommended
‐ A/THR use is recommended with managed speed.
Bear in mind the possible risk of optical illusions due to hindered night vision.
Note:
If the forecasted tailwind at landing is greater than 10 kt, decelerated approach is not
allowed, and the speed should be stabilized around VREF + 5 kt in final.
Ident.: PRO-NOR-SOP-18-C-H-00014573.0001001 / 08 AUG 13
INITIAL/INTERMEDIATE APPROACH
The flight plan selected on the MCDU should include the selection of the landing runway. The
downwind leg may also be part of the flight plan. This may be a useful indication of the aircraft
position in the circuit on the ND.
However, visual references must be used.
Therefore, at the beginning of the downwind leg:
Manually ACTIVATE APPR
Select FDs to OFF
Select TRK FPA to have FPV displayed
Check A/THR active.
Extend the downwind leg to 3 s/100 ft (± 1 s/1 kt of headwind / tailwind).
Turn into base leg with a maximum of 30 ° of bank. Descent with approximate FPA, in FLAPS 2, at
F speed.
Ident.: PRO-NOR-SOP-18-C-H-00014572.0001001 / 29 MAY 13
FINAL APPROACH
The speed trend arrow and FPV help the flight crew make timely and correct thrust settings (if in
manual thrust), and approach path corrections.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PRO-NOR-SOP-18-C P 17/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Avoid descending through the correct approach path with idle thrust. (Late recognition of this
situation without a prompt thrust increase may lead to considerable speed decay and altitude
loss).
Ensure that the aircraft is stabilized on the final descent path at VAPP (or ground speed mini)
in the landing configuration with the thrust stabilized (usually above idle) at 500 ft above airfield
elevation or as restricted by Operator policies/regulations.
If the aircraft is not stabilized, the flight crew must initiate a go around, unless they think that only
small corrections are necessary to rectify minor deviations from stabilized conditions due, amongst
others, to external perturbations.
Avoid any tendency to “duck under” in the late stages of the approach.
Avoid destabilizing the approach in the last 100 ft, in order to have the best chance of performing a
good touchdown at the desired position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-NOR-SOP-18-C P 18/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Ident.: PRO-NOR-SOP-18-C-H-00014571.0001001 / 08 DEC 14
VISUAL APPROACH (1 OR 2 ENGINES) PATTERN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
PRO-NOR-SOP-18-C P 19/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - APPROACH
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SOP-18-C P 20/20
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - LANDING
MANUAL LANDING
Applicable to: ALL
Ident.: PRO-NOR-SOP-19-A-00010351.0011001 / 25 APR 17
FLARE
The cockpit cut-off angle is 20 °.
In stabilized approach conditions, the flare height is approximately 30 ft:
FLARE........................................................................................................................ PERFORM
Avoid flaring high. Refer to Ground Clearance Diagram.
ATTITUDE................................................................................................................... MONITOR
THRUST levers.................................................................................................................... IDLE
If autothrust is engaged, it automatically disconnects when the pilot sets both thrust levers to
the IDLE detent.
In manual landing conditions, the "RETARD" callout is triggered at 20 ft radio height, in order
to remind the pilot to retard the thrust levers.
Note:
The ground spoilers extension is inhibited if:
‐ Both thrust levers remain above the idle detent, or
‐ One thrust lever is above idle and one thrust lever is at idle detent.
Ident.: PRO-NOR-SOP-19-A-00010352.0001001 / 30 JUN 15
AT TOUCHDOWN
DEROTATION...................................................................................................................... INITIATE
‐ Lower the nosewheel without undue delay.
‐ The PM continues to monitor the attitude.
ALL THRUST LEVERS................................................................................ REV MAX or REV IDLE
The flight crew must select reverse thrust immediately after main landing gear touchdown.
The flight crew must immediately select REV MAX, if any of the following occurs at any time during
the landing:
‐ An emergency
‐ The deceleration is not as expected
‐ A failure affects the landing performance
‐ A long flare or a long touchdown
‐ An unexpected tailwind.
A small pitch up may occur during thrust reversers deployment before nose landing gear
touchdown. However, the flight crew can easily control this pitch up.
As soon as the flight crew selects reverse thrust, they must perform a full-stop landing.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SOP-19 P 1/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - LANDING
GROUND SPOILERS....................................................................................... CHECK/ANNOUNCE
Check that the WHEEL SD page displays the ground spoilers extended after touchdown.
If no ground spoilers are extended:
‐ Verify and confirm that both thrust levers are set to IDLE or REV detent.
‐ Set both thrust reverser levers to REV MAX, and fully press the brake pedals.
Note:
If ground spoilers are not armed, ground spoilers extend at reverser thrust selection.
REVERSERS.................................................................................................... CHECK/ANNOUNCE
Check that the ECAM E/WD displays that the reverse deployment is as expected (REV green).
DIRECTIONAL CONTROL.................................................................................MONITOR/ENSURE
‐
‐
‐
‐
‐
Monitor directional control, if the rollout is automatic.
Ensure directional control, if rollout is manual. Use rudder pedals for directional control.
Do not use the nosewheel steering control handle before reaching taxi speed.
During rollout, the flight crew should avoid sidestick inputs (either lateral or longitudinal).
If directional control problems are encountered, the flight crew should reduce thrust to reverse
idle until directional control is satisfactory.
BRAKES............................................................................................................................. AS RQRD
‐ Monitor the autobrake, if it is ON. When required, brake with the pedals
‐ Although the green hydraulic system supplies the braking system, if pedals are pressed rapidly,
a brake pressure indication appears briefly on the BRAKE PRESS indicator.
‐ Braking may begin before the nosewheel has touched down, if required for performance
reasons. However, when comfort is the priority, the flight crew should delay braking until the
nosewheel has touched down.
Note:
If no ground spoilers are extended, the autobrake is not activated.
DECELERATION.............................................................................................. CHECK/ANNOUNCE
The deceleration is felt by the flight crew, and confirmed by the speed trend on the PFD.
Ident.: PRO-NOR-SOP-19-A-00010353.0001001 / 17 JUL 13
AT 70 KT
SEVENTY KNOTS......................................................................................................... ANNOUNCE
BOTH THRUST LEVERS.................................................................................................. REV IDLE
It is better to reduce thrust when passing 70 kt. However, high levels of reverse thrust may be
used in order to control aircraft speed in the case of an emergency.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-19 P 2/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CAUTION
STANDARD OPERATING PROCEDURES - LANDING
Avoid the use of high levels of reverse thrust at low airspeed, unless required due
to an emergency. The distortion of the airflow, caused by gases reentering the
compressor, can cause engine stalls that may result in excessive EGT.
Ident.: PRO-NOR-SOP-19-A-00010354.0001001 / 17 MAR 11
AT TAXI SPEED
BOTH THRUST LEVERS..................................................................................................FWD IDLE
‐ When reaching taxi speed, and before leaving the runway, deselect the reversers.
‐ On snow-covered grounds, the reversers should be stowed when the aircraft speed reaches
25 kt.
‐ When deselecting the reversers, be careful not to apply forward thrust by moving the thrust
levers beyond the FWD IDLE position.
CAUTION
Except in an emergency, do not use the reverse thrust to control the aircraft
speed while on taxiways.
On taxiways, the use of reversers, even when restricted to idle thrust, would have the following
effects:
‐ The engines may ingest fine sand and debris that may be detrimental to the engines and
airframe systems.
‐ On snow–covered areas, snow will recirculate into the air inlet, and may cause an engine
flameout or rollback.
Ident.: PRO-NOR-SOP-19-A-00010355.0001001 / 30 MAR 15
BEFORE 20 KT
AUTO BRK................................................................................................................... DISENGAGE
Disengage the autobrake to avoid some brake jerks at low speed.
The flight crew should use brake pedals to disengage the autobrake.
AUTOLAND
Applicable to: ALL
Ident.: PRO-NOR-SOP-19-B-00020897.0001001 / 20 MAR 17
The following items must be performed in addition to previous Refer to PRO-NOR-SOP-APPROACH
USING LOC G/S.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
PRO-NOR-SOP-19 P 3/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - LANDING
Ident.: PRO-NOR-SOP-19-B-00020898.0001001 / 20 MAR 17
AT 350 FT RA
ILS /GLS /MLS COURSE on PFD........................................................................... CHECK
If the ILS /GLS /MLS course pointer and the runway track differ by more than 5 °,
autoland is not authorized.
Ident.: PRO-NOR-SOP-19-B-00020899.0001001 / 20 MAR 17
AT 40 FT RA
FLARE mode................................................................................. CHECK ENGAGED/ANNOUNCE
Monitor flare by flight instrument.
If NO FLARE mode at 30 ft, discontinue the approach or perform a manual landing if visual
references are acquired.
Ident.: PRO-NOR-SOP-19-B-00020900.0001001 / 20 MAR 17
AT 30 FT RA
THRUST IDLE........................................................................................................................ CHECK
Monitor thrust reduction.
Ident.: PRO-NOR-SOP-19-B-00020901.0001001 / 20 MAR 17
AT 10 FT RA
BOTH THRUST LEVERS........................................................................................................... IDLE
Retard thrust levers at the "RETARD" autocallout.
LATERAL GUIDANCE....................................................................................................... MONITOR
Monitor the lateral guidance by using external references.
Ident.: PRO-NOR-SOP-19-B-00020902.0001001 / 11 JUL 17
AT TOUCHDOWN
Note:
In the case of NWS or Anti-Skid failure, set the AP OFF at touchdown.
ROLL OUT mode...........................................................................CHECK ENGAGED/ANNOUNCE
BOTH THRUST LEVERS.............................................................................REV MAX or REV IDLE
The flight crew must select reverse thrust immediately after main landing gear touchdown.
The flight crew must immediately select REV MAX, if any of the following occurs at any time during
the landing:
‐ An emergency
‐ The deceleration is not as expected
‐ A failure affects the landing performance
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-19 P 4/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - LANDING
‐ A long flare or a long touchdown
‐ An unexpected tailwind.
A small pitch up may occur during thrust reversers deployment before nose landing gear
touchdown. However, the auto-flight system will control this pitch up.
As soon as the flight crew selects reverse thrust, they must perform a full-stop landing.
GROUND SPOILERS....................................................................................... CHECK/ANNOUNCE
Check that the WHEEL SD page displays the ground spoilers extended after touchdown.
If no ground spoilers are extended:
‐ Verify and confirm that both thrust levers are set to IDLE or REV detent.
‐ Set both thrust reverser levers to REV MAX, and fully press the brake pedals.
Note:
If ground spoilers are not armed, ground spoilers extend at reverser thrust selection.
REVERSERS.................................................................................................... CHECK/ANNOUNCE
Check that the ECAM E/WD displays that the reverse deployment is as expected (REV green).
DIRECTIONAL CONTROL.................................................................................MONITOR/ENSURE
‐
‐
‐
‐
‐
Monitor directional control, if the rollout is automatic.
Ensure directional control, if rollout is manual. Use rudder pedals for directional control.
Do not use the nosewheel steering control handle before reaching taxi speed.
During rollout, the flight crew should avoid sidestick inputs (either lateral or longitudinal).
If directional control problems are encountered, the flight crew should reduce thrust to reverse
idle until directional control is satisfactory.
BRAKES............................................................................................................................. AS RQRD
‐ Monitor the autobrake, if it is ON. When required, brake with the pedals
‐ Although the green hydraulic system supplies the braking system, if pedals are pressed rapidly,
a brake pressure indication appears briefly on the BRAKE PRESS indicator.
‐ Braking may begin before the nosewheel has touched down, if required for performance
reasons. However, when comfort is the priority, the flight crew should delay braking until the
nosewheel has touched down.
Note:
If no ground spoilers are extended, the autobrake is not activated.
DECELERATION.............................................................................................. CHECK/ANNOUNCE
The deceleration is felt by the flight crew, and confirmed by the speed trend on the PFD.
Ident.: PRO-NOR-SOP-19-B-00020904.0001001 / 11 JUL 17
AT 70 KT
SEVENTY KNOTS......................................................................................................... ANNOUNCE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SOP-19 P 5/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - LANDING
BOTH THRUST LEVERS.................................................................................................. REV IDLE
It is better to reduce thrust when passing 70 kt. However, high levels of reverse thrust may be
used in order to control aircraft speed in the case of an emergency.
CAUTION
Avoid the use of high levels of reverse thrust at low airspeed, unless required due
to an emergency. The distortion of the airflow, caused by gases reentering the
compressor, can cause engine stalls that may result in excessive EGT.
Ident.: PRO-NOR-SOP-19-B-00020905.0001001 / 20 MAR 17
BEFORE 20 KT
AUTO BRK.................................................................................................................... DISENGAGE
Disengage autobrake before 20 kt to avoid some brake jerks at low speed.
The flight crew should use brake pedals to disengage the autobrake.
Ident.: PRO-NOR-SOP-19-B-00020906.0001001 / 20 MAR 17
END OF ROLL OUT
BOTH THRUST LEVERS..................................................................................................FWD IDLE
‐ When reaching taxi speed, and before leaving the runway, deselect the reversers.
‐ On snow-covered grounds, the reversers should be stowed when the aircraft speed reaches
25 kt.
‐ When deselecting the reversers, be careful not to apply forward thrust by moving the thrust
levers beyond the FWD IDLE position.
CAUTION
Except in an emergency, do not use the reverse thrust to control the aircraft
speed while on taxiways.
On taxiways, the use of reversers, even when restricted to idle thrust, would have the following
effects:
‐ The engines may ingest fine sand and debris that may be detrimental to the engines and
airframe systems.
‐ On snow–covered areas, snow will recirculate into the air inlet, and may cause an engine
flameout or rollback.
AP.................................................................................................................................................OFF
Disengage the APs at the end of the roll out (when leaving the runway at the latest).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-NOR-SOP-19 P 6/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - GO-AROUND
GO AROUND WITH FD
Applicable to: ALL
Ident.: PRO-NOR-SOP-20-A-00011576.0006001 / 30 JUN 15
Apply the following three actions simultaneously:
THRUST LEVERS........................................................................................................................ TOGA
If TOGA thrust is not required, set the thrust levers to TOGA detent then retard the thrust levers as
required. This enables to engage the GO-AROUND phase, with associated AP /FD modes.
The flight crew may use CL detent to have benefit of A/THR.
Note:
If the thrust levers are not set briefly to TOGA detent, the FMS does not engage the
GO-AROUND phase, and flying over, or close to the airport will sequence the Destination
waypoint in the F-PLN.
ROTATION............................................................................................................................PERFORM
Initiate rotation towards 15 ° of pitch with all engines operative (approximately 12.5 ° if one engine is
out) to get a positive rate of climb, then follow the SRS Flight Director pitch bars orders.
When near the ground, avoid excessive rotation rate in order to prevent a tail strike.
GO AROUND .................................................................................................................... ANNOUNCE
FLAPS lever............................................................................................................SELECT AS RQRD
Retract one step of flaps.
FMA.................................................................................................................................... ANNOUNCE
The following modes are displayed: MAN TOGA / SRS / GA TRK / A/THR (in blue).
POSITIVE CLIMB ..............................................................................................................ANNOUNCE
L/G UP ......................................................................................................................................ORDER
L/G...................................................................................................................................... SELECT UP
NAV or HDG mode................................................................................................................ AS RQRD
Reselect NAV or HDG, as required (minimum height 100 ft).
AP...........................................................................................................................................AS RQRD
Note:
Go-around may be flown with both autopilots engaged. Whenever any other mode
engages, AP 2 disengages.
Ident.: PRO-NOR-SOP-20-A-00011579.0002001 / 13 AUG 10
AT GO-AROUND THRUST REDUCTION ALTITUDE
THRUST levers.............................................................................................................................. CL
LVR CLB flashing on FMA.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SOP-20 P 1/2
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - GO-AROUND
Ident.: PRO-NOR-SOP-20-A-00011581.0001001 / 23 JUN 15
AT GO-AROUND ACCELERATION ALTITUDE
Monitor that the target speed increases to green dot.
If the target speed does not increase to green dot:
ALT knob........................................................................................................ CHECK and PULL
At F speed:
FLAPS 1.......................................................................................................................... ORDER
FLAPS 1......................................................................................................................... SELECT
At S speed:
FLAPS 0.......................................................................................................................... ORDER
FLAPS 0......................................................................................................................... SELECT
GND SPLRS...................................................................................................................DISARM
NOSE sw...............................................................................................................................OFF
RWY TURN OFF sw.............................................................................................................OFF
OTHER EXTERIOR LIGHTS.......................................................................................AS RQRD
The flight crew can maintain the LAND LIGHTS selector set to ON, according to airline policy
or regulatory recommendations.
Note:
Consider the next step:
‐ Engage NAV mode, to follow the published missed approach procedure, or
‐ Prepare for a second approach by selecting the ACTIVATE APP PHASE, and
CONFIRM on the PERF page.
AFTER TAKEOFF/CLIMB CHECKLIST down to the line............................................... COMPLETE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SOP-20 P 2/2
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - AFTER LANDING
AFTER LANDING
Applicable to: ALL
Ident.: PRO-NOR-SOP-21-A-00011841.0001001 / 06 DEC 16
GRND SPLRS......................................................................................................................... DISARM
Ident.: PRO-NOR-SOP-21-A-00011840.0001001 / 29 SEP 15
LAND LIGHTS selector ........................................................................................................ RETRACT
OTHER EXTERIOR LIGHTS................................................................................................. AS RQRD
External lights can be turned off, unless they are needed.
Set the NAV & LOGO to ON, as required, to turn on the navigation and logo lights .
L2 The PF may ask the PM to set the exterior lights.
Ident.: PRO-NOR-SOP-21-A-00011842.0001001 / 22 APR 16
RADAR.............................................................................................................................................OFF
Ident.: PRO-NOR-SOP-21-A-00011843.0001001 / 06 JAN 16
PREDICTIVE WINDSHEAR SYSTEM .....................................................................................OFF
Switching the radar and predictive windshear system to OFF after landing avoids risk of radiating
persons at the gate area.
Ident.: PRO-NOR-SOP-21-A-00011844.0001001 / 13 DEC 10
ENG MODE selector....................................................................................................................NORM
Ident.: PRO-NOR-SOP-21-A-00011845.0001001 / 08 AUG 13
FLAPS.................................................................................................................................... RETRACT
Set the FLAPS lever to position 0.
If the approach was made in icing conditions, or if the runway was contaminated with slush or snow,
do not retract the flaps and slats until after engine shutdown and after the ground crew has confirmed
that flaps and slats are clear of obstructing ice.
On ground, hot weather conditions may cause overheating to be detected around the bleed ducts
in the wings, resulting in “AIR L (R) WING LEAK” warnings. Such warnings may be avoided during
transit by keeping the slats in Configuration 1 when the OAT is above 30 °C.
To avoid damage on the RTLU (Rudder Travel Limit Unit) mechanical stop, the SLATS/FLAPS
should be retracted before all ADIRS are set to OFF simultaneously.
Ident.: PRO-NOR-SOP-21-A-00011846.0001001 / 04 JUL 17
TCAS............................................................................................................................................. STBY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SOP-21 P 1/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - AFTER LANDING
Ident.: PRO-NOR-SOP-21-A-00011847.0001001 / 20 JAN 15
ATC........................................................................................................................................ AS RQRD
ATC is set in accordance with airport requirements.
Ident.: PRO-NOR-SOP-21-A-00011848.0001001 / 17 MAR 15
APU............................................................................................................................................. START
APU START may be delayed until just prior to engine shutdown.
Note:
Prolonged use of the APU may cause a fuel imbalance. Pay particular attention to the fuel
imbalance limitation for the next take-off.
Ident.: PRO-NOR-SOP-21-A-00011849.0005001 / 17 MAR 17
CAUTION
In icing conditions (Refer to LIM-ICE_RAIN Definition of Icing Conditions), the flight
crew must turn on the engine anti-ice and should not wait until seeing ice building
up.
ANTI ICE................................................................................................................................ AS RQRD
‐ If engine anti-ice is used, take care to control taxi speed, especially on wet or slippery surfaces.
(N1 ground idle is increased).
‐ During ground operation, when in icing conditions for more than 30 min, the following procedure
should be applied for ice shedding:
CAUTION
If, during thrust increase, the aircraft starts to move, immediately retard the thrust
levers to IDLE.
If ground surface conditions and the environment permit, the flight crew should accelerate the
engines to approximately 70 % of N1 for 30 s at intervals not greater than 30 min.
If ground surface or environment do not permit to accelerate the engine to 70 % N1, then power
setting and dwell time should be as high as practical.
When operating in conditions of freezing rain, freezing drizzle, freezing fog or heavy snow, ice
shedding may be enhanced, by additional run ups at intervals, to not exceed 10 min, advancing
throttles to 70 % N1 momentarily (no hold time).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-21 P 2/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - AFTER LANDING
Ident.: PRO-NOR-SOP-21-A-00011850.0001001 / 17 MAR 17
BRAKE TEMPERATURE........................................................................................................... CHECK
‐ Check brake temperature on the WHEEL SD page for discrepancies and high temperature
‐ Maintenance action is due in the following cases:
• The temperature difference between two brakes of a gear is more than 150 °C, and the
temperature of one of these brakes is above or equal to 600 °C, or
• The temperature difference between two brakes of a gear is more than 150 °C, and the
temperature of one of these brakes is below or equal to 60 °C, or
• The difference between the average temperature of the left gear brakes (combination of body
and wing L/G s) and right brakes (combination of body and wing L/Gs) is above or equal to
200 °C, or
• The temperature of one brake exceeds 900 °C.
BRK FAN pb-sw ................................................................................................... AS REQUIRED
When the turnaround time is short or if the temperature of any brake is likely to exceed 500 °C, use
the brake fans without delay. In other cases, the flight crew should delay brake fans selection to
5 min after landing, or approaching the gate, whichever occurs first.
L2 For more information, Refer to FCTM/PR-NP-SOP-270 Use of Brake Fans.
Ident.: PRO-NOR-SOP-21-A-00011851.0001001 / 10 AUG 10
AFTER LANDING CHECKLIST.......................................................................................... COMPLETE
Ensure that the after-landing checks are completed, once the aircraft has cleared the runway.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-21 P 3/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - AFTER LANDING
Ident.: PRO-NOR-SOP-21-A-00020077.0001001 / 17 MAR 17
AFTER LANDING - FLOW PATTERN
After Landing Flow Pattern
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SOP-21 P 4/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - PARKING
PARKING
Applicable to: ALL
Ident.: PRO-NOR-SOP-22-A-00011852.0001001 / 21 MAR 17
Prior to performing this check, consider “GROUND OPERATIONS IN HEAVY RAIN” (Refer to
PRO-NOR-SUP-ADVWXR Ground Operations in Heavy Rain).
Ident.: PRO-NOR-SOP-22-A-00011853.0003001 / 20 JUL 15
ACCU PRESS indicator............................................................................................................. CHECK
The ACCU PRESS indication must be in the green band. In case of low accumulator pressure,
chocks are required before engine 1 shutdown.
PARKING BRAKE handle................................................................................................................. ON
When one brake temperature is above 500 °C (or 350 °C with brake fans ON), avoid applying
the parking brake, unless operationally necessary.
BRAKES PRESS indicator.........................................................................................................CHECK
Check for normal indications.
Ident.: PRO-NOR-SOP-22-A-00011854.0001001 / 13 AUG 10
ANTI-ICE..........................................................................................................................................OFF
Ident.: PRO-NOR-SOP-22-A-00011855.0001001 / 13 AUG 10
APU BLEED pb-sw............................................................................................................................ON
Select APU bleed ON, just before engine shutdown, to prevent engine exhaust fumes from entering
the air conditioning.
Ident.: PRO-NOR-SOP-22-A-00011856.0004001 / 17 MAR 17
If the APU is not available:
EXT PWR pb.............................................................................................................................. ON
No less than 3 min after high thrust operations:
ALL ENG MASTERS ............................................................................................................... OFF
CAUTION
If JP4 fuel is used at ambient temperatures higher than 10 °C, dry motor the
engines for 2 min after engine shutdown. This dry motor period should start
approximately 90 s after the master lever is selected OFF.
Check that engine parameters decrease.
The DOOR/OXY SD page is displayed on the lower ECAM display.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SOP-22 P 1/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L2
Note:
STANDARD OPERATING PROCEDURES - PARKING
The flight crew should operate the engines at or near idle thrust for a cooling period of
3 min before engine shutdown, in order to thermally stabilize the engines.
Idle reverse thrust and normal thrust to maneuver during taxi (i.e. at or near idle), are
not considered as high thrust operations. Therefore, both of the following applies:
‐ If the flight crew uses idle reverse thrust for landing and normal thrust to maneuver
during taxi after landing, the cooling period starts when the flight crew retards the
thrust lever during the flare
‐ If the flight crew uses maximum reverse for landing, the cooling period starts when
the flight crew sets the thrust lever to idle reverse during the landing rollout.
However, if operationally necessary, all engines can be shut down when the aircraft
arrives at the gate, regardless of the time necessary for landing.
Before engine shutdown, routine cooling periods that last less than the recommended
time, can result in engine degradation.
Ident.: PRO-NOR-SOP-22-A-00011858.0001001 / 04 MAR 14
SLIDES...................................................................................................................CHECK DISARMED
Check slides disarmed on the DOOR/OXY SD page. Warn the cabin crew, if any slide is not
disarmed.
Ident.: PRO-NOR-SOP-22-A-00011860.0001001 / 04 MAR 14
SEAT BELTS sw............................................................................................................................. OFF
Ident.: PRO-NOR-SOP-22-A-00011859.0001001 / 23 JUN 15
BEACON lights................................................................................................................................ OFF
Turn off the BEACON lights, when all engines are spooled down.
OTHER EXTERIOR LIGHTS................................................................................................. AS RQRD
Ident.: PRO-NOR-SOP-22-A-00011857.0001001 / 13 AUG 10
GROUND CONTACT.......................................................................................................... ESTABLISH
Establish ground communication.
Check chocks in place.
Ident.: PRO-NOR-SOP-22-A-00011862.0001001 / 13 AUG 10
FUEL PUMPS..................................................................................................................................OFF
Ident.: PRO-NOR-SOP-22-A-00011864.0001001 / 04 JUL 17
ATC................................................................................................................................................STBY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-22 P 2/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - PARKING
Ident.: PRO-NOR-SOP-22-A-00011865.0001001 / 20 OCT 16
IRS PERFORMANCE.................................................................................................................CHECK
‐ The NAV TIME is the cumulated block time since the latest IRS alignment (fast or complete).
‐ On the MCDU POSITION MONITOR page, read the deviation of each IRS position from the
FMGC position and check that the value does not exceed the following:
Ident.: PRO-NOR-SOP-22-A-00011866.0001001 / 13 AUG 10
FUEL QUANTITY....................................................................................................................... CHECK
Check that the sum of the fuel on board and the fuel used is consistent with the fuel on board at
departure. If an unusual discrepancy is found, maintenance action is due.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-22 P 3/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - PARKING
Ident.: PRO-NOR-SOP-22-A-00011867.0001001 / 24 FEB 15
STS pb (ECAM Control panel)...................................................................................................PRESS
Check the STATUS page.
Ident.: PRO-NOR-SOP-22-A-00011868.0001001 / 13 AUG 10
(BRAKE FAN ).......................................................................................................................... OFF
Switch off, when not required.
Ident.: PRO-NOR-SOP-22-A-00011869.0002001 / 13 AUG 10
PARKING BRAKE.................................................................................................................. AS RQRD
The parking brake should be released after chocks are in place, if one brake temperature is above
300 °C (or above 150 °C with brake fans ON).
Releasing the parking brake prevents the critical structures from being exposed to high temperature
levels for an extended time. However, if operational conditions dictate (e.g. slippery tarmac), the
parking brake may remain applied.
When parking with a flat tire on the nose gear, keep the parking brake on, to avoid aircraft yawing at
parking brake release.
Ident.: PRO-NOR-SOP-22-A-00011870.0001001 / 13 AUG 10
DUs...................................................................................................................................................DIM
Dim EFIS , ECAM and MCDU display units.
Ident.: PRO-NOR-SOP-22-A-00014395.0001001 / 20 MAR 17
EFB
EFB/eQRH transmitting mode......................................................................................... CONSIDER
In accordance with the Operator’s policy or, as required by operational regulations.
If performing transit stop:
eQRH My Aircraft/FLIGHT............................................................................................... CLEAR
Ident.: PRO-NOR-SOP-22-A-00011873.0001001 / 13 AUG 10
PARKING CHECKLIST....................................................................................................... COMPLETE
Ident.: PRO-NOR-SOP-22-A-00011874.0001001 / 13 AUG 10
REPORT SEVERE ICING CONDITIONS
Report severe icing conditions in the log book, requiring inspections of the fan accoustic panels of
the engines during the walkaround.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SOP-22 P 4/4
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - SECURING THE AIRCRAFT
SECURING THE AIRCRAFT
Applicable to: ALL
Ident.: PRO-NOR-SOP-23-A-00010336.0001001 / 17 MAR 17
GENERAL
Prior to performing this check, the following SUP Adverse Weather procedures should be taken
into account when appropriate:
‐ Securing the aircraft for cold soak (Refer to PRO-NOR-SUP-ADVWXR Securing the Aircraft for
Cold Soak).
‐ Water system draining (Refer to PRO-NOR-SUP-ADVWXR For Draining Water Procedure Introduction).
‐ Ground operations in heavy rain (Refer to PRO-NOR-SUP-ADVWXR Ground Operations in
Heavy Rain).
‐ Operations on contaminated airports (Refer to PRO-NOR-SUP-ADVWXR Parking).
‐ Operations with volcanic ash, sand or dust (Refer to PRO-NOR-SUP-ADVWXR Securing the
Aircraft).
Ident.: PRO-NOR-SOP-23-A-00010337.0001001 / 30 JUN 15
PARKING BRAKE
PARK BRK handle...........................................................................................................CHECK ON
To reduce hydraulic leak rate in the brake accumulator, keep the parking brake on.
Ident.: PRO-NOR-SOP-23-A-00010338.0001001 / 05 AUG 10
OXYGEN CREW SUPPLY
OXYGEN CREW SUPPLY pb.....................................................................................................OFF
Ident.: PRO-NOR-SOP-23-A-00010339.0001001 / 21 AUG 15
ADIRS
ALL IR MODE selectors.............................................................................................................. OFF
After the shutdown of the ADIRS , the flight crew must wait 10 s before the shutdown of the
electrical supply. This time ensures that the ADIRS memorize the most recent data.
Ident.: PRO-NOR-SOP-23-A-00010340.0001001 / 05 AUG 10
EXTERIOR LIGHTS
EXTERIOR LIGHTS.....................................................................................................................OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SOP-23 P 1/4
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - SECURING THE AIRCRAFT
Ident.: PRO-NOR-SOP-23-A-00010341.0001001 / 05 AUG 10
MAINTENANCE BUS
MAINT BUS sw.................................................................................................................. AS RQRD
Should electrical power be required for the crew or servicing personnel, consider setting the
overhead MAINT BUS sw (in the forward cabin) to the ON position, prior to setting aircraft power
to off.
Ident.: PRO-NOR-SOP-23-A-00010342.0001001 / 04 MAR 14
APU
APU BLEED pb-sw......................................................................................................................OFF
APU MASTER SW...................................................................................................................... OFF
Switch off the APU after the passengers have disembarked.
Ident.: PRO-NOR-SOP-23-A-00010343.0004001 / 04 MAR 14
EMER LIGHTS AND SIGNS
EMER EXIT LT sw...................................................................................................................... OFF
NO PORTABLE/ELEC DEVICE sw.............................................................................................OFF
Ident.: PRO-NOR-SOP-23-A-00010344.0001001 / 05 AUG 10
EXTERNAL POWER
EXT PWR pb......................................................................................................................AS RQRD
Ident.: PRO-NOR-SOP-23-A-00010345.0001001 / 05 AUG 10
BAT 1 AND 2
BAT 1 pb-sw and BAT 2 pb-sw.................................................................................................. OFF
Wait until the APU flap is fully closed (about 2 min after the APU AVAIL light goes out), before
switching off the batteries. Switching the batteries off before the APU flap is closed may cause
smoke in the cabin during the next flight.
If the batteries are off while the APU is running, APU fire extinguishing is not available.
Ident.: PRO-NOR-SOP-23-A-00010346.0001001 / 05 AUG 10
SECURING THE AIRCRAFT CHECKLIST
SECURING THE AIRCRAFT CHECKLIST.....................................................................COMPLETE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SOP-23 P 2/4
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - SECURING THE AIRCRAFT
Ident.: PRO-NOR-SOP-23-A-00014412.0001001 / 20 MAR 17
ELECTRONIC FLIGHT BAG EFB
EFB/eQRH LAPTOPS.................................................................................................. SWITCH OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SOP-23 P 3/4
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - SECURING THE AIRCRAFT
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SOP-23 P 4/4
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - STANDARD CALLOUTS
COMMUNICATIONS AND STANDARD TERMS
Ident.: PRO-NOR-SOP-90-00011900.0001001 / 13 AUG 10
Applicable to: ALL
Standard phraseology is essential to ensure effective crew communication. The phraseology should
be concise and exact. The following Chapter lists the callouts that should be used as standard. They
supplement the callouts identified in the SOP.
These standard Airbus callouts are also designed to promote situational awareness, and to ensure
crew understanding of systems and their use in line operation.
CHECKLIST CALLOUTS
Ident.: PRO-NOR-SOP-90-00011901.0001001 / 20 DEC 10
Applicable to: ALL
‐ “CHECK”: A command for the other pilot to check an item.
‐ “CHECKED”: A response that an item has been checked.
‐ “CROSSCHECKED”: A callout verifying information from both pilot stations.
If a checklist needs to be interrupted, announce: “HOLD CHECKLIST AT ___” and “RESUME
CHECKLIST AT ___” for the continuation.
Upon completion of a checklist announce: “__CHECKLIST COMPLETE”.
ACTIONS COMMANDED BY PF
Applicable to: ALL
Ident.: PRO-NOR-SOP-90-A-00011902.0001001 / 13 AUG 10
GENERAL
The following commands do not necessarily initiate a guidance mode change, eg.: selected to
managed/managed to selected. The intent is to ensure clear, consistent, standard communication
between crewmembers.
All actions performed on the FCU and MCDU must be checked on the PFD and ND (eg.: “FL 350
blue”, “FL 200 magenta"). Ensure that the correct FCU knob is used, then verify indications on the
PFD /ND.
Ident.: PRO-NOR-SOP-90-A-00011904.0001001 / 09 JUN 15
SET
The “SET” command means using an FCU knob to set a value, but not to change a mode.
SET is accomplished by only rotating the appropriate selection knob.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C →
PRO-NOR-SOP-90 P 1/10
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - STANDARD CALLOUTS
Example:
‐ ”SET GO AROUND ALTITUDE__FT”
‐ “SET FL __”
‐ “SET HDG __”
Ident.: PRO-NOR-SOP-90-A-00011905.0001001 / 20 DEC 10
MANAGE/PULL
The “MANAGE” command means pushing an FCU knob to engage, or arm, a managed mode or
target.
The “PULL” command means pulling an FCU knob to engage a selected mode or target. Example:
‐ "PULL HDG 090”
(HDG/TRK knob is pulled and turned).
‐ “MANAGE NAV”
(HDG/TRK knob is pushed).
‐ “FL 190 PULL”
(ALT knob is turned and pulled).
‐ “FL 190 MANAGE”
(ALT knob is turned and pushed).
‐ “PULL SPEED 250 KNOTS” (SPD/MACH knob is pulled and turned).
‐ “MANAGE SPEED”
(SPD/MACH knob is pushed).
Note:
If the value was previously set, there is no requirement to repeat the figure.
Simply call e.g. PULL HDG: PULL SPEED: FL PULL.
The VS/FPA knob has no managed function. The standard callouts for the use of this knob are as
follows:
V/S Plus (or Minus) 700 PULL, or
FPA Minus 3 ° PULL
(V/S/FPA knob is turned and pulled)
PUSH TO LEVEL OFF
(V/S/FPA knob is pushed)
Ident.: PRO-NOR-SOP-90-A-00011906.0001001 / 13 AUG 10
ARM
The “ARM __” command means arming a system by pushing the specified FCU button.
e.g. : “ARM APPROACH”
e.g. : “ARM LOC.”
Ident.: PRO-NOR-SOP-90-A-00011907.0001001 / 13 AUG 10
ON/OFF
The simple ON or OFF command is used for the autopilot, flight directors, autothrust and the bird
(flight path vector).
e.g.: BIRD ON (The HDG-V/S / TRK-FPA pb is pushed.)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PRO-NOR-SOP-90 P 2/10
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - STANDARD CALLOUTS
FMA
Ident.: PRO-NOR-SOP-90-00011908.0001001 / 23 DEC 14
Applicable to: ALL
The PF should call out any FMA change, unless specified differently (e.g. CAT II & III task sharing).
Therefore, the PF should announce:
‐ All armed modes with the associated color (e.g. blue, magenta): "G/S blue", "LOC blue".
‐ All active modes without the associated color (e.g. green, white): "NAV", "ALT".
The PM should check and respond, "CHECKED" to all FMA changes called out by the PF.
ALTITUDE
Ident.: PRO-NOR-SOP-90-00011909.0001001 / 23 DEC 14
Applicable to: ALL
The PM calls out "one thousand to go" when passing 1 000 ft before the cleared altitude or FL , and
the PF calls out "checked".
FLAPS OR GEAR CALLOUTS
Applicable to: ALL
Ident.: PRO-NOR-SOP-90-B-00011910.0001001 / 23 DEC 14
FLAPS' CALLOUTS
FLAPS' CONFIGURATION
1
1+F
0
CALLOUT
"FLAPS ONE"
"FLAPS ONE"
"FLAPS ZERO"
The reply will be given when selecting the new flap position.
e.g.:
PF
CALLOUT
"FLAPS ONE"
"SPEED CHECKED"
PM
"FLAPS ONE"
REMARK
PM checks the speed:
‐ Above the S or F speed and accelerating (Takeoff)
‐ Below VFE next and decelerating (Approach)
PM selects the FLAPS lever position and replies after checking the blue number
on the ECAM flaps indicator to confirm the correct selection has been made.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D to F →
PRO-NOR-SOP-90 P 3/10
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - STANDARD CALLOUTS
Ident.: PRO-NOR-SOP-90-B-00011911.0001001 / 23 DEC 14
GEAR CALLOUTS
CALLOUT
"GEAR UP (DOWN)"
"GEAR UP (DOWN)"
PF
PM
REMARKS
The PM selects the L/G lever position and replies
after checking the red lights on the LDG GEAR
indicator to confirm gear operation.
FLIGHT PARAMETERS
Applicable to: ALL
Ident.: PRO-NOR-SOP-90-C-00011912.0001001 / 22 MAR 17
APPROACH
During approach, the PM announces:
‐ "SPEED" if the speed decreases below the speed target -5 kt or increases above the speed
target +10 kt.
‐ "SINK RATE" when the descent rate exceeds 1 000 ft/min
‐ "BANK" when bank angle becomes greater than 7 °
‐ "PITCH" when pitch attitude becomes lower than -2.5 ° or higher than +10 °
‐ "LOC" or "GLIDE" when either localizer or glide slope deviation is:
• ½ dot LOC
• ½ dot GS.
‐
‐
‐
‐
"CROSS TRACK" when the XTK is greater than 0.1 NM
"V/DEV" when the vertical deviation is greater than ½ dot
"COURSE" when greater than ½ dot or 2.5 ° (VOR ) or 5 ° (ADF).
"__ FT HIGH (LOW)" at altitude checks points.
Note:
The PM announces the attitude deviations until landing.
Ident.: PRO-NOR-SOP-90-C-00021570.0001001 / 22 MAR 17
LANDING
During landing, the PM announces:
‐ "PITCH PITCH", if the pitch attitude approaches the tail strike pitch limit indicator , or
reaches 10 °
‐ "BANK BANK", if the bank angle reaches 7 °.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G →
PRO-NOR-SOP-90 P 4/10
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - STANDARD CALLOUTS
Ident.: PRO-NOR-SOP-90-C-00011913.0001001 / 22 MAR 17
GO-AROUND
During a go-around, the PM announces:
‐ "BANK", if the bank angle becomes greater than 7 °
‐ "PITCH", if the pitch attitude becomes greater than 20 ° up or less than 10 ° up
‐ "SINK RATE", if there is no climb rate.
PF/PM DUTIES TRANSFER
Ident.: PRO-NOR-SOP-90-00011914.0001001 / 23 DEC 14
Applicable to: ALL
To transfer control, flight crewmembers must use the following callouts:
‐ To give control : The pilot calls out "YOU HAVE CONTROL". The other pilot accepts this transfer
by calling out "I HAVE CONTROL", before assuming PF duties.
‐ To take control : The pilot calls out "I HAVE CONTROL". The other pilot accepts this transfer by
calling out "YOU HAVE CONTROL", before assuming PM duties.
SUMMARY FOR EACH PHASE
Applicable to: ALL
Ident.: PRO-NOR-SOP-90-D-00011917.0001001 / 23 DEC 14
EVENT
Initial ground contact
External __ disconnection
TO REMOVE GROUND SUPPLY
PF or PM
GND Mech
GROUND (from) COCKPIT
COCKPIT (from) GROUND
REMOVE EXTERNAL __
EXTERNAL__ REMOVED
Ident.: PRO-NOR-SOP-90-D-00011918.0001001 / 23 DEC 14
EVENT
Before start up clearance received
After start up clearance received
BEFORE ENGINE START/PUSH BACK
PF
PM
BEFORE START C/L
DOWN TO THE LINE
BELOW THE LINE
BEFORE START C/L COMPLETE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← G to I →
PRO-NOR-SOP-90 P 5/10
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - STANDARD CALLOUTS
Ident.: PRO-NOR-SOP-90-D-00011919.0001001 / 17 MAR 16
PUSH BACK/ENGINE START
EVENT
PF
GND Mech.
When ready for pushback, and pushback GROUND (from) COCKPIT,
clearance received from ATC
CLEARED FOR PUSH
COCKPIT (from) GROUND, RELEASE
BRAKES
Start of push
BRAKES RELEASED READY
TO PUSH
When ready to start engines
CLEAR TO START ?
CLEAR TO START
STARTING ENG(S)__
When pushback completed
SET BRAKES
BRAKES SET
When ready to disconnect (after engine CLEAR TO DISCONNECT
started, and parameters are stabilized) (hand signals on left/right)
DISCONNECTING (hand signals on left/right)
Ident.: PRO-NOR-SOP-90-D-00011920.0001001 / 23 DEC 14
EVENT
All engines started and stabilized and
GND is disconnected
AFTER ENGINE START
PF
AFTER START C/L
PM
AFTER START C/L COMPLETE
Ident.: PRO-NOR-SOP-90-D-00011921.0002001 / 23 DEC 14
EVENT
When taxi clearance obtained
TAXI
PF
CLEAR LEFT (RIGHT) SIDE
Brake check
Flight control check in the following
sequence (the check is possible before
the start of taxi)
1. Elevators
2. Ailerons/Spoilers
3. Rudder(1)
During taxi
BRAKE CHECK
FLIGHT CONTROL CHECK
Line up on the runway
BELOW THE LINE
(1)
RUDDER
BEFORE TAKEOFF C/L
PM
CLEAR RIGHT (LEFT) SIDE
FULL UP, FULL DOWN, NEUTRAL
FULL LEFT, FULL RIGHT, NEUTRAL
FULL LEFT, FULL RIGHT, NEUTRAL
DOWN TO THE LINE
BEFORE TAKEOFF C/L COMPLETE
The PM should follow pedal movement with his/her feet
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
PRO-NOR-SOP-90 P 6/10
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - STANDARD CALLOUTS
Ident.: PRO-NOR-SOP-90-D-00011922.0001001 / 23 DEC 14
EVENT
Setting thrust levers to initial stabilization TAKEOFF
value
Before passing 80 kt
At 100 kt
CHECKED
At V1
At VR
Gear retraction
GEAR UP
TAKEOFF
PF
PM
THRUST SET
ONE HUNDRED KNOTS
V1
ROTATE
POSITIVE CLIMB
If AP is engaged by PM
Checklist
AP 1(2) ON
AFTER TAKEOFF/CLIMB C/L
At transition altitude
BELOW THE LINE
GEAR UP
DOWN TO THE LINE
AFTER TAKEOFF/CLIMB C/L COMPLETE
Ident.: PRO-NOR-SOP-90-D-00011923.0001001 / 17 MAR 16
If GO decision
If RTO decision
EVENT
MALFUNCTION BEFORE V1 AT TAKEOFF
CAPT
GO
STOP
‐ REV green on EWD
‐ Deceleration
F/O
REVERSE GREEN(1)
DECEL(2)
(1)
If the reverse deployment is not as expected, call NO REVERSE ENGINE__or NO REVERSE, as
appropriate
(2)
In case of failure or no positive deceleration, NO DECEL
DECEL callout means that the deceleration is felt by the crew, and confirmed by the speed trend on
the PFD.
Ident.: PRO-NOR-SOP-90-D-00011924.0001001 / 12 MAY 16
ALTIMETER SETTING CHANGES TO/FROM QNH /QFE-STD
EVENT
PF
PM
Barometric setting change and
SET STANDARD
subsequent altimeter cross-check
(SET QNH/QFE)
STANDARD (QNH/QFE) CROSS-CHECKED
PASSING FL__(__FT) NOW
CHECKED
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
PRO-NOR-SOP-90 P 7/10
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - STANDARD CALLOUTS
Ident.: PRO-NOR-SOP-90-D-00011925.0001001 / 17 MAR 16
EVENT
Approach checklist
Activation of approach Phase
RA alive
At G/S *, FINAL APP engagement, or
below GA altitude for approach using
FPA guidance
FAF
Landing checklist
1 000 ft RA
100 ft above MDA /DH
MDA /DH visual reference
MDA /DH no visual reference
After touchdown
Ground spoilers extended
REV green on EWD
Deceleration
At 70 kt
APPROACH AND LANDING
PF
PM
APPROACH C/L
APPROACH C/L COMPLETE
ACTIVATE APPROACH
PHASE
APPROACH PHASE ACTIVATED
RADIO ALTIMETER ALIVE(1)(2)
CHECKED
SET GA ALTITUDE __FT
GA ALTITUDE - SET,
PASSING__(Fix Name),__ FT,
CHECKED
LANDING C/L
LANDING C/L COMPLETE
ONE THOUSAND(2)
CHECKED
ONE HUNDRED ABOVE(2)
CHECKED
MINIMUM(2)
CONTINUE
GO AROUND-FLAPS
MINIMUM(2)
ONE HUNDRED(2)
FIFTY(2)
SPOILERS(3)
REVERSE GREEN(4)
DECEL(5)
SEVENTY KNOTS
CHECKED
(1)
Crew awareness, crew should now keep RA in scan to landing
(2)
PM monitors pin-programmed auto callout, or announces if inoperative.
(3)
If the spoilers are not extended, call NO SPOILERS
(4)
If the reverse deployment is not as expected, call NO REVERSE ENGINE__ or NO REVERSE, as
appropriate.
(5)
DECEL Callout means that the deceleration is felt by the crew, and confirmed by the speed trend
on the PFD .If no positive deceleration, NO DECEL.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I→
PRO-NOR-SOP-90 P 8/10
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - STANDARD CALLOUTS
Ident.: PRO-NOR-SOP-90-D-00015353.0001001 / 23 DEC 14
EVENT
DISCONTINUED APPROACH decision
DISCONTINUED APPROACH
PF
CANCEL APPROACH
PM
Ident.: PRO-NOR-SOP-90-D-00011926.0001001 / 17 MAR 16
EVENT
GO AROUND decision
Flaps retraction
Gear retraction
GO AROUND
PF
GO AROUND - FLAPS
GEAR UP
Checklist
AFTER TAKEOFF/CLIMB C/L
At transition altitude
BELOW THE LINE
PM
FLAPS__
POSITIVE CLIMB
GEAR UP
DOWN TO THE LINE
AFTER TAKEOFF/CLIMB C/L COMPLETE
Ident.: PRO-NOR-SOP-90-D-00011927.0001001 / 23 DEC 14
Checklist
EVENT
AFTER LANDING
PF
AFTER LANDING C/L
PM
AFTER LANDING C/L COMPLETE
Ident.: PRO-NOR-SOP-90-D-00011928.0001001 / 23 DEC 14
Checklist
EVENT
PARKING
PF
PARKING C/L
PM
PARKING C/L COMPLETE
Ident.: PRO-NOR-SOP-90-D-00011929.0001001 / 23 DEC 14
Checklist
EVENT
SECURING THE AIRCRAFT
PF
PM
SECURING THE AIRCRAFT
C/L
SECURING THE AIRCRAFT C/L COMPLETE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←I
PRO-NOR-SOP-90 P 9/10
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
STANDARD OPERATING PROCEDURES - STANDARD CALLOUTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SOP-90 P 10/10
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES SUPPLEMENTARY PROCEDURES MENU
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES
Applicable to: ALL
Ident.: PRO-NOR-SUP-SUP-SUP-00-00020244.0001001 / 17 MAR 17
ADVERSE WEATHER
[SUP] AIRFRAME DEICING/ANTI-ICING PROCEDURE ON GROUND (Refer to procedure)
[SUP] GROUND OPERATIONS IN COLD WEATHER CONDITIONS (Refer to procedure)
[SUP] GROUND OPERATION IN HEAVY RAIN (Refer to procedure)
[SUP] MINIMUM SPEED WITH ICE ACCRETION (Refer to procedure)
[SUP] OPERATIONS ON CONTAMINATED AIRPORTS (Refer to procedure)
[SUP] OPERATIONS WITH VOLCANIC ASH, SAND OR DUST (Refer to procedure)
[SUP] SECURING THE AIRCRAFT FOR COLD SOAK (Refer to procedure)
[SUP] FOR DRAINING WATER PROCEDURE (Refer to procedure)
[SUP] WATER SYSTEM DRAINING (Refer to procedure)
Ident.: PRO-NOR-SUP-SUP-SUP-00-00020245.0001001 / 20 MAR 17
COMMUNICATION
[SUP] VHF, HF UTILIZATION (Refer to procedure)
Ident.: PRO-NOR-SUP-SUP-SUP-00-00020248.0001001 / 17 MAR 17
ENGINE
[SUP] MANUAL ENGINE START (Refer to procedure)
[SUP] ENGINE START WITH EXTERNAL PNEUMATIC POWER (Refer to procedure)
[SUP] CROSSBLEED ENGINE START (Refer to procedure)
[SUP] ENGINE START VALVE MANUAL OPERATION (Refer to procedure)
[SUP] ENGINE VENTILATION (DRY CRANKING) (Refer to procedure)
[SUP] ONE ENGINE TAXI (Refer to procedure)
Ident.: PRO-NOR-SUP-SUP-SUP-00-00020249.0001001 / 17 MAR 17
FUEL
[SUP] REFUELING (Refer to procedure)
[SUP] REFUELING WITH ONE ENGINE RUNNING (Refer to procedure)
[SUP] GROUND FUEL TRANSFER (Refer to procedure)
[SUP] DEFUELING (Refer to procedure)
Ident.: PRO-NOR-SUP-SUP-SUP-00-00020251.0001001 / 17 MAR 17
LANDING GEAR
[SUP] OPERATION WITH NOSEWHEEL STEERING OFFSET (Refer to procedure)
[SUP] FLIGHT WITH GEAR DOWN (Refer to procedure)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SUP-SUP P 1/2
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES SUPPLEMENTARY PROCEDURES MENU
Ident.: PRO-NOR-SUP-SUP-SUP-00-00020254.0001001 / 17 MAR 17
MISCELLANEOUS
[SUP] MISCELLANEOUS (Refer to procedure)
Ident.: PRO-NOR-SUP-SUP-SUP-00-00020252.0001001 / 17 MAR 17
NAVIGATION
[SUP] INSERTION OF APPROACH MINIMA (Refer to procedure)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SUP-SUP P 2/2
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
AIRFRAME DEICING/ANTI-ICING PROCEDURE ON GROUND
Applicable to: ALL
Ident.: PRO-NOR-SUP-ADVWXR-A-00020694.0001001 / 21 MAR 17
BEFORE FLUID SPRAYING
In all situations, it is the captain’s responsibility to decide if the ground crew must deice/anti-ice the
aircraft, and/or if additional deicing/anti-icing treatment are required.
CAUTION
L2
L1
L2
L1
L2
L1
L2
L1
‐ Make sure that the low or high-pressure ground connectors do not supply any
external air to the aircraft.
‐ If it is necessary for the ground crew to repeatedly anti-ice the aircraft, they
must deice the surfaces with a hot fluid mixture before applying a new layer of
anti-icing fluid.
COMMUNICATION WITH GROUND CREW..................................................................ESTABLISH
Establish communication with the crew that will apply the procedure.
DEICING/ANTI-ICING FLUIDS TYPE......................................................... CHECK APPROPRIATE
Check that the ground crew uses the correct deicing/anti-icing fluids, in accordance with the
applicable operator requirements and aircraft maintenance manual (AMM).
DO NOT START THE ENGINES DURING FLUID SPRAYING
Engines and APU can be either stopped or running during deicing/anti-icing.
CAUTION
Note:
‐ The ground crew should take care when spraying deicing fluid, and make sure
that the engines and APU do no ingest any fluid.
‐ Do not move flaps, slats, ailerons, spoilers or elevators if they are not free of
ice.
‐ Always ensure that both left and right side of the aircraft receive the same
complete and symmetrical deicing/anti-icing treatment.
In case of frost formation on one or several areas of the wing, the Captain can request a
local deicing application only on the affected areas. The Captain shall take care that both
wings receive the same symmetrical treatment, even if frost formation does not affect
both wing symmetrically. For more information, refer to AMM.
CAB PRESS MODE SEL............................................................................................CHECK AUTO
ENG 1 BLEED............................................................................................................................. OFF
ENG 2 BLEED............................................................................................................................. OFF
APU BLEED.................................................................................................................................OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SUP-ADVWXR P 1/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L2
L1
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
DITCHING pb................................................................................................................................ ON
Outflow valve, pack valves, and avionic ventilation inlet and extract valves close.
This prevents deicing/anti-icing fluid from entering the aircraft. Avionic ventilation is in a closed
circuit with both fans running. In view of the low OAT, there is no time limit for this configuration.
Note:
For passenger comfort reason, it is not recommended to operate on ground with both
PACKS set to OFF for more than 20 min.
Note:
If the “VENT AVNCS SYS FAULT” alert appears, reset the AEVC circuit breaker at the
end of the aircraft deicing/anti-icing procedure.
AIR COND /AVNCS VENT/CTL D06 on 49VU.
AIR COND /AVNCS /VENT/MONG Y17 on 122 VU.
THRUST LEVERS.........................................................................................................CHECK IDLE
“AIRCRAFT PREPARED FOR SPRAYING”........................................... INFORM GROUND CREW
Ident.: PRO-NOR-SUP-ADVWXR-A-00002311.0001001 / 20 SEP 16
UPON COMPLETION OF THE SPRAYING OPERATION
DITCHING pb...............................................................................................................................OFF
OUTFLOW VALVE......................................................................................................CHECK OPEN
On the ECAM PRESS page, confirm that the outflow valve indication reaches the open green
position to avoid any unexpected aircraft pressurization.
ENG BLEED 1 + 2........................................................................................................................ ON
PITOTS and STATICS (ground crew)....................................................................................CHECK
CAUTION
When the OAT is low (below -5 °C) during snow/freezing rain precipitations ,
melted snow or raindrops may drip from the cockpit windshields and freeze on
the fuselage below. This could create ice build up on the forward fuselage that
could possibly disturb the airflow around the static/pitot/angle-of-attack probes,
and result in unreliable air data measurements during takeoff. Therefore, during
taxi out before takeoff, beware of this possible build up of ice. The area around
static/pitot/angle-of-attack probes must be free of ice/snow before starting takeoff.
GROUND EQUIPMENT...................................................................................................... REMOVE
DEICING/ANTI-ICING REPORT.......................................................................................RECEIVED
The information from ground personnel, who performed the deicing/anti-icing and post-application
check, must include (ANTI-ICING CODE):
• Type of fluid used
• The mix ratio of fluid to water (for example 75/25)
• When the holdover time began.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SUP-ADVWXR P 2/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
At least 5 minutes after completion of spraying operation:
APU BLEED.................................................................................................................AS RQRD
Note:
There is a risk of de-icing fluid ingestion by the APU air intake, resulting in specific
odors, or smoke warnings. Therefore:
‐ Keep the APU running with the APU BLEED OFF for 5 min after spraying
completion before setting the APU BLEED to ON (if required),
‐ Consider APU BLEED OFF for takeoff.
NORMAL PROCEDURE..................................................................................................... RESUME
Apply appropriate normal procedures. Pay special attention to the flight control check. In freezing
precipitation, perform the appropriate checks to evaluate aircraft icing. Base the decision on
whether to takeoff, or to re-protect the aircraft, on the amount of ice that has built up on the critical
surfaces since the last deicing/anti-icing, as revealed by a personal inspection from the inside and
outside of the aircraft. Make this inspection before the holdover time expires, or just before takeoff.
GROUND OPERATIONS IN COLD WEATHER CONDITIONS
Applicable to: ALL
Ident.: PRO-NOR-SUP-ADVWXR-B-00020703.0001001 / 21 MAR 17
GENERAL
For ground operations on contaminated runways, Refer to PER-TOF-CTA-10 GENERAL and
Refer to PRO-NOR-SUP-ADVWXR General.
The following procedures supplement the normal operating procedures.
Ident.: PRO-NOR-SUP-ADVWXR-B-00020698.0001001 / 21 MAR 17
SAFETY EXTERIOR INSPECTION
PROTECTIVE COVERS...................................................................................................REMOVED
APU INTAKE.............................................................................CHECK FREE OF SNOW AND ICE
PACKS INLET/OUTLET DOORS..............................................CHECK FREE OF SNOW AND ICE
OUTFLOW VALVES................................................................. CHECK FREE OF SNOW AND ICE
PRESSURE RELIEF VALVES.................................................. CHECK FREE OF SNOW AND ICE
ABOVE ITEMS.............................................................................................DEICE IF NECESSARY
Ident.: PRO-NOR-SUP-ADVWXR-B-00020699.0001001 / 21 MAR 17
PRELIMINARY COCKPIT PREPARATION
L2
PRELIMINARY COCKPIT PREPARATION - SOP.......................................................COMPLETED
APU is started and the air conditioning is on.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
PRO-NOR-SUP-ADVWXR P 3/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
L1
L2
L1
L2
L1
‐ Ground power should be used to start the APU if the OAT is -15 °C (5 °F) or below.
‐ With cockpit temperatures below -15 °C (5 °F), the display units may not be available.
If the avionics bay is cold soaked:
The aircraft was parked without electrical ground supply or without air conditioning.
IRS...........................................................................................................INITIATE ALIGNMENT
For temperatures at or below -15 °C (5 °F) in the avionics bay, the IRS alignment requires
15 min.
WINDSHIELD AND UPPER COCKPIT FUSELAGE.....................................ICE/SNOW REMOVED
CAUTION
L2
L1
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
With ice or snow accumulated on the windshield and/or the upper cockpit
fuselage, and if the PROBE/WINDOW HEAT is on, melted ice or snow running
down from these areas could re-freeze on the fuselage area below, if the
temperature is very low. This could create ice build-up on the forward fuselage
that could possibly disturb the airflow around the static/pitot/angle-of-attack
probes.
PROBE COVERS............................................................................................... CHECK REMOVED
Ensure that the probe covers are removed in order to prevent the covers from melting.
PROBE/WINDOW HEAT...............................................................................................................ON
Ident.: PRO-NOR-SUP-ADVWXR-B-00020700.0001001 / 21 MAR 17
EXTERIOR WALKAROUND
L2
SURFACES ............................................................... CHECK FREE OF FROST, ICE AND SNOW
Check critical surfaces: leading edges, upper wing surfaces, vertical and horizontal stabilizers, all
control surfaces, slats and flaps.
Note:
L1
L2
L1
L2
L1
Thin hoarfrost is acceptable on the upper surface of the fuselage. Refer to
LIM-ICE_RAIN Definition of Thin Hoarfrost
On the underside of the wing tank areas, a maximum layer of 3 mm (0.125 in) of frost is
acceptable.
LANDING GEAR......................................................... CHECK FREE OF FROST, ICE AND SNOW
Check gear assemblies, lever locks, tires and doors
ENGINES....................................................................CHECK FREE OF FROST, ICE AND SNOW
Check inlets, inlet lips, fans, spinners, fan exhaust ducts, reversers assemblies.
ENGINE FANS.........................................................................................CHECK FREE ROTATION
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SUP-ADVWXR P 4/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L2
L1
L2
L1
L2
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
Check that engine fans are not stuck and can rotate freely.
DRAINS, BLEEDS, PROBES......................................CHECK FREE OF FROST, ICE AND SNOW
Probes: pitot tubes, static ports, TAT sensors and AOA sensors.
FUEL TANK VENTS................................................... CHECK FREE OF FROST, ICE AND SNOW
RADOME.................................................................... CHECK FREE OF FROST, ICE AND SNOW
WATER SUPPLIES............................................................ CHECK NOT FROZEN AND REFILLED
Commercial water supplies should have been previously emptied prior to aircraft cold soak.
Ident.: PRO-NOR-SUP-ADVWXR-B-00020701.0001001 / 21 MAR 17
AFTER START
L2
L1
After first engine start:
PROBE/WINDOW HEAT....................................................................................................AUTO
Heating will continue to operate automatically.
NORMAL PROCEDURE...............................................................................................RESUME
GROUND OPERATIONS IN HEAVY RAIN
Ident.: PRO-NOR-SUP-ADVWXR-00020720.0001001 / 21 MAR 17
Applicable to: ALL
L2
L1
L2
L1
L2
On ground (Aircraft taxiing or parked) in case of heavy rain, water may enter the avionics ventilation
system via the skin air inlet valve.
When on ground:
EXTRACT...............................................................................................................................OVRD
This closes the skin air inlets, preventing rainwater from entering the avionics bay.
PACK 1 ON......................................................................................................................... CHECK
PACK 2 ON......................................................................................................................... CHECK
Air conditioning compensates the avionics cooling reduction when the skin air inlet is closed.
If air conditioning not available:
When the aircraft avionics are powered, closing the skin air inlet valve reduces avionics
cooling capability. With air conditioning not available, the reduced cooling is efficient for a
limited period of time, depending on the outside temperature.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-NOR-SUP-ADVWXR P 5/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
FLIGHT CREW
OPERATING MANUAL
L1
Aircraft should not remain powered more than:
‐ OAT ≤ 39 °C (102 °F): no limit
‐ 39 °C (102 °F ) < OAT ≤ 45 °C (113 °F): 3 h
‐ 45 °C (113 °F) < OAT: 30 min
After takeoff:
EXTRACT............................................................................................................................... AUTO
MINIMUM SPEED WITH ICE ACCRETION
Ident.: PRO-NOR-SUP-ADVWXR-00020722.0002001 / 21 MAR 17
Applicable to: ALL
Evidence of ice accretion can be ice on the visual indicator (between the two cockpit windshields) or
on the windshield wipers.
CAUTION
Extended flight in icing conditions with the slats extended should be avoided.
If wing anti ice is operative:
In CONF clean, 1, 2 or 3:
MIN SPEED: VLS + 10 kt
In CONF FULL:
MIN SPEED: VLS + 5 kt
The minimum speed takes into account ice accretion on non-heated structure.
If wing anti ice is not operative:
MIN SPEED: VLS + 10 kt/GREEN DOT
The minimum speed takes into account ice accretion on the entire airframe when anti-ice is
inoperative.
OPERATIONS ON CONTAMINATED AIRPORTS
Applicable to: ALL
Ident.: PRO-NOR-SUP-ADVWXR-C-00020729.0001001 / 21 MAR 17
GENERAL
If the ground surfaces are not contaminated but the weather corresponds to icing conditions with
falling rain, slush or snow, anticipate a probable resulting runway/surfaces contamination.
There is a low probability of fluid ingestion by the engines which should anyway not degrade the
safety. The risk of ingestion is independent of the depth of the contaminant.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to E →
PRO-NOR-SUP-ADVWXR P 6/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
Ident.: PRO-NOR-SUP-ADVWXR-C-00020726.0002001 / 21 MAR 17
SPURIOUS ALERTS
The radio altimeter indication may fluctuate on contaminated surfaces and trigger auto callouts or
GPWS warnings. These alerts can be disregarded.
Note:
Spurious GPWS warnings may trigger at the apron, during taxi, takeoff and landing runs.
The radio altimeter may also not compute valid data:
‐ On surfaces covered with snow, ice or deicing fluid, and/or
‐ Due to deicing fluid on the antenna.
Note:
As a result, the "NAV RA 1(2)(1+2) FAULT" ECAM alert may be triggered. This alert may
disappear when the radio altimeter provides valid data again, when:
‐ The aircraft is on a non-contaminated surface, or
‐ The antenna is cleaned, or
‐ A period of time elapses after deicing, allowing the fluid covering the antenna to dry. The taxi
time between deicing spot and holding point may be sufficient.
In case of invalid LGCIU information, disregard the following alerts if triggered:
‐ ENG DUAL FAILURE
‐ ANTI-ICE CAPT(F/O) TAT FAULT
‐ L/G SHOCK ABSORBER FAULT
Ident.: PRO-NOR-SUP-ADVWXR-C-00020725.0001001 / 21 MAR 17
PARKING
L2
L1
L2
L1
After engine shutdown and before shutting down electrical supply:
FLAPS/SLATS............................................................. CONFIRM FREE OF CONTAMINATION
Perform a visual inspection to determine if the flaps/slats mechanism is free of contamination.
If necessary, perform decontamination.
YELLOW ELEC PUMP pb......................................................................................................ON
BLUE ELEC PUMP pb.......................................................................................................AUTO
BLUE PUMP OVRD pb.......................................................................................................... ON
SLATS/FLAPS............................................................................................................. RETRACT
Monitor slats/flaps retraction on ECAM upper display.
When slats and flaps are retracted:
YELLOW ELEC PUMP pb..............................................................................................OFF
BLUE PUMP OVRD pb.................................................................................................. OFF
NORMAL PROCEDURE........................................................................................ RESUME
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-NOR-SUP-ADVWXR P 7/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
OPERATIONS WITH VOLCANIC ASH, SAND OR DUST
Applicable to: ALL
Ident.: PRO-NOR-SUP-ADVWXR-G-00020733.0001001 / 21 MAR 17
PRELIMINARY COCKPIT PREPARATION
L2
L1
L2
L1
L2
APU................................................................................................................................. AVOID USE
Request ground power for air conditioning and electricity. If ground power is not available, the APU
should be used only to start the engines.
WINDSHIELD WIPERS............................................................................................... DO NOT USE
Do not use the windshield wipers to remove ash, sand or dust.
For takeoff performance:
BRAKING PERFORMANCE MAY BE DEGRADED
A layer of volcanic ash, sand or dust on the runway may degrade the braking efficiency.
Ident.: PRO-NOR-SUP-ADVWXR-G-00020734.0001001 / 21 MAR 17
EXTERIOR WALKAROUND
L2
L1
L2
SURFACES AND EQUIPMENT.........................................................CHECK FREE OF DEPOSITS
Ground maintenance should remove ash, sand or dust that has settled on exposed lubricated
surfaces and could penetrate seals or enter the engine gas path, air conditioning system, air data
probes, access doors and panels and other orifices on the aircraft.
ENGINE/APU INLETS....................................................................... CHECK FREE OF DEPOSITS
Inspect the inlets and order them cleaned of deposit. Have the area within 8 m (25 ft) of the engine
inlet cleaned of volcanic ash, as much as practical.
Ident.: PRO-NOR-SUP-ADVWXR-G-00020735.0001001 / 21 MAR 17
ENGINE START
L2
Use external pneumatic supply, if available, to start the engines. Refer to PRO-NOR-SUP-ENG
Engine Start with External Pneumatic Power.
ENGINE.................................................................................................................................. CRANK
Before starting the engines, ventilate them by dry cranking at maximum motoring speed for two
minutes. This will blow away any contaminant ash that may have entered the booster area.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PRO-NOR-SUP-ADVWXR P 8/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
Ident.: PRO-NOR-SUP-ADVWXR-G-00020736.0001001 / 21 MAR 17
TAXI
L2
L1
L2
L1
L2
ONE ENGINE TAXI...........................................................................................DO NOT PERFORM
Minimize the thrust during taxi.
ENG 1 BLEED............................................................................................................................. OFF
ENG 2 BLEED............................................................................................................................. OFF
Keep engine bleed valves closed for taxiing, especially in volcanic ash.
FOR 180 ° TURN ON RUNWAY: INITIATE THE TURN DOWNWIND
In order to prevent ash, sand or dust ingestion.
Ident.: PRO-NOR-SUP-ADVWXR-G-00020737.0001001 / 21 MAR 17
TAKEOFF
L2
L1
L2
L1
ASH, SAND OR DUST..................................................................................... ALLOW TO SETTLE
Allow ash, sand or dust to settle on runway before starting the takeoff roll.
PACK OFF TAKEOFF..................................................................................................... CONSIDER
This will prevent air conditioning system contamination.
ROLLING TAKEOFF........................................................................................................CONSIDER
Ident.: PRO-NOR-SUP-ADVWXR-G-00020738.0001001 / 21 MAR 17
AFTER TAKEOFF
L2
L1
MINIMIZE TIME IN SAND OR DUST CLOUD
Climb to quickly exit the sand/dust cloud. If possible, altitude constraints may be disregarded in
coordination with ATC.
ENG 1 BLEED...............................................................................................................................ON
ENG 2 BLEED...............................................................................................................................ON
Ident.: PRO-NOR-SUP-ADVWXR-G-00020739.0001001 / 21 MAR 17
IN FLIGHT
L2
L1
AVOID ASH, SAND OR DUST CLOUD
If sand or dust cloud encounter:
MINIMIZE TIME IN SAND OR DUST CLOUD
If possible and in coordination with ATC, adapt flight path (route and altitude) to exit the cloud.
If ash cloud encounter:
VOLCANIC ASH ENCOUNTER PROCEDURE............................................................... APPLY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-NOR-SUP-ADVWXR P 9/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
Refer to PRO-ABN-MISC [QRH] VOLCANIC ASH ENCOUNTER .
Ident.: PRO-NOR-SUP-ADVWXR-G-00020740.0001001 / 21 MAR 17
DESCENT PREPARATION
L2
L1
L2
AUTOLAND RECOMMENDED
Deposits on the windshield and landing lights may significantly reduce visibility during approach
and landing. Consider a diversion to an airport where autoland is possible.
For landing performance:
CONSIDER IDLE REVERSE
BRAKING PERFORMANCE MAY BE DEGRADED
A layer of volcanic ash, sand or dust on the runway may degrade the braking efficiency.
Ident.: PRO-NOR-SUP-ADVWXR-G-00020741.0001001 / 21 MAR 17
DESCENT
AVOID LEVEL FLIGHT IN ASH, SAND OR DUST CLOUD
If possible and in coordination with ATC, perform holding patterns and last level off before final
descent outside of the cloud.
Ident.: PRO-NOR-SUP-ADVWXR-G-00020742.0001001 / 21 MAR 17
LANDING
L2
L1
L2
Before Landing:
ENG 1 BLEED...................................................................................................................... OFF
ENG 2 BLEED...................................................................................................................... OFF
PACK 1 and 2..................................................................................................... AS REQUIRED
Consider to set the packs OFF in order to avoid contamination of the air conditioning system.
During Landing:
REVERSERS.......................................................................................................AS REQUIRED
If it appears that maximum reverse thrust is needed, apply reverse thrust when the main
landing gear touches down. Limit the use of reverse thrust as much as possible, because
reverse flow may throw up ash, sand or dust and impair visibility.
Ident.: PRO-NOR-SUP-ADVWXR-G-00020744.0001001 / 21 MAR 17
AFTER LANDING
L2
L1
ONE ENGINE TAXI...........................................................................................DO NOT PERFORM
Minimize thrust during taxi.
APU................................................................................................................................. AVOID USE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-NOR-SUP-ADVWXR P 10/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
FOR 180 ° TURN ON RUNWAY: INITIATE THE TURN DOWNWIND
Ident.: PRO-NOR-SUP-ADVWXR-G-00020745.0001001 / 21 MAR 17
SECURING THE AIRCRAFT
L2
L1
L2
L1
L2
L1
If the aircraft is parked at an airport covered with volcanic ash, sand or dust, install engine inlet
covers and other protective covers and plugs.
In addition:
After switching off all bleeds and before switching off the electrical AC power:
DITCHING pb..........................................................................................................................ON
This closes the outflow valve, pack valves and avionics ventilation inlet and extract valves.
After switching off the electrical AC power and the batteries:
DITCHING pb........................................................................................................................ OFF
All the applicable valves will open at the next power-up.
PROTECTIVE COVERS................................................................................................INSTALL
Request ground crew to install protective covers and plugs, in order to protect the aircraft and
engines from volcanic ash, sand or dust.
LOGBOOK......................................... REPORT ASH, SAND OR DUST CLOUD ENCOUNTER
SECURING THE AIRCRAFT FOR COLD SOAK
Ident.: PRO-NOR-SUP-ADVWXR-00020772.0001001 / 21 MAR 17
Applicable to: ALL
WHEN SECURING THE AIRCRAFT
L2
L1
L2
L1
L2
L1
L2
After switching off all bleeds and before switching off the electrical AC power:
DITCHING pb ........................................................................................................................ ON
This closes the outflow valve, pack valves and avionics ventilation inlet and extract valves.
When the chocks are in place:
PARKING BRAKE pb .......................................................................................................... OFF
Releasing the parking brake prevents the brakes from freezing.
After switching off the electrical AC power and the batteries:
DITCHING pb .......................................................................................................................OFF
All the applicable valves will open at the next power-up.
PROTECTIVE COVERS................................................................................................INSTALL
Request ground crew to install protective covers and plugs, in order to protect the wheels, the
engines and the probes from snow and ice.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G →
PRO-NOR-SUP-ADVWXR P 11/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L1
L2
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
WATER SYSTEM DRAINING.....................................................................................REQUEST
Request maintenance actions to drain the water system for cold soak prevention purposes.
Refer to PRO-NOR-SUP-ADVWXR Water System Draining.
FOR DRAINING WATER PROCEDURE
Applicable to: ALL
Ident.: PRO-NOR-SUP-ADVWXR-D-00002313.0001001 / 21 MAR 17
INTRODUCTION
This procedure uses electrical power.
ACCESS PLATFORM(S)......................................................................................PUT IN POSITION
SHUTOFF VALVE IN GALLEYS/TOILETS................................................................ CHECK OPEN
FWD/AFT ACCESS PANEL DOORS.......................................................................................OPEN
DRAIN PORT CAPS........................................................................................................... REMOVE
Remove drain port caps on forward drain and aft service panels.
DRAIN HOSES..................................................................................................................CONNECT
Connect drain hoses to :
• the drain port on the forward drain panel.
• the full/drain port on the aft service panel.
Ident.: PRO-NOR-SUP-ADVWXR-D-00002314.0001001 / 21 MAR 17
ON THE FORWARD DRAIN PANEL
DRAIN CONTROL HANDLE...........................................................................................TURN LEFT
Turn the control handle to drain.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← G to H →
PRO-NOR-SUP-ADVWXR P 12/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
Ident.: PRO-NOR-SUP-ADVWXR-D-00002315.0001001 / 21 MAR 17
ON THE AFT SERVICE PANEL
FILL/DRAIN CONTROL HANDLE.....................................................TURN TO “DRAIN” AND PULL
Turn the handle to the “DRAIN” position and pull it out to its mechanical stop to drain.
The indicator light comes on.
Ident.: PRO-NOR-SUP-ADVWXR-D-00002316.0001001 / 21 MAR 17
WHEN THE WATER SYSTEM IS DRAINED
In freezing conditions, the drain valves must stay open to prevent damage to the system. Do not
put on the caps and leave the access door open.
DRAIN HOSES............................................................................................................DISCONNECT
PANELS................................................................................................................ CLEAN AND DRY
ACCESS PLATFORM(S).................................................................................................... REMOVE
WATER SYSTEM DRAINING
Ident.: PRO-NOR-SUP-ADVWXR-00002205.0001001 / 21 MAR 17
Applicable to: ALL
Drain the water system, if the OAT requires it, as shown below :
Air Conditioning
ON
OFF
Configuration
Cabin
Outside Air Temperature
temperature
Above
Between 0 °C and -15 °C (32 °F and
10 °C
5 °F)
(50 °F)
Below -15 °C (5 °F)
Between 0 °C and -7 °C (32 °F and
19.4 °F)
Between -7 °C and -15 °C (19.4 °F and
5 °F)
Below -15 °C (5 °F)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← H to I
Exposure time
None
Water tank drain
Not required
1 h 15 min
1 h 30 min
0 h 30 min
Required
Any
PRO-NOR-SUP-ADVWXR P 13/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ADVERSE WEATHER
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SUP-ADVWXR P 14/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - COMMUNICATION
VHF, HF UTILIZATION
Applicable to: ALL
Ident.: PRO-NOR-SUP-COM-A-00002210.0001001 / 21 MAR 17
Note:
1. Reception of some frequencies could be noisy, on one or more VHFs. In such cases, try
selecting an unaffected one.
2. If two frequencies are closer than 2 MHz (between VHF 1 and 2, or between VHF 3 and
2), or closer than 6 MHz (between VHF1 and 3), some interference may occur.
Ident.: PRO-NOR-SUP-COM-A-00002211.0002001 / 22 MAR 17
TUNING
The pilot should normally use his onside RMP to tune any one of the VHF or HF radios. If the SEL
lights come on, when tuning the radio, the pilot should turn them off by selecting the appropriate
radio system dedicated to his RMP.
ON/OFF switch................................................................................................................ CHECK ON
VHF or HF key....................................................................................................................... PRESS
The green light comes on.
ACTIVE and STBY/CRS windows display active and preset frequencies, respectively.
Note:
When an RMP tunes a transceiver that is normally associated with another RMP , the
SEL lights on both RMPs come on.
TO CHANGE FREQUENCY
Rotating knob........................................................................................................................ TURN
Make the STBY/CRS window display the new frequency.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SUP-COM P 1/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - COMMUNICATION
Outer knob is for units, inner knob for decimals.
Transfer key........................................................................................................................ PRESS
This interchanges the ACTIVE and STBY frequencies.
The receiver is now tuned to the new ACTIVE frequency.
AM key (if necessary).........................................................................................................PRESS
Green light comes on.
SEL lt......................................................................................................................... CHECK OFF
If SEL light is on, select the appropriate radio systems dedicated to the on side RMP.
FAILURE CASES
When an RMP fails :
‐ The affected RMP no longer controls the selected receiver.
‐ The frequency displays disappear and the green VHF or HF lights go out.
Affected RMP........................................................................................................... SWITCH OFF
One RMP can control all receivers.
•
•
•
•
if RMP 1 fails tune VHF 1 through RMP 3
if RMP 2 fails tune VHF 2 through RMP 3
if RMP 3 fails tune, HF1 through RMP 1, HF2 through RMP 2
if two RMP ’s fail, tune all receivers through the remaining RMP.
Ident.: PRO-NOR-SUP-COM-A-00002212.0004001 / 03 JAN 11
TRANSMISSION AND RECEPTION
Note:
If the VHF3 VOICE DIRECTORY page is customized with user frequencies:
‐ Use it as a pure directory
‐ Do not press the key adjacent to the desired frequency for direct turning
‐ VHF 3 in VOICE mode should either be tuned using the MANUAL FREQ field, or using
the RMP.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SUP-COM P 2/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - COMMUNICATION
VHF or HF transmission key.................................................................................................. PRESS
Green bars on the selected system key light up.
Microphones and PTT command are connected to the selected system.
VHF or HF reception key....................................................................................................... PRESS
The integrated white light comes on.
The receiver brings in the selected system.
To adjust the volume, turn the key.
Note:
Do not use VHF 3 for communications with ATC , if ACARS is installed, unless VHF 1
and VHF 2 are inoperative.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SUP-COM P 3/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - COMMUNICATION
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SUP-COM P 4/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ENGINES
MANUAL ENGINE START
Applicable to: ALL
Ident.: PRO-NOR-SUP-ENG-A-00009443.0001001 / 21 MAR 17
Pilots normally use automatic starting to start an engine.
However, manual starting is recommended in the following cases:
‐ After aborting a start, because of:
• Engine stall
• Engine EGT overlimit
• Low start air pressure
‐ When expecting a start abort, because of:
• Degraded bleed performance, due to hot conditions, or at a high-altitude airfields.
• An engine with a reduced EGT margin, in hot conditions, or at a high-altitude airfields.
• Marginal performance of the external pneumatic power group.
Ident.: PRO-NOR-SUP-ENG-A-00020858.0003001 / 17 MAR 17
MANUAL ENGINE START PROCEDURE
Note:
During a manual engine start, if the flight crew suspects an engine start malfunction, or
if an engine-related ECAM alert is triggered, the PF must abort the start sequence as
follows:
‐ Before the PF sets the ENG MASTER lever to ON, the PF must set the ENG MAN
START pb-sw to OFF
‐ After the PF sets the ENG MASTER lever to ON, the PF must set the ENG MASTER
lever to OFF, and then the ENG MAN START pb-sw to OFF.
In that case, the flight crew should consider a dry crank cycle of the affected engine
before they perform another start attempt (Refer to PRO-NOR-SUP-ENG Engine
Ventilation (Dry Cranking)).
Then, in the case of an ECAM alert, the PF must announce "ECAM actions", in
accordance with the ECAM management philosophy.
THR LEVERS..............................................................................................................................IDLE
CAUTION
L2
The engines start regardless of the thrust lever position. If the thrust levers are not
set to IDLE, the thrust rapidly increases to the corresponding thrust lever position,
causing a hazardous situation.
ENG MODE sel........................................................................................ NORM THEN IGN/START
The lower ECAM displays the engine page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SUP-ENG P 1/10
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L1
L2
Note:
SUPPLEMENTARY PROCEDURES - ENGINES
If both engines are started manually, the following procedure applies one engine at a
time.
When all engines parameters are available on the upper ECAM display (no amber
crosses displayed):
ENG MAN START pb-sw....................................................................................................... ON
START VALVE...................................................................................................CHECK IN-LINE
OIL PRESS INCREASE.................................................................................................. CHECK
N2 INCREASE................................................................................................................. CHECK
If the N2 does not reach 20 %:
PACK VALVES..........................................................................................CHECK CLOSED
If the APU bleed is used for engine start and the pack valves are closed, shed
the APU electrical loads as follows:
Shedding APU electrical loads enables to increase bleed air pressure.
GALY & CAB............................................................................................................OFF
If needed, shed also:
BLUE ELEC PUMP (on ground only)................................................................OFF
FUEL X FEED..................................................................................................... ON
FUEL PUMPS (except R TK PUMP 2)............................................................. OFF
BLOWER....................................................................................................... OVRD
CAB FANS.........................................................................................................OFF
L1
When N2 reaches 22 % or the maximum motoring speed (20 % minimum):
Note:
L2
L1
The maximum motoring speed is defined as the speed at which N2 acceleration is
less than 1 % in approximately 5 s.
ENG MASTER........................................................................................................................ ON
CHRONO.......................................................................................................................... START
The PM starts the timing in order to monitor the light-up duration.
IGNITERS A AND B................................................................................................. CHECK ON
FUEL FLOW INCREASE.................................................................................................CHECK
15 s maximum after fuel flow increase:
EGT INCREASE.............................................................................................................. CHECK
N1 INCREASE................................................................................................................. CHECK
If the electrical power supply is interrupted during the start sequence (indicated by loss of
ECAM displays), abort the start by setting the ENG MASTER lever to OFF. Then perform a
30 s dry crank (Refer to PRO-NOR-SUP-ENG Engine Ventilation (Dry Cranking)).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SUP-ENG P 2/10
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L2
L1
SUPPLEMENTARY PROCEDURES - ENGINES
When N2 reaches 50 %:
START VALVE (between 50 and 56 % N2)............................................. CHECK CROSS LINE
IGNITERS A AND B................................................................................................CHECK OFF
MAIN ENG PARAMETERS.............................................................................CHECK NORMAL
SECONDARY ENG PARAMETERS............................................................... CHECK NORMAL
The gray background on the N2 indication disappears.
Note:
CFM 56-5B1/B2 engines, N2 accelerates slowly from 50 % to idle. Start abort is not
required as long as N2 increases.
ENG MAN START pb-sw......................................................................................................OFF
ENG MODE sel................................................................................................................. NORM
When no other engine requires to be started manually:
SHEDDED SYSTEMS.......................................................................................... RESTORE
SOP - ENGINE START..........................................................................................RESUME
ENGINE START WITH EXTERNAL PNEUMATIC POWER
Ident.: PRO-NOR-SUP-ENG-00020859.0002001 / 17 MAR 17
Applicable to: ALL
L2
L1
Before connecting external pneumatic power :
PACK 1......................................................................................................................................OFF
PACK 2......................................................................................................................................OFF
Packs are selected off to prevent any possible contamination of the packs by the external
pneumatic power.
APU BLEED.............................................................................................................................. OFF
ENG 1 BLEED.......................................................................................................................... OFF
ENG 2 BLEED.......................................................................................................................... OFF
X BLEED................................................................................................................................ OPEN
EXTERNAL PNEUMATIC POWER CONNECTION..............................................................REQUEST
When cleared to start :
ENG 2...................................................................................................................................START
Note:
As necessary, engine 1 can also be started by using the external pneumatic power.
If engine 1 is started first, check the brake ACCU pressure prior to engine start.
The minimum recommended starter air supply pressure is 30 PSI, when the start valve
is open.
Two external pneumatic power units may be used in parallel if necessary.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
PRO-NOR-SUP-ENG P 3/10
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ENGINES
After Engine 2 is started :
EXT PWR................................................................................................................. CHECK AVAIL
WARNING
Disconnection of the external power with the EXT PWR pb-sw ON may cause
injury to the ground engineer. Request disconnection of the external power only
with the EXT PWR pb-sw AVAIL.
EXT PWR DISCONNECTION........................................................................................ REQUEST
Note:
The external electrical power can be removed after the second engine start.
If external pneumatic power is used to start engine 1 :
ENG 1...................................................................................................................................START
When engine 1 is started:
EXTERNAL PNEUMATIC POWER REMOVAL....................................................... REQUEST
X BLEED..........................................................................................................................AUTO
ENG 1 BLEED......................................................................................................................ON
ENG 2 BLEED......................................................................................................................ON
PACK 1.................................................................................................................................ON
PACK 2.................................................................................................................................ON
If the crossbleed engine start procedure is used to start engine 1 :
EXTERNAL PNEUMATIC POWER REMOVAL..............................................................REQUEST
PACK 1....................................................................................................................................... ON
PACK 2....................................................................................................................................... ON
ENG 2 BLEED............................................................................................................................ ON
CROSSBLEED ENGINE START PROC.............................................................................. APPLY
Refer to PRO-NOR-SUP-ENG Crossbleed Engine Start
CROSSBLEED ENGINE START
Ident.: PRO-NOR-SUP-ENG-00020860.0001001 / 17 MAR 17
Applicable to: ALL
CAUTION
Do not perform the crossbleed engine start procedure during pushback.
Simultaneous use of engine bleed supply and external pneumatic power supply is
prohibited.
One engine must be running in order to supply air for other engine start.
Before second engine start :
APU BLEED.............................................................................................................................. OFF
L2
The BLEED valve of the supplying engine reopens and the cross bleed valve closes.
L1
ENG BLEED (supplying engine).................................................................................................ON
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-NOR-SUP-ENG P 4/10
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L2
L1
SUPPLEMENTARY PROCEDURES - ENGINES
ENG BLEED (receiving engine)................................................................................................OFF
The bleed valve of receiving engine is closed to avoid reverse flow leakage.
X BLEED................................................................................................................................ OPEN
When cleared to start :
AREA CLEAR OF OBSTACLES..................................................................................... CONFIRM
L2
Ensure increased power jet wake does not constitute any hazard to people or installation behind
the aircraft.
L1
THR LEVER (supplying engine).............................................. ADJUST FOR BLEED PRESSURE
Adjust thrust of supplying engine to obtain an engine bleed pressure of 30 PSI before start
initiation, and at least 25 PSI during the start sequence.
If the thrust required to obtain the appropriate engine bleed pressure exceeds 40 % N1, pay
particular attention to the surrounding area.
Note:
If the supplying engine is a DAC engine, preset a 30 % N1 before launching the start
sequence.
RECEIVING ENGINE........................................................................................................... START
Apply the normal engine start procedure.
After start :
THR LEVER (supplying engine).............................................................................................. IDLE
X BLEED................................................................................................................................ AUTO
ENG BLEED (receiving engine)................................................................................................. ON
PACK 1....................................................................................................................................... ON
PACK 2....................................................................................................................................... ON
ENGINE START VALVE MANUAL OPERATION
Ident.: PRO-NOR-SUP-ENG-00020861.0001001 / 17 MAR 17
Applicable to: ALL
BEFORE ENGINE START
Advise ground crew to prepare for manual engine start valve operation.
WARNING
To ensure safety of the ground crew when starting an engine with manual
operation of the start valve, the flight crew should start the affected engine first.
ENGINE START
AUDIO CONTROL PANEL..........................................................................................................CAB
GROUND CREW CLEARANCE............................................................................................OBTAIN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
PRO-NOR-SUP-ENG P 5/10
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ENGINES
When the ground crew is ready:
“ENGINE 1(2) START”............................................................................................ ANNOUNCE
ENG MODE sel.........................................................................................................IGN/START
ENG MASTER........................................................................................................................ ON
“OPEN START VALVE AND KEEP OPEN”....................................................................ORDER
If not maintained in the OPEN position by the ground crew, the start valve closes.
When N2 at 50 %:
“CLOSE START VALVE”................................................................................................ ORDER
SOP – ENGINE START............................................................................................... RESUME
ENGINE VENTILATION (DRY CRANKING)
Ident.: PRO-NOR-SUP-ENG-00020943.0001001 / 17 MAR 17
Applicable to: ALL
On ground, after:
‐ An unsuccessful manual engine start, or
‐ An unsuccessful automatic start not followed by an automatic dry crank,
the flight crew can perform a dry crank cycle on the affected engine to remove the fuel vapors.
Before dry crank:
ENG MASTER (affected engine)................................................................................ CHECK OFF
ENG MODE sel....................................................................................................... CHECK NORM
ENG MAN START pb-sw (affected engine)................................................................CHECK OFF
Dry crank:
ENG MODE sel................................................................................................................... CRANK
ENG MAN START pb-sw (affected engine)............................................................................... ON
Note:
To clear fuel vapors, a 30 seconds dry crank cycle is the minimum required.
L2
Note:
A manual start sequence can be initiated following a dry crank cycle (Refer to
PRO-NOR-SUP-ENG Manual Engine Start - Procedure). The flight crew should consider
the starter limitations (Refer to LIM-ENG Starter).
L1
When the dry crank is completed:
ENG MAN START pb-sw (affected engine)............................................................................. OFF
ENG MODE sel..................................................................................................................... NORM
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E
PRO-NOR-SUP-ENG P 6/10
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ENGINES
ONE ENGINE TAXI - GENERAL
Applicable to: ALL
Ident.: PRO-NOR-SUP-ENG-CA-00021004.0001001 / 17 MAR 17
Except in some operational conditions (e.g. uphill slopes, slippery taxiways or high gross weights),
brake life and fuel savings may govern company policy on permitting aircraft to taxi with one engine
shut down.
Before applying this procedure, the flight crew should be aware of the following:
‐ Taxi with one engine shut down may require higher thrust than usual. Caution must therefore be
exercised to avoid excessive jet-blast and the risk of Foreign Object Damage (FOD)
‐ Slow or tight turns in the direction of the operating engine may not be possible at high gross
weights
‐ When one engine taxi is planned, pay particular attention to the fuel imbalance limitation for the
next take-off.
ONE ENGINE TAXI - AT DEPARTURE
Applicable to: ALL
Ident.: PRO-NOR-SUP-ENG-CB-00021005.0002001 / 17 MAR 17
BRAKE ACCU PRESS...............................................................................................................CHECK
If necessary, use the Y ELEC PUMP to pressurize the brake accumulator.
L1 ENG 1......................................................................................................................................... START
L2 Engine 1 pressurizes the green hydraulic system, providing normal braking.
L1 X BLEED.......................................................................................................................................OPEN
L2 Open the cross bleed valve in order to supply both packs with engine 1.
L2
L1
APPLY THE “AFTER START” NORMAL PROCEDURE, BUT:
‐ Keep the APU running and switch the APU BLEED to OFF.
L2
The APU generator provides power to the engine fire extinguisher, prevents electrical transients
and enables galley operation. Closing the APU BLEED prevents engine exhaust gases ingestion
in the air conditioning system.
L1 ‐ Delay the ECAM STATUS check and the wing anti-ice setting until all engines are started.
Ident.: PRO-NOR-SUP-ENG-CB-00021007.0002001 / 17 MAR 17
BEFORE RELEASING THE PARKING BRAKE
L2
Y ELEC PUMP.............................................................................................................................. ON
This pressurizes the yellow hydraulic system, providing nosewheel steering without using the PTU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F to G →
PRO-NOR-SUP-ENG P 7/10
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L1
SUPPLEMENTARY PROCEDURES - ENGINES
APPLY THE “TAXI” NORMAL PROCEDURE, BUT:
‐ Delay the flight controls check until all engines are started
‐ Arm the autobrake after the flight controls check.
Ident.: PRO-NOR-SUP-ENG-CB-00021008.0006001 / 01 JUN 17
BEFORE TAKEOFF
ENGINE WARM-UP TIME BEFORE TAKEOFF (remaining engine)...............................CONSIDER
The second engine must be started soon enough before takeoff, in order to take into account the
engine start time and ensure the applicable engine warm-up time (Refer to PRO-NOR-SOP-09
After Start - ENG Mode Selector).
For ENG 2 start and when taxiing in a straight line:
L2
L1
Note:
During the engine start, a slight jerk forward may occur if the brakes are applied
while the aircraft is moving.
Note:
Maintain taxi in a straight line during at least 5 s after the selection of the ENG 2
master lever to ON, in order to ensure the PTU auto-test is completed.
Y ELEC PUMP......................................................................................................................OFF
The yellow electric pump must be set to OFF to enable PTU automatic test during engine 2
start.
APU BLEED............................................................................................................................ ON
ENG 2............................................................................................................................... START
APU.................................................................................................................................... AS RQRD
X BLEED................................................................................................................................... AUTO
APPLY THE “AFTER START” NORMAL PROCEDURE, INCLUDING:
‐ ECAM STATUS check
‐ Selection of the ENG 2 anti-ice and wing anti-ice, as required.
AFTER START CHECKLIST.......................................................................................... COMPLETE
FLIGHT CONTROLS..............................................................................................................CHECK
AUTO BRK.................................................................................................................................. MAX
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G
PRO-NOR-SUP-ENG P 8/10
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ENGINES
ONE ENGINE TAXI - AT ARRIVAL
Applicable to: ALL
Ident.: PRO-NOR-SUP-ENG-CC-00021009.0001001 / 17 MAR 17
L2
APU............................................................................................................................................. START
Start the APU before shutting down one engine, in order to provide power to the engine fire
extinguisher and avoid electrical transients.
Ident.: PRO-NOR-SUP-ENG-CC-00021010.0001001 / 17 MAR 17
After high thrust operations:
ENGINE MINIMUM COOLING TIME............................................................................ CONSIDER
Refer to PRO-NOR-SOP-22 Parking - ENG MASTER Levers.
When the APU indicates AVAIL and taxiing in a straight line:
Note:
L2
During engine shutdown, a slight jerk forward may occur if the brakes are applied while
the aircraft is moving.
ENG 2........................................................................................................................ SHUT DOWN
Y ELEC PUMP............................................................................................................................ON
This avoids running the PTU.
Ident.: PRO-NOR-SUP-ENG-CC-00021011.0001001 / 17 MAR 17
At parking:
Y ELEC PUMP..........................................................................................................................OFF
ENG 1........................................................................................................................ SHUT DOWN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
PRO-NOR-SUP-ENG P 9/10
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - ENGINES
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SUP-ENG P 10/10
19 JUN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - FUEL
REFUELING
Applicable to: ALL
Ident.: PRO-NOR-SUP-FUEL-A-00021256.0002001 / 25 JUL 17
WARNING
1. Prior initiation of any ground fuel operations, obey the below fuel safety
precautions. This will prevent injury to people and/or damage to the aircraft.
2. Do not request or perform any ground fuel operations if a fire or engine overheat
warning is displayed.
3. f the APU fails during any ground fuel operations, do not restart the APU. For
APU use during refueling/defueling Refer to LIM-APU APU Start/Shutdown during
Refueling/Defueling.
4. Do not refuel in bad weather conditions and electrical storms.
PREPARATION
SAFETY PRECAUTIONS........................................................................................................APPLY
During refueling operations, ensure that:
‐ HF transmission (including HF transmission via the HF DATA LINK pb) is not performed
‐ The aircraft is properly bonded to the tanker
‐ The tanker and the aircraft grounding requirement is based on local regulations. Always connect
the ground cable to the parking ground point (or to the tanker) before connecting it to the
aircraft.
‐ The external lighting is not operated (except for NAV & LOGO).
In the cockpit, check that the PARK BRK is ON and that the ACCU PRESS has sufficient
pressure. If the PARK BRK cannot be set to ON, check that the chocks are in place.
ACCESS PLATFORM...................................................................................................IN POSITION
MAX REFUELING PRESSURE: 50 PSI (3.5 bar)
On refueling control panel:
TEST sw................................................................................................................................ LTS
Lights on the panel come on. FUEL QTY and the PRESELECTED and ACTUAL displays
show 8’s.
TEST sw............................................................................................................................ HI.LVL
HI LVL lights change state if the high level sensors and their circuits are serviceable.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SUP-FUEL P 1/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - FUEL
Ident.: PRO-NOR-SUP-FUEL-A-00021257.0002001 / 21 MAR 17
AUTOMATIC REFUELING
On cockpit refueling control panel:
REFUEL PWR pb-sw..............................................................................................................ON
Cockpit panel takes priority. The CKPT light comes on and REFUELG is displayed on the
ECAM MEMO.
[PRESELECTOR sw] REQUESTED BLOCK FUEL............................................................. SET
REFUEL CTL pb-sw............................................................................................................... ON
Refueling starts. When refueling is finished, the END light comes on.
REFUEL CTL pb-sw..............................................................................................................OFF
REFUEL PWR pb-sw............................................................................................................OFF
On refueling control panel:
REFUEL VALVES sel................................................................CHECK NORM and GUARDED
[PRESELECTOR sw] REQUESTED BLOCK FUEL............................................................. SET
MODE SELECT sw........................................................................................................ REFUEL
START REFUELING
When the refueling is finished the END light comes on.
ACTUAL QUANTITY........................................................................................................CHECK
The actual quantity must be within 100 kg (220 lb) of the preselected quantity.
MODE SELECT sw.....................................................................................OFF and GUARDED
Ident.: PRO-NOR-SUP-FUEL-A-00021260.0001001 / 21 MAR 17
MANUAL REFUELING
REFUEL VALVES sel............................................................................................................... SHUT
MODE SELECT sw.............................................................................................................. REFUEL
REFUEL VALVES sel (tanks to be filled).................................................................................OPEN
START REFUELING
FUEL QTY..........................................................................................................................MONITOR
When the contents of the tanks reach the required level :
Corresponding REFUEL VALVES sel................................................................................ SHUT
MODE SELECT sw.....................................................................................OFF and GUARDED
REFUEL VALVES sel............................................................................. NORM and GUARDED
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SUP-FUEL P 2/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - FUEL
FLIGHT CREW
OPERATING MANUAL
REFUELING WITH ONE ENGINE RUNNING
Ident.: PRO-NOR-SUP-FUEL-00001677.0003001 / 21 MAR 17
Applicable to: ALL
‐ Refuel with one engine running only at airports where no external ground pneumatic power is
available and only when APU is unserviceable.
‐ Only the RH fuel couplings can be used.
‐ Overwing gravity filling is not permitted.
‐ Disembark all passengers.
‐ Obtain airport authorization.
The Airport Fire Department should standby at the aircraft during the entire refueling procedure.
‐ Point the aircraft into the wind at a location where the slope is negligible.
Set the parking brake and check its pressure.
Run engine n° 1 at ground idle with its generator connected.
‐ Do not start engine n° 2, do not shut down engine n° 1 or do not attempt to start the APU before all
fueling operations have been completed.
‐ Position the fuel truck under the extremity of the right wing. Its pressure should not exceed 30 PSI.
‐ Follow manual refueling procedure.
OPERATION MONITORING
DURING THE ENTIRE REFUELING PROCEDURE :
‐ Monitor the fuel truck shut off valve.
‐ Be sure that the fueling company is keeping permanent control of the emergency fuel shut off
device.
‐ Have a flight crew member in the cockpit monitoring all systems and the running engine.
‐ Have a qualified ground crew member at the fueling station to operate the refuel valve
switches.
‐ Monitor the refueling closely and be prepared to close the refuel valves in order not to exceed
the following fuel quantities :
DENSITY (kg/l)
L(R) WING (kg)
CENTER (kg)
0.77
5 710
6 030
0.78
5 780
6 110
0.79
5 860
6 190
0.8
5 930
6 270
0.81
6 005
6 350
0.82
6 080
6 430
0.83
6 160
6 500
AFTER SECOND ENGINE START :
Reset the 3DMCs in order to reinitialize the fuel used values :
DMC 1 SPLY C/B (E11 on 49VU).................................................................................. PULL
DMC 2 SPLY C/B (Q8 on 121 VU).................................................................................PULL
DMC 3 SPLY C/B (Q9 on 121 VU).................................................................................PULL
DMC 3 SPLY STBY (E10 on 49 VU)..............................................................................PULL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-NOR-SUP-FUEL P 3/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - FUEL
FLIGHT CREW
OPERATING MANUAL
After 5 s :
All C/B’s....................................................................................................................PUSH
Note:
The T.O MEMO does not appear automatically since one engine is kept
running.
GROUND FUEL TRANSFER
Ident.: PRO-NOR-SUP-FUEL-00021258.0001001 / 25 JUL 17
Applicable to: ALL
WARNING
1. Prior initiation of any ground fuel operations, obey the below fuel safety
precautions. This will prevent injury to people and/or damage to the aircraft.
2. Do not request or perform any ground fuel operations if a fire or engine overheat
warning is displayed.
3. If the APU fails during any ground fuel operations, do not restart the APU. For
APU use during refueling/defueling Refer to LIM-APU APU Start/Shutdown during
Refueling/Defueling.
SAFETY PRECAUTIONS............................................................................................................APPLY
During ground operations, ensure that:
‐ HF transmission is not performed (including HF transmission via the HF DATA LINK pb)
‐ If connected :
‐ The aircraft is properly bonded to the tanker
‐ The tanker and the aircraft grounding requirement is based on local regulations. Always connect
the ground cable to the parking ground point (or to the tanker) before connecting it to the aircraft
‐ The external lighting is not operated (except for NAV & LOGO).
In the cockpit, check that the PARK BRK is ON and that the ACCU PRESS has sufficient pressure. If
the PARK BRK cannot be set to ON, check that the chocks are in place.
ACCESS PLATFORM.......................................................................................................IN POSITION
On cockpit overhead FUEL panel:
PUMPS (of the tanks not to be defueled)................................................................................ OFF
MODE SEL pb-sw ...................................................................................................................MAN
PUMPS (of the tank to be defueled).......................................................................................... ON
if left wing and/or center tanks is (are) to be defueled :
X FEED.................................................................................................................................ON
OPEN light comes on.
On refueling control panel :
REFUEL VALVES sel (of tanks not to be filled).................................................................... SHUT
REFUEL VALVES sel (of tanks to be filled)..........................................................................OPEN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-NOR-SUP-FUEL P 4/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - FUEL
MODE SELECT sw .................................................................................................. DEFUEL/XFR
OPEN light comes on.
FUEL QTY....................................................................................................................... MONITOR
When the tank contents reach the required level :
Corresponding REFUEL VALVES sel............................................................................. SHUT
MODE SELECT sw .................................................................................OFF and GUARDED
OPEN light goes out.
REFUEL VALVES sel...........................................................................NORM and GUARDED
Set cockpit FUEL panel to normal configuration.
DEFUELING
Ident.: PRO-NOR-SUP-FUEL-00021259.0001001 / 25 JUL 17
Applicable to: ALL
WARNING
1. Prior initiation of any ground fuel operations, obey the below fuel safety
precautions. This will prevent injury to people and/or damage to the aircraft.
2. Do not request or perform any ground fuel operations if a fire or engine overheat
warning is displayed.
3. If the APU fails during any ground fuel operations, do not restart the APU. For
APU use during refueling/defueling Refer to LIM-APU APU Start/Shutdown during
Refueling/Defueling.
4. Do not defuel in bad weather conditions and electrical storms.
5. Defueling by suction is not possible
SAFETY PRECAUTIONS............................................................................................................APPLY
During defueling operations, ensure that:
‐ HF transmission (including HF transmission via the HF DATA LINK pb) is not performed
‐ The aircraft is properly bonded to the tanker
‐ The tanker and the aircraft grounding requirement is based on local regulations. Always connect
the ground cable to the parking ground point (or to the tanker) before connecting it to the aircraft
‐ The external lighting is not operated (except for NAV & LOGO).
In the cockpit, check that the PARK BRK is ON and that the ACCU PRESS has sufficient pressure. If
the PARK BRK cannot be set to ON, check that the chocks are in place.
ACCESS PLATFORM.......................................................................................................IN POSITION
MAX DEFUELING PRESSURE: 11 PSI (0.75 bar)
On cockpit overhead FUEL panel:
PUMPS...................................................................................................................................... OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
PRO-NOR-SUP-FUEL P 5/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - FUEL
On refueling control panel:
REFUEL VALVES sel........................................................................................................... NORM
MODE SELECT sw .................................................................................................. DEFUEL/XFR
OPEN light comes on
On cockpit overhead FUEL panel :
MODE SEL pb-sw ...................................................................................................................MAN
PUMPS (of the tank(s) to be defueled)......................................................................................ON
X FEED....................................................................................................................................... ON
OPEN light comes on
FUEL QTY....................................................................................................................... MONITOR
When tank contents reach required level
Corresponding PUMPS...................................................................................................... OFF
On refueling control panel:
MODE SELECT sw ....................................................................................... OFF and GUARDED
OPEN light goes out
REFUEL VALVES sel................................................................................. NORM and GUARDED
Set cockpit FUEL panel to normal configuration.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PRO-NOR-SUP-FUEL P 6/6
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - L/G
FLIGHT CREW
OPERATING MANUAL
Flight with Landing Gear Down
GENERAL
Ident.: PRO-NOR-SUP-LG-LG_DN-00001997.0001001 / 04 SEP 17
Applicable to: ALL
It is possible to perform a flight with the landing gear locked down and the doors closed.
This chapter applies to either of the following two situations:
‐ The dispatch of an aircraft with the landing gear down, or
‐ The continuation of the flight when a landing gear retraction failure happens after takeoff.
The limitations, procedures and performance associated to a flight with the landing gear down are
described below.
LIMITATIONS
Ident.: PRO-NOR-SUP-LG-LG_DN-00001999.0002001 / 04 SEP 17
Applicable to: ALL
For a flight with the landing gear down, all of the following supplementary limitations apply:
‐ Consider a VMO /MMO of 235 kt/M 0.60
‐ Landing gear doors must be closed
‐ Avoid icing conditions
‐ Do not use managed speeds, except during the approach
‐ Do not use CLB and DES autopilot modes
‐ Disregard FMS fuel, altitude, speed, and time prediction. Time prediction is valid on waypoints in
cruise only
‐ Use the TCAS in TA ONLY mode
‐ The ALTITUDE ALERT feature is not available
‐ Do not perform ETOPS flight.
Note:
Ditching with the landing gear down is not assessed.
PROCEDURES
Applicable to: ALL
Ident.: PRO-NOR-SUP-LG-LG_DN-B-00002000.0002001 / 04 SEP 17
PREFLIGHT
In addition to the SOPs apply the following:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C →
PRO-NOR-SUP-LG-LG_DN P 1/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L2
L1
SUPPLEMENTARY PROCEDURES - L/G
VMO/MMO setting:
VMO-MMO sw............................................................................................................L/G DOWN
The switch is located in the avionics compartment (on the 188VU panel). This switch changes
the VMO/MMO to 235 kt/M 0.60. As a result, an alert is triggered if the speed exceeds the
flight with gear down speed limitation.
CAUTION
In the case of continuation of the flight after a gear retraction failure, the flight
crew can not access the VMO/MMO switch. Therefore, the airspeed/Mach
number must be carefully monitored in order not to exceed 235 kt/M 0.60 as
there is no alert if the aircraft exceeds this limitation.
Ident.: PRO-NOR-SUP-LG-LG_DN-B-00002003.0012001 / 04 SEP 17
FLIGHT CONTROLS
Failure cases, which would normally lead to ALTN law, will degrade F/CTL laws down to DIRECT
law, if the landing gear is extended.
FAILURE OF BOTH ENGINES
When both engines are failed, to ease the handling of all the different ECAM procedures resulting
from this all engine flame out situation, it is recommended to use the ENG DUAL FAILURE QRH
procedure, and if time permits, to clear the ECAM.
Follow all the steps of the QRH procedure, except those that are modified by the procedure
below :
If APU is not available
‐ Attempt an APU start
‐ . If APU start is unsuccessful, a windmilling relight can be performed, as long as the speed
is above 300 kt (corresponding N2 above 12 %). In this case, increase the aircraft speed
and disregard VMO warning.
If APU is available : perform an assisted relight, when below FL 200.
‐ Flight controls are in direct laws. Use manual pitch trim as necessary (not indicated on PFD
if APU GEN not available).
TAKEOFF
Applicable to: ALL
Ident.: PRO-NOR-SUP-LG-LG_DN-C-00021928.0006001 / 04 SEP 17
GENERAL
The recommended takeoff configuration is 1 + F, as this provides the best climb gradient.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
PRO-NOR-SUP-LG-LG_DN P 2/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - L/G
It is not recommended to takeoff with tailwind.
To take into account the most limiting aspects of the takeoff, the second segment condition and
the final segment condition are considered.
Once the takeoff weight determined, read the corresponding speeds in the RTOW chart.
Ident.: PRO-NOR-SUP-LG-LG_DN-C-00002006.0017001 / 04 SEP 17
SECOND SEGMENT CONDITIONS
The MTOW for a flight with gear down can be determined with use of the basic RTOW chart
published for a normal flight.
To simplify calculations, a weight reduction percentage is applied for each configuration,
regardless of the limitation. This weight reduction takes into account the most critical case which is
obstacle clearance.
Takeoff configuration
Weight reduction
1+F
22 %
2
19 %
3
19 %
MTOW DETERMINATION
Enter the basic RTOW chart with the runway conditions (temperature, pressure, etc.) desired
aircraft configuration, and obtain the basic MTOW.
Obtain the weight reduction percentage corresponding to the desired takeoff configuration from
the above table.
Reduce the previous basic MTOW by this percentage to obtain the MTOW, limited by the
second segment condition.
Ident.: PRO-NOR-SUP-LG-LG_DN-C-00002007.0405001 / 04 SEP 17
FINAL SEGMENT CONDITIONS - LANDING GEAR DOWN - ONE ENGINE INOP
MAX. CLIMB THRUST
SPEED VLS
AIR CONDITIONING ON
ANTI ICING OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
CG 25 %
←D→
GROSS GRADIENT 1.2 %
PRO-NOR-SUP-LG-LG_DN P 3/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - L/G
MTOW DETERMINATION
Enter the chart with the airport’s OAT . Move up to the position corresponding to the airport’s
pressure altitude. Then, move right and obtain the MTOW limited by the final segment condition.
In the case of CG forward of 25 %, decrease the obtained weight by 400 kg (900 lb).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PRO-NOR-SUP-LG-LG_DN P 4/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - L/G
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING
Ident.: PRO-NOR-SUP-LG-LG_DN-00002011.0001001 / 04 SEP 17
Applicable to: ALL
GENERAL
Flying with the gear down induces additional drag and therefore deteriorates aircraft performance.
This drag affects all phases of the flight where the landing gear is normally retracted.
MAXIMUM TAKEOFF WEIGHT DETERMINATION
The MTOW for the flight with gear down is determined by keeping the lowest of the weights given
by:
‐ The second segment condition
‐ The final segment condition
‐ The en-route conditions
‐ The go-around conditions.
To determine the MTOW for a flight with the gear down, perform all following steps:
1. Determine the MTOW limited by the second segment condition (Refer to
PRO-NOR-SUP-LG-LG_DN Second Segment Conditions).
2. Determine the MTOW limited by the final segment condition (Refer to
PRO-NOR-SUP-LG-LG_DN Final Segment Conditions).
3. Keep the lowest of the above weights as the MTOW.
4. With the MTOW determined in step 3, check the obstacle clearance along the planned route
(en-route).
To determine the One Engine Inoperative (OEI) obstacle clearance:
‐ Refer to PRO-NOR-SUP-LG-LG_DN Driftdown Net Flight Path - One Engine Inoperative
‐ Refer to PRO-NOR-SUP-LG-LG_DN Gross Ceilings - One Engine Inoperative.
If necessary, reduce the takeoff weight, in order to obtain the appropriate obstacle clearance.
5. Determine the go-around limiting weight (Refer to PRO-NOR-SUP-LG-LG_DN Go-Around). If
necessary, reduce the MTOW to comply with this requirement.
6. Keep the lowest MTOW from steps 3, 4, and 5.
FLIGHT PLAN
The flight planning can be performed with the use of the tables provided in this procedure, or with
a planning software (PEP, FlySmart, etc.).
FUEL BURN CORRECTION
The climb, cruise, and descent tables are determined for ISA conditions. For each degree Celsius
above ISA and per nautical mile of air distance, add a fuel burn correction of 0.05 kg/°C/NM air
distance (0.11 lb/°C/NM air distance).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
PRO-NOR-SUP-LG-LG_DN P 5/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - L/G
CLIMB
Climb at 230 kt/M 0.50 with the use of maximum climb thrust.
Refer to PRO-NOR-SUP-LG-LG_DN Climb.
CRUISE
The recommended cruise speed is 230 kt/M 0.50.
Refer to PRO-NOR-SUP-LG-LG_DN Cruise.
HOLDING
The holding configuration is CONF 1.
Refer to PRO-NOR-SUP-LG-LG_DN Holding.
DESCENT
The recommended descent speed is 230 kt/M 0.50.
Refer to PRO-NOR-SUP-LG-LG_DN Descent.
GO-AROUND
Refer to PRO-NOR-SUP-LG-LG_DN Go-Around.
LANDING
The landing is standard.
ENGINE FAILURE
In case of engine failure, select maximum continuous thrust (MCT) on the remaining engine and
adopt the specified driftdown speed.
For obstacle clearance and depending on the chosen strategy:
‐ Refer to PRO-NOR-SUP-LG-LG_DN Driftdown Net Flight Path - One Engine Inoperative
‐ Refer to PRO-NOR-SUP-LG-LG_DN Gross Ceilings - One Engine Inoperative.
Note:
The OEI required obstacle clearances are 1 000 ft in climb or level flight, and 2 000 ft in
descent.
For fuel burn calculations with one engine inoperative and landing gear down, use the standard
OEI cruise fuel flow and apply the fuel penalty as per QRH/OPERATIONAL DATA/FUEL
PENALTY FACTORS.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-NOR-SUP-LG-LG_DN P 6/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - L/G
CLIMB
Ident.: PRO-NOR-SUP-LG-LG_DN-00002012.0009001 / 14 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-NOR-SUP-LG-LG_DN P 7/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - L/G
CRUISE
Ident.: PRO-NOR-SUP-LG-LG_DN-00002014.0009001 / 14 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
PRO-NOR-SUP-LG-LG_DN P 8/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - L/G
HOLDING
Ident.: PRO-NOR-SUP-LG-LG_DN-00002017.0009001 / 04 SEP 17
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
H
PRO-NOR-SUP-LG-LG_DN P 9/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - L/G
DESCENT
Ident.: PRO-NOR-SUP-LG-LG_DN-00002016.0021001 / 14 FEB 11
Applicable to: ALL
GO-AROUND
Ident.: PRO-NOR-SUP-LG-LG_DN-00002010.0001001 / 04 SEP 17
Applicable to: ALL
Refer to PER-GOA-GEN GENERAL for go-around requirements.
Further decrease the basic limiting weight by 15 %.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
I to J
PRO-NOR-SUP-LG-LG_DN P 10/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - L/G
FLIGHT CREW
OPERATING MANUAL
ONE ENGINE INOPERATIVE
Applicable to: ALL
Ident.: PRO-NOR-SUP-LG-LG_DN-D-00002019.0013001 / 04 SEP 17
EN ROUTE NET FLIGHT PATH - L/G DOWN - ONE ENGINE INOP
MAX. CONTINUOUS THRUST
GREEN DOT SPEED
HIGH AIR CONDITIONING
ANTI ICE OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
ISA
CG = 23 %
K→
MINIMUM ENGINE
PRO-NOR-SUP-LG-LG_DN P 11/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
SUPPLEMENTARY PROCEDURES - L/G
←K→
PRO-NOR-SUP-LG-LG_DN P 12/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - L/G
FLIGHT CREW
OPERATING MANUAL
Ident.: PRO-NOR-SUP-LG-LG_DN-D-00004080.0005001 / 04 SEP 17
BLEED CORRECTIONS
LONG RANGE
GREEN DOT
ENGINE ANTI ICE ON
TOTAL ANTI ICE ON
ENGINE ANTI ICE ON
TOTAL ANTI ICE ON
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←K
ISA
-500 ft
-1 300 ft
-200 ft
-1 200 ft
≥ ISA +10
-2 800 ft
-4 600 ft
-1 700 ft
-3 500 ft
PRO-NOR-SUP-LG-LG_DN P 13/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - L/G
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SUP-LG-LG_DN P 14/14
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - L/G
FLIGHT CREW
OPERATING MANUAL
Operation with Nosewheel Steering Offset
OPERATION WITH NOSEWHEEL STEERING OFFSET
Applicable to: ALL
Ident.: PRO-NOR-SUP-LG-LG-A-00020945.0001001 / 17 MAR 17
During taxi in a straight line, the crew may notice aircraft veering tendency. This can be due to
external conditions (crosswind, slope....), or to a nosewheel steering offset.
A nosewheel steering offset is usually notified through consecutive crew reports. The NWS offset
value is determined regarding the necessary rudder trim input used to cancel the veering tendency.
Ident.: PRO-NOR-SUP-LG-LG-A-00020946.0001001 / 17 MAR 17
When the NWS offset is within admissible limits, the flight crew can operate the aircraft as follows:
CAUTION
A rudder trim reset must be performed before takeoff.
When the rudder trim adjustment is above the maintenance tolerance (±0.5 ° NWS
offset corresponding to ±3 ° rudder trim necessary to taxi straight), the flight crew
must systematically and accurately report the rudder trim value in the logbook.
NWS Offset
Offset ≤ 0.5 °
Necessary
Rudder Trim Input
Trim ≤ 3 °
Procedure
Taxi:
RUDDER TRIM.....................................................ADJUST
Adjust trim until the aircraft taxies in a straight line. Check
input value.
Before takeoff:
RUDDER TRIM......................................................RESET
Taxi:
RUDDER TRIM.....................................................ADJUST
Adjust trim until the aircraft taxies in a straight line. Check
input value.
0.5 ° < Offset ≤ 1.5 °
3 ° < Trim ≤ 8.8 °
Before takeoff:
RUDDER TRIM......................................................RESET
Landing:
Offset > 1.5 °
Trim > 8.8 °
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
For autoland:
MAX CROSSWIND............................................10 kt
MAINTENANCE ACTION............................................REQUEST
Do not attempt takeoff. Request for troubleshooting.
A
PRO-NOR-SUP-LG-LG P 1/2
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - L/G
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SUP-LG-LG P 2/2
05 SEP 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
Pushback with Power Push Unit
PUSHBACK WITH POWER PUSH UNIT VIA THE MAIN LANDING GEAR
Applicable to: ALL
Ident.: PRO-NOR-SUP-MISC-D-A-00020472.0002001 / 17 MAR 17
When pushback is performed with a Power Push Unit (PPU) via the main landing gear, this
procedure replaces the BEFORE PUSHBACK OR START SOP.
Before start clearance
SOP - BEFORE START CLEARANCE..........................................................................PERFORM
L2
Refer to PRO-NOR-SOP-07 Before Start Clearance.
L1
BEFORE START CHECKLIST down to the line.......................................................... COMPLETE
NW STRG DISC MEMO........................................................................CHECK NOT DISPLAYED
L2
The ground crew should check that the towing lever is in the normal position.
L1
At start clearance
PUSHBACK/START CLEARANCE.....................................................................................OBTAIN
L2
Obtain ATC pushback/start clearance.
Obtain ground crew clearance.
L1
ATC............................................................................................................ SET FOR OPERATION
L2
ATC is set in accordance with airport requirements.
L1
WINDOWS AND DOORS....................................................................................CHECK CLOSED
L2
- To ensure that the sliding window is correctly closed, push the handle of the sliding window fully
forward to the closed position, and check that the red indicator is visible.
- Check, on the ECAM lower display, that all the aircraft doors are closed.
- When required by local airworthiness authorities, check that the cockpit door is closed and
locked (no cockpit door open/fault indication).
If entry is requested, identify the person requesting entry before unlocking the door. With the
cockpit door sw on NORM, the cockpit door is closed and locked. If entry is requested from the
cabin, and if no further action is performed by the pilot, the cabin crew will be able to unlock the
door by using the emergency access procedure. Except for crew entry/exit, the cockpit door
should remain closed until engine shutdown.
L1
SLIDES.................................................................................................................. CHECK ARMED
L2
- Check, on the ECAM lower display, that all slides are armed.
L1
BEACON sw................................................................................................................................ON
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SUP-MISC-D P 1/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
THRUST LEVERS....................................................................................................................IDLE
CAUTION
L2
L1
L2
L1
Engines will start, regardless of the thrust lever position; thrust will rapidly
increase to the corresponding thrust lever position, causing a hazardous
situation, if thrust levers are not at IDLE.
ACCU PRESS indicator.......................................................................................................CHECK
The ACCU PRESS indication must be in the green band. If required, use the electric pump on
yellow hydraulic system to recharge the brake accumulator.
PARK BRK handle........................................................................................................ CHECK ON
BRAKES PRESS indicator.................................................................................................. CHECK
Check for normal indication.
BEFORE START CHECKLIST below the line............................................................. COMPLETE
Ident.: PRO-NOR-SUP-MISC-D-A-00020473.0002001 / 17 MAR 17
L2
ENG 2......................................................................................................................................... START
Engine 2 is usually started first to pressurize the yellow hydraulic system, making the nosewheel
steering and parking brake available.
Ident.: PRO-NOR-SUP-MISC-D-A-00020474.0001001 / 17 MAR 17
PUSHBACK
L2
L1
L2
L1
L2
L1
Due to a face-to-face situation between the ground personnel and the flight crew, a clear
understanding of directional phraseology is essential.
PARK BRK handle.......................................................................................................................OFF
BRAKES PRESS indicator..........................................................................................CHECK ZERO
A slight residual pressure may remain for a short period of time on the triple indicator. Advise the
ground crew that the parking brake is off and that the pushback can be started.
CAUTION
Do not use the brakes during pushback, except in case of emergency.
Do not move flight controls or flap lever.
In case of emergency, order the ground crew to separate the PPU and move it away from the
evacuation areas. Nevertheless, evacuation is possible with the PPU in place.
STEERING HANDWHEEL.........................................................................................AS REQUIRED
Steer the aircraft using guidance from the ground crew.
When pushback is completed:
PARK BRK handle..................................................................................................................ON
BRAKES PRESS indicator.............................................................................................. CHECK
GROUND CREW.......................................................................... ADVISED TO REMOVE PPU
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SUP-MISC-D P 2/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
When PPU is removed and ground crew clearance obtained:
ENG 1............................................................................................................................... START
SOP - AFTER START.................................................................................................. RESUME
Refer to PRO-NOR-SOP-09 After Start
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SUP-MISC-D P 3/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SUP-MISC-D P 4/4
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
FLIGHT CREW
OPERATING MANUAL
Hight Altitude Airport Operations
HIGH ALTITUDE AIRPORT OPERATIONS
Applicable to: ALL
Ident.: PRO-NOR-SUP-MISC-A-A-00020650.0017001 / 20 MAR 17
TAKEOFF ON AIRPORT WITH AN ELEVATION OF 9 200 FT OR ABOVE
COCKPIT PREPARATION
HIGH ALT LDG pb-sw (for all on ground operation).................................................................ON
BEFORE PUSHBACK OR START
L2
L1
ACCU PRESS.................................................................................................................... CHECK
If required, use the HYD YELLOW ELEC PUMP to recharge the brake accumulator.
GEN 1...................................................................................................................................... OFF
GEN 2...................................................................................................................................... OFF
G ENG PUMP..........................................................................................................................OFF
Y ENG PUMP.......................................................................................................................... OFF
ENGINE START
When idle is reached
GEN 1................................................................................................................................. ON
GEN 2................................................................................................................................. ON
G ENG PUMP.....................................................................................................................ON
Y ENG PUMP..................................................................................................................... ON
TAKEOFF
Note:
L2
L1
For A/C operating under FAA requirements, as long as the cabin altitude is above
12 000 ft in flight, at least one pilot must use the oxygen mask continuously.
APU BLEED................................................................................................................... AS RQRD
Packs may be supplied for takeoff by the engine bleed, or by the APU bleed up to 17 000 ft
depending on the takeoff performance requirement.
CRUISE
LDG ELEV AUTO [CRUISE page].....................................................................................CHECK
When cabin altitude below 12 000 ft and decreasing:
HIGH ALT LDG pb-sw...................................................................................................... OFF
CHECK THAT CABIN ALTITUDE DECREASES BELOW 9 550 ft +/- 350 ft
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SUP-MISC-A P 1/2
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L2
L1
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
This will allow the CAB PR EXCESS CAB ALT alert to trigger again if necessary despite the
clear action.
LANDING ON AIRPORTS WITH AN ELEVATION OF 9 200 FT OR ABOVE
CRUISE
If CAB ALT exceeds 8 000 ft:
LDG ELEV: 8 000 ft:......................................................................................................... SET
L2
L1
Manually selecting a landing field elevation overrides the FMGS landing field elevation for the
remaining time of cruise.
Note:
A step descent or turbulence conditions may trigger an early CPC descent mode
detection, leading the CPC to start controlling to the landing field elevation pressure.
DESCENT PREPARATION
Note:
L2
L1
L2
L1
For A/C operating under FAA requirements, at least one pilot must use the oxygen
mask continuously until landing.
HIGH ALT LDG pb-sw...............................................................................................................ON
Passengers oxygen masks would drop when cabin altitude is above 14 000 ft +250/-750 ft if
HIGH ALT LDG pushbutton switch is OFF.
Note:
Passengers oxygen masks drop above 16 000 ft +250/-750 ft cabin altitude if HIGH
ALT LDG pushbutton switch is ON.
LDG ELEV.............................................................................................................................AUTO
CPC starts controlling the pressure to the landing field elevation at beginning of descent.
AFTER LANDING
HIGH ALT LDG pb-sw (for all on ground operation).................................................................ON
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SUP-MISC-A P 2/2
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
Operations at QNH Above 1050 hPa
GENERAL
Ident.: PRO-NOR-SUP-MISC-C-00002100.0015001 / 03 FEB 11
Applicable to: ALL
Some airlines may occasionally experience high barometric correction settings above 1 050 hPa,
or 31.0 inHg on some airfields, due to polar anticyclonic air mass conditions occuring near the polar
area during winter.
The FMS , FCU , ISIS instrument, PFD , and CPCS are capable of operating at QNH /QFE up to
1 100 hPa, or 32.48 inHg.
However, the ATC/TCAS operates only up to 1050 hPa (i.e. as long as the aircraft altitude remains
above –1000 feet standard pressure altitude).
Therefore, when using QNH , or QFE for QFE pin-programmed aircraft, for departure and arrival, the
crew should be aware of the following consequences, and should apply the following procedures.
It is necessary for the airline to obtain operational approval from its national airworthiness authorities.
CONSEQUENCES
Ident.: PRO-NOR-SUP-MISC-C-00002102.0038001 / 17 MAR 11
Applicable to: ALL
ON THE ATC-TCAS:
For takeoff, approach and landing, the ATC altitude reporting and the TCAS TA/RA function may
generate erroneous altitude information and nuisance TCAS alerts for other aircraft, if the aircraft
standard altitude is below -1 000 ft standard pressure altitude.
To avoid this, it is recommended to set ALT RPTG to OFF when the QNH exceeds 1 050 hPa, and
to inform the ATC . As a consequence the TCAS reverts to STBY mode.
PROCEDURES
Ident.: PRO-NOR-SUP-MISC-C-00002104.0015001 / 20 MAR 17
Applicable to: ALL
BEFORE TAKEOFF
L2
L1
L2
ALT RPTG ..................................................................................................................................OFF
ALT RPTG OFF memo and TCAS STBY memo appear on the WD.
ATC........................................................................................................................................ NOTIFY
Notify the ATC that the altitude reporting is not available.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C →
PRO-NOR-SUP-MISC-C P 1/2
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L1
L2
L1
L2
L1
SUPPLEMENTARY PROCEDURES - MISCELLANEOUS
TAKEOFF
Above 1 000 ft, when time permits:
ALT RPTG ............................................................................................................................. ON
As a result, the TCAS automatically reverts to its previous setting.
APPROACH
Before final approach:
ATC..................................................................................................................................NOTIFY
Notify the ATC that the altitude reporting will be turned off.
ALT RPTG ........................................................................................................................... OFF
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PRO-NOR-SUP-MISC-C P 2/2
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - NAVIGATION
INSERTION OF APPROACH MINIMA
Applicable to: ALL
Ident.: PRO-NOR-SUP-NAV-A-00015220.0011001 / 21 MAR 17
QNH USE FOR AIRCRAFT NOT EQUIPPED WITH QFE OPTION
This table explains how the flight crew must insert the approach minimum on the MCDU PERF
APPR page.
Guidance Modes
LOC G/S
CAT II & CAT III
approaches
BARO field
MCDU PERF
APPR page
RADIO field
FMA display
LOC G/S
CAT I approaches
--DH or RA
“RADIO XXX”
DA
FINAL APP
DA or MDA
--“BARO XXXX”
NAV FPA
LOC FPA
LOC B/C FPA
TRK FPA
MDA
Ident.: PRO-NOR-SUP-NAV-A-00015222.0001001 / 21 MAR 17
QFE USE FOR AIRCRAFT NOT EQUIPPED WITH QFE OPTION
The crew should not use QFE on aircraft with a “QNH only” pin programming (incorrect profile
computation of the managed vertical modes CLB , DES and FINAL APPR, possible false GPWS
warnings in mountainous areas).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-NOR-SUP-NAV P 1/2
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SUPPLEMENTARY PROCEDURES - NAVIGATION
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SUP-NAV P 2/2
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Introduction
INTRODUCTION
Ident.: PRO-NOR-SRP-01-05-00003959.0001001 / 09 OCT 12
Applicable to: ALL
Note:
This chapter is an amplification of the SOP. Anytime it was feasible, the same chapters and
the same titles of paragraph were retained.
The following discussion of the FMGS uses this flight plan as an example.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SRP-01-05 P 1/2
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
SYSTEMS RELATED PROCEDURES - FMS
←A
PRO-NOR-SRP-01-05 P 2/2
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Cockpit Preparation
FMGS INITIALIZATION
Ident.: PRO-NOR-SRP-01-10-00003960.0002001 / 22 MAY 12
Applicable to: ALL
CHECKING THE CLOCK DATE
CHECK the CLOCK DATE and ADJUST, if necessary.
If the date in the active database does not match the clock date, the MCDU displays “CHECK
DATA BASE CYCLE”. If this message appears, check the period of validity in the second
database and select it, if required.
CAUTION
Cycling the navigation database deletes the active and secondary flight plans. Do
not cycle it while airborne because doing so will delete the flight plan, eliminate all
speed predictions, and blank the ND. If the aircraft is in managed speed, Green
Dot becomes the speed target.
CHECKING STORED WAYPOINTS, NAVAIDS, RUNWAYS, OR ROUTES
PRESS the DATA key.
PRESS the next page key.
SELECT, successively, as required:
‐ STORED WAYPOINT
‐ STORED NAVAIDS
‐ STORED RUNWAYS
‐ STORED ROUTES
CHECK the contents of each of these data storages and DELETE items, as appropriate.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SRP-01-10 P 1/28
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
NAVAIDS DESELECTION
If NOTAMS indicate that selected NAVAIDs are unreliable or unserviceable, deselect
them as follows:
PRESS the DATA key.
SELECT the POSITION MONITOR page.
SELECT the SELECTED NAVAIDS page.
Under “DESELECT”, INSERT the NAVAID identifier in the brackets.
The pilot can only make six deselections.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SRP-01-10 P 2/28
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT PLAN INITIALIZATION
Applicable to: ALL
Ident.: PRO-NOR-SRP-01-10-A-00003961.0025001 / 22 MAY 12
GENERAL
Follow SOP instructions, when the route is a company route stored in the database.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
PRO-NOR-SRP-01-10 P 3/28
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
If the company route is unknown, proceed as follows:
WRITE a “FROM/TO” city pair, then ENTER it:
If one or more company routes run between the cities, the ROUTE SELECTION page appears
and defines them.
INSERT the preferred company route.
If the database does not contain a company route:
The flight plan must be constructed manually:
PRESS the INIT key
ENTER a city pair in the FROM/TO field.
The ROUTE SELECTION page comes up with “NONE”
SELECT RETURN [6L] key then construct the flight plan manually.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-10 P 4/28
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
If waypoints, NAVAIDs or airports are not in the NAV database, the crew must define and
store them manually, using the “data stored” function.
Ident.: PRO-NOR-SRP-01-10-A-00003962.0046001 / 23 JUN 15
ALIGNING IRS
The alignment phase is completed, when the ADIRS is initialized to an appropriate position. If the
GPS is available, initialization is automatic, using the GPS position. Flight crew intervention is not
necessary.
However, automatic initialization may be manually overriden by flight crew entry, at any moment
during the alignment phase. In this case, perform the following procedure as soon as possible, to
prevent delays if an alignment error occurs:
PRESS the INIT key, and then the IRS INIT prompt.
IRS INIT page is displayed with the airport reference point as default coordinates.
If necessary, PRESS [1L] and/or [1R] and use scroll keys to adjust the latitude and/or longitude
values.
For example, this can be used to enter the gate precise coordinates when the aircraft is intended
to fly without GPS on long segments without radio coverage.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-10 P 5/28
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
PRESS the ALIGN ON REF prompt and CONFIRM ALIGN* prompt.
The displayed coordinates are sent to ADIRS for initialization.
The alignment status changes to ALIGNING ON REF.
If the “CHECK IRS/AIRPORT POS” or "REF/GPS POS DIF" or "REF/LAST IRS POS DIF"
message is displayed:
CHECK the departure airport on INIT A page and CORRECT it if necessary.
REALIGN the IRS per the procedure described previously.
If a new FROM or a new CO RTE is entered after IRS alignment is already completed,
the ALIGN ON REF prompt is displayed in [6R]:
REALIGN the IRS per the procedure described previously.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-10 P 6/28
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Ident.: PRO-NOR-SRP-01-10-A-00003963.0010001 / 22 MAY 12
LATERAL FLIGHT PLAN
SELECTING A DEPARTURE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-10 P 7/28
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
You may use the ”NEXT PAGE” , or the “←” or “→” keys to gain access to the listings of
runways, SIDs, and transitions.
Procedure
PRESS the F-PLN key on MCDU
SELECT the DEPARTURE prompt [1L] key
SELECT the RWY in USE, SID and TRANS
CHECK the resulting temporary F-PLN
If it is correct, INSERT it using [6R] key.
If it is not correct, ERASE it using [6L] key.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-10 P 8/28
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Ident.: PRO-NOR-SRP-01-10-A-00003964.0004001 / 22 MAY 12
VERTICAL FLIGHT PLAN
ENTERING/MODIFYING A SPEED LIMIT
PRESS the F-PLN key on the MCDU.
SELECT VERTICAL REVISION at the FROM waypoint.
WRITE a new speed limit/altitude and ENTER.
The crew can insert one climb speed limit and one descent speed limit into the vertical flight
plan, or modify or clear the limits that are already in it.
The speed limit is defined by a speed and an altitude (for example, 230/9 000), which means
that the managed speed target will be limited by the speed limit when the aircraft flies below the
specified altitude.
In both climb and descent, 250 kt at 10 000 ft is the default speed limit in the vertical flight plan.
The vertical revision page presents the climb speed (CLB SPD) limit if the revised waypoint is
between departure and top of descent.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-10 P 9/28
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
The vertical revision page shows the descent speed (DES SPD) limit, if the revised waypoint is
between top of descent and destination.
It can be deleted by a clear action, the field reverts to brackets. It can also be cleared directly on
the F-PLN A page by clearing the SPD LIM pseudo-waypoint.
ENTERING A SPEED CONSTRAINT
Procedure
PRESS the F-PLN key on the MCDU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-10 P 10/28
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
SELECT the VERT REV page at the revised waypoint.
WRITE the speed constraint value into the scratchpad and ENTER it in 3L.
INSERT the constraint using the appropriate *CLB or DES * prompt when displayed. If CLB
and DES are not displayed, insertion occurs when the value is entered in 3L.
The system displays the climb (CLB ) or the descent (DES) prompt at [6L] or [6R] when the
predictions are not yet available or when the waypoint is part of the cruise phase as originally
defined.
When predictions are not yet available, the constraints are displayed on the F-PLN A page in
magenta.
When predictions are available, the speed constraint is highlighted by a star (*).
* If the predicted speed matches the constraint, the star is magenta.
* If the prediction is that the aircraft will miss the speed constraint, the star is amber.
If a speed constraint cannot be met (by more than 10 kt), the FMGS generates the
message “SPD ERROR AT WPT XX”.
A speed constraint may be assigned to any waypoint in the climb or the descent phase
except the FROM, origin, or destination waypoints, and any pseudo waypoint.
When a speed constraint is assigned to a waypoint, the constraint will limit the managed
speed target as follows:
‐ In takeoff or climb phase until you pass the constrained waypoint.
‐ In descent an approach phase, after passing the constrained waypoint.
Speed constraints are observed by the FMGS when NAV mode and speed managed are
active.
ENTERING A SPEED CONSTRAINT THROUGH F-PLN A PAGE
You may also enter a speed constraint through the F-PLN A page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-NOR-SRP-01-10 P 11/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
SYSTEMS RELATED PROCEDURES - FMS
You may delete the constraint using the clear key on the relevant right hand key.
However if there is an altitude constraint assigned at that point, the clear action deletes
it too.
ENTERING AN ALTITUDE CONSTRAINT
Procedure
PRESS the F-PLN key on the MCDU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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PRO-NOR-SRP-01-10 P 12/28
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PROCEDURES
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
SELECT the “VERT REV” page at the revised waypoint.
WRITE an altitude constraint in the scratchpad and ENTER it in 3R.
INSERT the constraint using *CLB or DES* prompt when it is displayed. Otherwise the value
is inserted when it is entered in 3R field.
The system displays the *CLB or DES* prompt, when the predictions are not yet available, or
when the waypoint is part of the cruise phase as originally defined.
Note:
In case of QFE operations, the altitude constraints must be converted and entered
as an altitude in feet.
You or the database may assign an altitude constraint to any waypoint in the climb or descent
phases except the FROM, origin, or destination waypoints, or any pseudo waypoint.
An altitude constraint may be defined as an “at”, an “at or above”, or an “at or below”
constraint. In certain procedures, the database may define an altitude constraint as a window
in which the aircraft should fly.
Enter “AT” constraints with no sign.
Enter “AT or ABOVE” constraints preceded by a + sign (+FL 130, for example).
Enter “AT or BELOW” constraints preceded by a – sign (-15 000, for example).
enter four or five-digit number when entering altitude. Include the lead zero (0 500 ft , for
example).
For flight level, enter a two- or three-digit number, with or without the letters “FL”. The lead
zero is optional. (Examples : +FL 120 or +120 ; -FL 090 or -90 or -090)
Enter the altitude value as either altitude or flight level ; the MCDU displays the selected value
as an “ALT ” or “FL,” as appropriate for the transition altitude.
The constraint must be higher than the thrust reduction altitude and lower than the cruise
flight level.
Once inserted in the flight plan, the altitude constraint (ALT CSTR) is displayed in magenta as
long as predictions are not available.
When predictions are available, the altitude constraints are replaced by the predicted altitude
at relevant waypoints highlighted by a star.
* If the predicted altitude matches the constraint the star is magenta. If the predicted altitude
is missed (by more than 250 ft), the star is amber.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
The vertical revision page displays “ALT ERROR”, along with the difference between the
constraint and the predicted altitude at the revised waypoint.
ND Display
An altitude-constrained waypoint is marked by a circle ( ) on the navigation display.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PROCEDURES
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
This circle is white when the guidance does not take the altitude constraint into account. It is
magenta if the guidance system takes the altitude constraint into account and predicts that it
will be matched.
It is amber if the guidance system takes the altitude constraint into account and predicts that it
will not be matched.
The aircraft should be at or below FL 120 at AGN and above FL 180 at LACOU.
Entering an Altitude Constraint Through F-PLN A Page
The pilot may also enter an altitude constraint directly through the F-PLN A page.
When entering the value into the scratchpad do not forget the slash e.g. /-120 or /-FL 120.
If the slash is omitted the value will be considered as a speed constraint if it is within the
range value.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-10 P 15/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Use CLR to delete them directly from the flight plan page, as well. However, if there is also a
speed constraint assigned at that waypoint, the clear action deletes it too.
ENTERING AN ESTIMATED TIME OF TAKEOFF (ETT)
In Preflight Phase:
SELECT the SEC F-PLN key on the MCDU.
SELECT a VERT REV at any waypoint.
SELECT the Required Time of Arrival (RTA) prompt (2R).
The MCDU displays the RTA page.
ENTER the Estimated Takeoff Time in the [ 6R ] field.
The format is HHMMSS (entry of seconds is not mandatory).
ENTER it in the 6R field
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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PRO-NOR-SRP-01-10 P 16/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
If the aircraft has not taken off by the time entered as estimated takeoff time, the MCDU
displays the “CLK IS TAKE OFF TIME” message, meaning that the system will replace your
estimated takeoff time with the actual time.
When beginning the takeoff roll, the system automatically adopts that clock time as the
takeoff time.
If the origin airport is changed, or the clock time is invalid, the system automatically deletes
the estimated takeoff time.
Ident.: PRO-NOR-SRP-01-10-A-00003965.0001001 / 15 FEB 11
FLIGHT PLAN CHECK
CHECK the EOSID on the ND plan mode (yellow line).
Note:
If the details of the EOSID require review, select the EOSID as a TMPY F-PLN and
review it as TMPY. Then ERASE it.
Ident.: PRO-NOR-SRP-01-10-A-00003966.0001001 / 09 DEC 09
SECONDARY F-PLN
For details : Refer to DSC-22_20-60-50 Secondary Flight Plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-10 P 17/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Ident.: PRO-NOR-SRP-01-10-A-00003967.0001001 / 15 FEB 11
RADIO NAV
Whenever a NAVAID IDENT is correctly decoded, in agreement with that published, no audio
check is necessary.
Morse decoding is displayed on the ND for VOR/DME, VOR/TAC, DME , ADF , and on the PFD
for ILS.
Preferably use the identifier for NAVAID entry.
If the ADF IDENT is not in the database, be sure to include a decimal point when tuning the
frequency (e.g 315. or 325.7).
Note:
Whenever, the runway ILS is intented to be retained for guidance after the takeoff phase,
it is recommended to manually tune the ILS by its identifier.
FMGS DATA INSERTION
Applicable to: ALL
Ident.: PRO-NOR-SRP-01-10-B-00003968.0024001 / 05 OCT 16
WEIGHT/CG INSERTION AND FUEL PLANNING
The flight crew must enter the Zero Fuel Weight (ZFW ) and Zero Fuel Weight Center of Gravity
(ZFWCG ) values on the INIT B page, to allow the FMS to perform the fuel planning computations.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-NOR-SRP-01-10 P 18/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
PROCEDURE
PRESS the INIT key, and the Next (“→”) key to access the INIT B page.
ENTER the ZFW and ZFWCG value in the [ 1R ] field.
The “FUEL PLANNING →” prompt appears in the [ 3R ] field.
Note:
As long as the final Load and Trim Sheet is not available, the crew should insert the
estimated ZFW /ZFWCG in order to get fuel estimates. The ZFW and ZFWCG values
must be updated with the final Load and Trim Sheet values.
CHECK/MODIFY the TAXI [ 1L ], RTE RSV [ 3L ] and FINAL TIME [ 5L ] values.
The TAXI, RTE RSV and FINAL TIME fields display the default values specified in the AMI file
(for example, “0.4 t” for TAXI, “5.0 %” for RTE RSV and "0045" for FINAL TIME). The flight crew
may modify these values.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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PRO-NOR-SRP-01-10 P 19/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
SYSTEMS RELATED PROCEDURES - FMS
At takeoff, the RTE RSV field will automatically be reset to 0. The RTE RSV fuel is
then added to the EXTRA fuel, which ensures that the EXTRA fuel and MIN DEST
FOB values are consistent in flight.
ENTER an ALTN fuel value in the [4L] field, as necessary.
The flight crew may enter the ALTN fuel value planned on the Computerized Flight Plan (CFP),
as necessary.
ENTER a MIN DEST FOB value in the [6L] field, as necessary.
Note:
MIN DEST FOB (equal to ALTN + FINAL) can be increased at flight crew discretion
(e.g. when HOLD is expected at destination).
ENTER the TRIP WIND value in the [ 5R ] field, as necessary.
In no wind profile has been entered in the F-PLN, the crew may enter an average TRIP WIND in
this field, to obtain more realistic fuel/time predictions before departure.
Note:
1. The flight crew should only enter a TRIP WIND to obtain realistic fuel/time
predictions, on ground. Then, the flight crew should enter a wind profile using the
WIND pages, for fuel/time predictions in flight. As soon as flight crew has entered a
wind profile on the WIND pages, the TRIP WIND will be erased.
2. If the crew has already defined a wind profile, even partially (such as climb wind), it
is not possible to enter a TRIP WIND.
ENTER the planned BLOCK fuel, as indicated in the computerized flight plan (CFP)
If the planned BLOCK fuel is not available, the crew may obtain a prediction of the minimum
BLOCK fuel required for the flight by pressing the FUEL PLANNING prompt [3R].
Pressing this prompt makes the FMS compute the minimum required BLOCK fuel, which is the
BLOCK fuel required to have EXTRA fuel = 0, based on the parameters entered on the INIT and
F-PLN pages.
The computed BLOCK fuel value is displayed in the [2R] field, and a BLOCK CONFIRM prompt
appears in the [3R] field.
Note:
In order to obtain a realistic fuel computation, the flight crew should ensure that the
F-PLN initialization has been completed (including insertion of the ALTN F-PLN and/or
ALTN fuel and/or MIN DEST FOB if necessary), and that flight parameters, such as
CRZ FL, steps climbs (if any), and winds, have been inserted.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PRO-NOR-SRP-01-10 P 20/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
When the final Load and Trim Sheet (LTS) data are available:
ENTER the final ZFW/ZFWCG [1R], and the required BLOCK fuel [2R].
The FMS computes the predictions, based on the entered BLOCK fuel, and estimates the
EXTRA fuel value.
CHECK the resulting computed data, against the data planned on the CFP: TRIP fuel, RTE
RSV fuel, ALTN fuel, FINAL and EXTRA fuel values.
If necessary, the flight crew may modify the ALTN or FINAL fuel values.
PRINT the PREFLIGHT REPORT, if necessary.
When the final Load and Trim Sheet values (ZFW /ZFWCG /BLOCK) have been entered,
the crew may print the pre-flight report, which provides a copy of the F-PLN with the
associated FMS predictions.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PRO-NOR-SRP-01-10 P 21/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Ident.: PRO-NOR-SRP-01-10-B-00003969.0010001 / 15 FEB 11
TAKEOFF WITH NO WEIGHT/CG DATA
If the crew does not enter ZFW /ZFWCG data prior takeoff, or if the FMGC looses these values
due to a power interruption, the following will occur:
‐ At takeoff, the Speed Reference System (SRS ) mode is available (provided a V2 has been
inserted)
‐ When the aircraft leaves the SRS mode, the target speed becomes the current speed and
reverts to selected.
Note:
If the AP /FD has reverted to ALT or V/S (FPA ) mode, the associated A/THR mode is
SPEED. In this case, the system will probably reduce thrust, because the speed will be
equal to, or greater than, the target speed.
When appropriate, to regain FMS predictions and associated managed modes:
INSERT the ZFW/ZFWCG values on the FUEL PRED page.
Ident.: PRO-NOR-SRP-01-10-B-00003970.0007001 / 15 FEB 11
INSERTING WEIGHT/CG DATA AFTER ENGINE START
The flight crew must enter the ZFW /ZFWCG values on INIT B page prior to engine start. If these
data have not been entered at engine start, the MCDU displays the “INITIALIZE WEIGHTS” amber
message in the scratchpad. After engine start, the crew should enter the ZFW /ZFWCG values on
the FUEL PRED page.
PRESS to the FUEL PRED key.
INSERT the ZFW /ZFWCG values in the [4R] field.
This allows predictions and performance computation.
CHECK the resulting computed data, against the data planned on the CFP: TRIP fuel, RTE RSV
fuel, ALTN fuel, FINAL and EXTRA fuel values.
If necessary, the flight crew may modify the ALTN or FINAL fuel values.
PRINT the PREFLIGHT REPORT, if necessary.
When the final load sheet values (ZFW /ZFWCG /BLOCK) have been entered, the crew may print
the pre-flight report, which provides a copy of the F-PLN with the associated FMS predictions.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PRO-NOR-SRP-01-10 P 22/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Ident.: PRO-NOR-SRP-01-10-B-00003971.0001001 / 22 MAR 16
TAKEOFF DATA INSERTION
PROCEDURE
PRESS the PERF key on the MCDU.
WRITE successively and ENTER : V1 , VR , V2.
WRITE and ENTER FLX TEMP or DRT TO .
CHECK/MODIFY the THR RED ALT (Thrust reduction altitude) See *.
CHECK/MODIFY the ACC ALT (acceleration altitude) See *.
CHECK/MODIFY the ENG OUT ACC (engine out acceleration altitude) See *.
CHECK/MODIFY the TRANS ALT (transition altitude) See *
WRITE and ENTER T.O. SHIFT.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-NOR-SRP-01-10 P 23/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
CHECK V1 , V2 on PFD See **
*
Altitudes less than 400 ft above airfield elevation cannot be selected.
** If the PFD does not display V2 at the top of its speed scale, check that at least one FD is
ON.
ENTERING A FLEX TEMPERATURE
WRITE the desired flex temperature in the scratchpad and ENTER using the [4R] key.
Ident.: PRO-NOR-SRP-01-10-B-00003972.0003001 / 22 MAY 12
CLIMB SPEED PRESELECTION
If the managed speeds for the initial climb are not suitable, the pilot can preselect an appropriate
climb speed on the “PERF CLB” page, as long as the climb phase is not active.
The CLB SPD preselection applies, when the:
‐ ATC specifies an initial climb speed.
‐ Initial climb speed must be lower than normal because:
• There are to be turns greater than 120 ° in the initial climb out.
• Obstacle clearance, or some other situation, requires a high climb angle.
• The airfield has a risk area to be quickly cleared (birds reported, for example).
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
PROCEDURE
PRESS the PERF key on the MCDU.
The PERF TAKE OFF page is displayed.
SELECT the “NEXT PHASE” [6R] key to display the CLB page.
WRITE a climb speed and ENTER it.
To revert to managed speed, select MANAGED by pressing [3L].
When the aircraft is transitioning into the climb phase, the preselected value becomes the target
speed:
‐ The selected speed target is active.
‐ The primary flight display shows the target speed in blue.
‐ The FCU’s speed window displays the new speed or Mach number.
Ident.: PRO-NOR-SRP-01-10-B-00003973.0003001 / 09 OCT 12
CRUISE MACH (SPEED) PRESELECTION
The pilot preselects a cruise Mach, when a Mach number other than the ECON cruise Mach
number is required.
When the aircraft transitions to the cruise phase, the speed target symbol goes to the preselected
value and “SELECTED” becomes the active speed mode (blue target on PFD , target MACH
shown in the speed/Mach window of the FCU).
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PROCEDURES
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A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
PROCEDURE
PRESS the PERF key on the MCDU.
PRESS the “NEXT PHASE” [6R] key on the MCDU , until the CRZ page is accessed.
WRITE a cruise Mach (or speed) in the scratchpad and ENTER it in [4L].
To revert to managed speed, PRESS [3L].
When the cruise phase is active, you cannot preselect a cruise Mach or speed.
Ident.: PRO-NOR-SRP-01-10-B-00004095.0001001 / 09 OCT 12
ENTERING A HEADING/TRACK PRESET FUNCTION
Tfhe heading/track preset allows the pilot to preset a takeoff or go-around heading or track before
commanding the aircraft to take up that heading or track (manual activation).
The flight crew can enter a heading or a track preset while the aircraft is on the ground and until
takeoff.
PROCEDURE
Before takeoff:
SET the appropriate HDG or TRK in the FCU window.
This disarms the navigation mode and allows the runway mode to remain engaged after
takeoff.
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PROCEDURES
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FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
After takeoff:
PULL HDG/TRK knob.
The heading or track mode engages on the preset value.
The direction in which the pilot rotates the HDG/TRK selection knob usually determines the
direction of the turn. A left rotation (decreasing heading) produces a left turn; a right rotation
produces a right turn.
However, when a heading has been preset before takeoff or go-around, the direction of the
turn will be such as to cause the shortest turn at the moment of engagement.
CANCELLING THE HEADING/TRACK PRESET FUNCTION
The pilot can cancel the heading preset by pushing the HDG/TRK knob back in again. This
engages or arms the NAV mode.
FMGS RE-INITIALIZATION AFTER A CANCELED FLIGHT
Ident.: PRO-NOR-SRP-01-10-00013064.0001001 / 16 NOV 11
Applicable to: ALL
If the flight crew initially prepared a flight with all the data associated with this flight (takeoff speeds,
winds, etc.), and if this flight is later canceled and replaced by another flight, the flight crew may use
the following procedure to initialize the FMGS again:
PREPARE the new flight data in the secondary flight plan, using SEC INIT A, SEC INIT B, and SEC
PERF pages
ACTIVATE the secondary flight plan.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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← C to D →
PRO-NOR-SRP-01-10 P 27/28
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PROCEDURES
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FLIGHT CREW
OPERATING MANUAL
Note:
SYSTEMS RELATED PROCEDURES - FMS
When the flight crew activates the secondary flight plan, the following data of the primary
flight plan is lost if the secondary flight plan does not include any replacement data:
‐ Alternate data
‐ Winds and cruise TEMP at waypoints as inserted on CRZ WIND pages
‐ Departure and arrival selection (STAR , APP, RWY ) and approach parameters (QNH ,
TEMP , WIND, TRANS ALT , VAPP , MDA /MDH , DH , LDG CONF)
‐ Altitude, speed, and time constraints
‐ Steps
‐ CMS
‐ Offsets
‐ Flaps/THS
‐ Preselected cruise and descent speeds.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←D
PRO-NOR-SRP-01-10 P 28/28
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Before Pushback or Start
CHANGE OF RUNWAY
Ident.: PRO-NOR-SRP-01-15-00003975.0003001 / 22 MAY 12
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SRP-01-15 P 1/4
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
PRESS the F-PLN key on the MCDU.
SELECT the LAT REV at origin.
SELECT the DEPARTURE prompt [1L].
SELECT the new RWY in use.
SELECT the appropriate SID and TRANS.
CHECK the resulting temporary F-PLN and INSERT it.
CHECK TAKE OFF DATA comes up in the scratchpad if the PERF TO page had been filled in.
ENTER the new V1 , VR , V2 , FLEX TEMP or CONF, as appropriate.
Note:
If the previously selected SID is compatible with the new runway, it automatically appears in
the temporary flight plan. Any revision the pilot may have made to the previous SID will not
be transferred.
If the pilot still wants it, he has to reenter it.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SRP-01-15 P 2/4
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
TAKEOFF FROM INTERSECTION
Ident.: PRO-NOR-SRP-01-15-00003976.0001001 / 09 DEC 09
Applicable to: ALL
Use RTOW or FCOM to revise takeoff parameters :
PRESS the [PERF] key on MCDU
ENTER the takeoff shift
ENTER the new V1 , VR , V2 , FLX TEMP, or CONF, as appropriate
Note:
The insertion of the shift in takeoff position permits the system to make an accurate revision
to its navigation data at takeoff.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PRO-NOR-SRP-01-15 P 3/4
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SRP-01-15 P 4/4
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Taxi
FCU SELECTION FOR TAKEOFF
Ident.: PRO-NOR-SRP-01-20-00003978.0004001 / 09 OCT 12
Applicable to: ALL
PROCEDURE
ENSURE that HDG – V/S modes are selected (change over pb).
CONFIRM or SELECT the first cleared altitude
CROSS CHECK on PFD the target altitude
CONFIRM both FDs ON
FMA MODE CHECK
Ident.: PRO-NOR-SRP-01-20-00003979.0002001 / 22 MAY 12
Applicable to: ALL
CHECK that the FMA CLB (or ALT) mode is armed
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A to B →
PRO-NOR-SRP-01-20 P 1/4
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PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
SYSTEMS RELATED PROCEDURES - FMS
ALT (in blue or magenta) may be displayed instead of CLB if the FCU altitude or a
constraint is set at or below the acceleration altitude.
If a HDG /TRK was preset, NAV is disarmed.
SELECTING A NAVIGATION DISPLAY
Ident.: PRO-NOR-SRP-01-20-00003980.0001001 / 22 MAY 12
Applicable to: ALL
SET the minimum range to display the first waypoint after departure or as required for weather radar.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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← B to C →
PRO-NOR-SRP-01-20 P 2/4
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
SYSTEMS RELATED PROCEDURES - FMS
←C
PRO-NOR-SRP-01-20 P 3/4
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
SELECTING TAKEOFF DISPLAYS FOR PILOT'S AND COPILOT'S MCDU
Ident.: PRO-NOR-SRP-01-20-00003981.0001001 / 23 DEC 14
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PRO-NOR-SRP-01-20 P 4/4
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Takeoff
MONITORING THE TAKEOFF
Ident.: PRO-NOR-SRP-01-30-00003983.0007001 / 09 OCT 12
Applicable to: ALL
At power set (thrust levers in FLX or TOGA position)
CHECK that the navigation is updated to the runway threshold by verifying that the aircraft
symbol is centered on the runway threshold of the navigation display.
CHECK the FMA for appropriate mode selection
Note:
‐ RWY mode appears if an ILS is tuned to a station corresponding to the departure
runway. Otherwise no lateral mode comes up until the aircraft has lifted off.
At 30 ft
If NAV is armed, it engages automatically.
If NAV is not armed, RWY TRK mode engages and remains displayed until the crew
selects another lateral mode.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SRP-01-30 P 1/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
At 100 ft
Engage AP1 or AP2.
The FMGS has an internal delay that prevents the AP from engaging 5 s after liftoff and if the
aircraft is below 100 ft.
At thrust reduction altitude
“LVR CLB” flashes in the first column of the FMA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SRP-01-30 P 2/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Procedure
SET the thrust levers to the CL detent
A/THR activates automatically
CHECK that A/THR turns to white in the 5th FMA column.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SRP-01-30 P 3/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
CHECK that THR CLB appears in green in the first column.
Depending on the next level off altitude, CLB or ALT is armed and displayed in the second
column.
ALT is armed:
‐ in blue if the next predicted level-off is the FCU -selected altitude (target altitude blue at the
top of the ALT scale)
‐ in magenta if the next predicted level-off is an ALT CSTR (target altitude magenta at the top of
the ALT scale)
At acceleration altitude
The vertical phase automatically switches to climb.
CLB mode engages. The target speed jumps to initial climb speed on the PFD.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SRP-01-30 P 4/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Procedure
CHECK that “CLB” appears in green in the second FMA column.
‐ The speed reference system (SRS ) mode remains engaged until CLB phase is engaged,
which occurs at ACCEL ALT or at any other vertical mode engagement, whichever comes
first.
‐ If during takeoff the FCU altitude is set below the current aircraft altitude, the system ignores
the FCU altitude and the aircraft remains in SRS mode until the pilot selects an altitude above
the aircraft altitude or engages any other mode.
PRESELECTING A HDG OR A TRK
Ident.: PRO-NOR-SRP-01-30-00003984.0001001 / 16 NOV 11
Applicable to: ALL
PROCEDURE
If a HDG or a TRK was preselected on the ground :
PULL OUT the HDG/TRK selector knob when required
CHECK that the HDG/TRK mode is active and displayed on the FMA
When a HDG or TRK is preset, OP CLB mode will engage at the acceleration altitude. (CLB
mode is not available in HDG/TRK mode).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B
PRO-NOR-SRP-01-30 P 5/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
NORMAL TAKEOFF PROFILE
Ident.: PRO-NOR-SRP-01-30-00003985.0002001 / 22 MAY 12
Applicable to: ALL
NO FLIGHT DIRECTOR TAKEOFF
Ident.: PRO-NOR-SRP-01-30-00003986.0004001 / 09 OCT 12
Applicable to: ALL
If a takeoff is initiated without FDs, the system responds as follow:
‐ There are no FD bars.
‐ There is no A/THR arming.
‐ There is no guidance available.
‐ The target speed on the PFD is that selected on the FCU or is defaulted to 100 kt.
‐ Setting the thrust levers to the CL detent does not activate A/THR.
Note:
Do not engage the autothrust prior to selecting a target speed on the FCU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C to D →
PRO-NOR-SRP-01-30 P 6/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
PROCEDURE
Establish initial climb of 15 °
When reaching the thrust reduction altitude (THR RED ALT):
SELECT a climb speed.
SET the thrust levers to CL detent.
ACTIVATE the autothrust.
TURN ON the FDs (basic modes engage).
SELECT appropriate mode.
Failure of both FDs after the start of takeoff:
‐ The FD bars disappear.
‐ The FCU window displays the target speed, which synchronizes on V2, or the current speed
(if it is higher).
‐ The autothrust remains armed.
‐ At thrust reduction altitude, LVR CLB flashes. If the pilot set the thrust levers to the CLB
detent, the autothrust becomes active in selected SPD mode (no FDs selected).
If the current speed is greater than the target speed, the thrust decreases.
‐ At acceleration altitude the target speed does not change, since it is selected.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PRO-NOR-SRP-01-30 P 7/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
TAKEOFF WITH NO V2 ENTRY
Ident.: PRO-NOR-SRP-01-30-00003987.0001001 / 16 NOV 11
Applicable to: ALL
If V2 is not inserted, the speed reference system (SRS) will not engage for takeoff.
5 s after lift off, V/S mode will engage. When V/S engages the current airspeed becomes the FCU
target speed.
To regain a normal speed target, the pilot must :
SELECT the appropriate climb speed on the FCU and PULL out the knob.
At ACC ALT :
PUSH the A/THR pb on the FCU.
SET the thrust levers to CL detent.
PUSH in the SPD selector knob to get a managed speed target.
TAKEOFF USING THE LOCALIZER OF THE OPPOSITE RUNWAY
Ident.: PRO-NOR-SRP-01-30-00003988.0005001 / 09 OCT 12
Applicable to: ALL
If the localizer, of the ILS associated with the opposite runway, must be used for takeoff:
SELECT the RAD NAV PAGE.
ENTER the ILS IDENT.
If the ILS is in the database, the system tunes the proper frequency.
Check that the ILS front course is displayed in the CRS field.
Note:
This may trigger the “RWY /ILS MISMATCH” message. Disregard it.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E to F →
PRO-NOR-SRP-01-30 P 8/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
If the ILS is not in the database:
SET the appropriate frequency, and SET the ILS front course in the CRS field.
DESELECT the LS pb on the FCU.
Since the PFD displays reverse deviation.
DESELECT the LS pb on ISIS.
Since ISIS displays LOC reverse deviation.
SELECT ROSE-ILS on one ND.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
PRO-NOR-SRP-01-30 P 9/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SRP-01-30 P 10/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Climb
MONITORING THE CLIMB PHASE
Ident.: PRO-NOR-SRP-01-40-00003989.0031001 / 23 DEC 14
Applicable to: ALL
The PF MCDU should display the PERF CLB page allowing him to monitor the climb.
The PM MCDU should display the F-PLN page to allow the pilot to monitor time, speed and altitude
predictions. This page also displays matched or missed information for constraints.
CHECK vertical mode CLB if NAV is engaged.
CHECK vertical mode OP CLB if HDG /TRK is engaged.
MONITORING THE ND (ROSE NAV OR ARC)
Displays the lateral and vertical paths, in the current AP /FD active modes.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SRP-01-40 P 1/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
MONITORING THE AP /FD MODES AND FMA
If CLB mode is engaged, the flight mode annunciator (FMA ) and the navigation display (ND) show
the tactical situation as follows:
CASE 1
The FCU selected altitude is set above the next altitude constraint
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SRP-01-40 P 2/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
CASE 2
The FCU selected altitude is set at the next altitude constraint
The aircraft will automatically levels off at this altitude.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SRP-01-40 P 3/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
To resume the climb automatically when the waypoint AAA is reached, apply the following
procedure during the level off (Position 4):
SELECT the FCU altitude to the next constraint (if any) or the cruise FL.
PUSH the FCU ALT selector knob to arm CLB mode.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SRP-01-40 P 4/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
RECOMMENDATION:
To ensure that you will not miss the next constraint, it is recommended to select the FCU
altitude to the next constraint as described above.
MONITORING THE CONSTRAINTS
SPEED, ALTITUDE and TIME constraint can be checked using MCDUs. Each constraint is
preceded by a star that indicates if the constraint is matched (magenta star) or missed (amber
star).
ALTITUDE CONSTRAINT
If an altitude constraint is predicted as missed, use the following procedure:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SRP-01-40 P 5/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
SET the FCU ALT to the next ALT CSTR
CHECK the position of the level off symbol on the ND (blue arrow) with respect to the
waypoint with the constraint.
DECREASE the target speed until the constraint is met.
SPEED CONSTRAINT
CHECK the SPD CSTR predictions on the MCDU.
A magenta or amber star (*) indicates that the aircraft will match or miss the constraint.
If the aircraft is to miss the constraint by more than 10 kt, the MCDU scratchpad displays “SPD
ERROR AT WPT ---- ”.
“CHECK WEIGHT” MESSAGE.
Refer to DSC-22_20-90-20 "CHECK WEIGHT" Message
HDG /TRK MODE ENGAGEMENT
If HDG/TRK is engaged, the guidance does not consider any F-PLN constraint. Therefore if
the flight crew disengages NAV, CLB mode reverts to OP CLB.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SRP-01-40 P 6/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
SPEED SELECTION
If a specific speed is required:
TURN and PULL the SPD selector knob. (This changes the target speed to blue on the PFD
speed scale).
Predictions on the F-PLN page assume that the speed remains selected until the next
SPD LIM or SPD CSTR, or the next phase, whichever comes first.
EXPEDITE CLIMB
Ident.: PRO-NOR-SRP-01-40-00003990.0002001 / 11 FEB 11
Applicable to: ALL
The flight may use the expedite mode temporarily to clear a specified altitude or to match a
constraint.
PRESS EXPED pb on the FCU.
The AP acquires and maintains Green Dot speed. There is no benefit to use expedite mode above
FL 250. The mach corresponding to green dot is too low to maintain an increased vertical speed.
To revert to normal climb:
PUSH ALT knob CLB mode will engage.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
PRO-NOR-SRP-01-40 P 7/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Note:
Pulling ALT knob or V/S knob or SPD/MACH knob also disengages EXPEDITE.
PRESSING EXPED pb never disengages the mode.
IMMEDIATE RETURN TO ORIGIN AIRPORT
Ident.: PRO-NOR-SRP-01-40-00003991.0003001 / 23 JUN 15
Applicable to: ALL
If the SEC F-PLN has been prepared for an immediate return to the airport of origin:
ACTIVATE the SEC F-PLN.
PERFORM a DIR TO the appropriate waypoint.
If the SEC F-PLN has not been prepared for an immediate return to the airport of origin:
PERFORM a lateral revision at TO waypoint
ENTER the departure airport ident in the NEW DEST field and INSERT the temporary flight plan.
PERFORM a lateral revision at the new destination
SELECT: APPR – STAR – VIA – TRANS and INSERT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-NOR-SRP-01-40 P 8/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
When cleared to divert:
PERFORM a DIR TO the suitable waypoint.
ENTER QNH, WIND, MDA/MDH, LDG CONF.
CHECK RAD NAV page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PRO-NOR-SRP-01-40 P 9/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SRP-01-40 P 10/10
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Cruise
REACHING CRUISE FLIGHT LEVEL
Ident.: PRO-NOR-SRP-01-50-00003992.0002001 / 03 NOV 14
Applicable to: ALL
On reaching the cruise flight level, the flight crew should be sure that the FMA displays “ALT CRZ ”
in its second column, which ensures that the aircraft is at cruise flight level and at Economy Cruise
Mach (ECON CRZ MACH).
The FMGS engages the “soft altitude” (SOFT ALT ) mode 2 min after the cruise flight level is
captured and Mach stabilized. (SOFT ALT) mode allows the aircraft to deviate ± 50 ft from the target
altitude to minimize the thrust variation and reduce the fuel consumption.
If the FMA does not display ALT CRZ at the assigned flight level, soft altitude mode will
not engage and the predictions will be computed at the preplanned flight level. This will occur
when the ATC assigned flight level is lower than the preplanned flight level entered on the PROG
page.
If the FMA does not display ALT CRZ at the assigned FL (as may occur when the
ATC-assigned FL is lower than the preplanned FL selected initially):
PRESS the [PROG].
ENTER the current cruise flight level.
Note:
If the current cruise flight level is above the preplanned FL , selecting the FCU updates
it automatically.
“SET SPD AUTO” OR “SET MANAGED SPD” OR “CHECK SPEED MODE”
If the climb phase was flown in selected speed and if the cruise phase is planned to be
flown in managed speed (ECON MACH/SPEED) , “SET SPD AUTO” or “SET MANAGED
SPEED” or "CHECK SPEED MODE" appears on the PFD and MCDU as a reminder.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SRP-01-50 P 1/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
PRESS the FCU speed selector knob to activate the managed Mach.
MONITORING THE NAVIGATION ACCURACY
Applicable to: ALL
Ident.: PRO-NOR-SRP-01-50-A-00003993.0001001 / 22 MAY 12
GENERAL
On aircraft equipped with GPS PRIMARY, the navigation accuracy check is not required as long
as GPS PRIMARY is available.
Otherwise, navigation accuracy shall be checked periodically in cruise.
The PROG page displays an estimated accuracy as being high or low (center of sixth line):
‐ “HIGH” means that the FMGS estimates the FM position accurate enough to meet the EN
ROUTE criteria,
‐ “LOW” means that the pilot must compare raw data from tuned navaids with corresponding data
computed by FM and shown on the ND or MCDU PROG page. The appearance of the message
“NAV ACCUR DOWNGRAD” on the MCDU calls for a similar crosscheck.
Note:
The pilot should make such a comparison periodically, even if the PROG page is
displaying “HIGH” and navaids are available: this allows him to quantify the FM position
error.
The method for checking the accuracy is explained in the SOP and in Evaluation of position
accuracy chapter (Refer to DSC-22_20-20-20 General).
A quick check is explained here below when the TO waypoint is a DME type. (VOR /DME or VOR
/TAC or DME or TAC)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B →
PRO-NOR-SRP-01-50 P 2/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Ident.: PRO-NOR-SRP-01-50-A-00003994.0013001 / 22 NOV 11
POSITION DISCREPANCY
If there is a discrepancy between the raw data position and the FM position:
PRESS the DATA key on the MCDU.
SELECT the POSITION MONITOR page.
SELECT “FREEZE”.
On the other MCDU : Select the GPS MONITOR page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-NOR-SRP-01-50 P 3/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
MONITORING THE FUEL PREDICTIONS
Ident.: PRO-NOR-SRP-01-50-00003995.0013001 / 14 FEB 11
Applicable to: ALL
The F-PLN and FUEL PRED pages display fuel and time predictions throughout the flight. These
predictions are meaningful if the lateral and vertical flight plan, and the entered winds are kept
accurate enough as the flight progresses.
PROCEDURE
In addition to the Fuel Management procedure described in the SOPs (Refer to
PRO-NOR-SOP-15 Cruise - Flight Progress), periodically apply the following actions:
KEEP ACCURATE FMS PREDICTIONS
Periodically UPDATE the F-PLN elements (F-PLN waypoints, step altitudes, predicted winds).
CHECK the MIN DEST FOB value on the FUEL PRED page
The MIN DEST FOB value is computed by the FMS and by default it is equals to ALTN + FINAL.
ALTN , FINAL and MIN DEST FOB can be modified by the flight crew.
At the beginning of the CRZ phase, and/or after any change of destination or alternate airport,
check that the MIN DEST FOB value is meaningful. Otherwise, update the MIN DEST FOB value,
as appropriate.
CHECK the DEST EFOB value on the F-PLN or FUEL PRED page
MONITOR the EFOB at destination on the F-PLN or FUEL PRED page. If necessary, ADAPT the
flight strategy.
"DEST EFOB BELOW MIN" MESSAGE
If the predicted EFOB at destination becomes less than the MIN DEST FOB value displayed on
the FUEL PRED page:
‐ The destination EFOB turns to amber on the F-PLN , FUEL PRED and PERF (CLB , CRZ ,
DES) pages, and REPORT page.
‐ The “DEST EFOB BELOW MIN ” amber message is displayed on the MCDU scratchpad, after
2 min (if the FMS is in CRZ or DES phase).
Note:
If the flight crew has cleared the “DEST EFOB BELOW MIN ” message, and if the
predicted EFOB at destination is still less than the MIN DEST FOB value, the “DEST
EFOB BELOW MIN” message will appear again at the beginning of the descent phase.
PROCEDURE
If the “DEST EFOB BELOW MIN” message is triggered on the MCDU:
CHECK the DEST EFOB value on the F-PLN or FUEL PRED page,
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PRO-NOR-SRP-01-50 P 4/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
CHECK the hypothesis used by the FMS to compute the fuel predictions,
Check that the F-PLN elements (F-PLN waypoints, step altitudes, predicted winds) are
up-to-date, to ensure that the FMS predictions are accurate.
Check that the MIN DEST FOB fuel value is meaningful and corresponds to the planned
fuel strategy.
ADAPT the flight strategy as required.
ENTERING A STEP CLIMB OR A STEP DESCENT
Ident.: PRO-NOR-SRP-01-50-00003996.0002001 / 22 MAY 12
Applicable to: ALL
The crew may use the STEP ALTS page to enter up to four geographic step points or one optimal
step (computed by the FMGS) at any waypoint of the cruise.
PROCEDURE
PRESS the PERF key.
SELECT “STEP ALTS” prompt.
The PERF PAGE displays this prompt in cruise phase. The crew may also call up the STEP ALTS
page using a vertical revision at any cruise waypoint.
ENTERING AN OPTIMAL STEP (ONLY STEP CLIMB)
WRITE a step altitude or FL into the scratchpad.
ENTER the step altitude or FL in the [1R] field.
CHECK the FUEL and TIME SAVINGS predictions on the 5L and 5R fields.
PUSH the INSERT prompt [6R] if adequate.
After insertion, the optimum step climb is updated only when the flight crew presses the UPDATE
prompt [6R].
The ND shows symbols for the start of climb (S/C ) and the top of climb (T/C ). The MCDU shows
the associated pseudo-waypoints.
It is possible to convert an optimum step to a geographic step by overwriting the [1L] field (see
geographic step).
When reaching the step climb pseudo-waypoint:
REQUEST climb clearance.
ADJUST the FCU altitude to the STEP ALT, and PUSH.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
PRO-NOR-SRP-01-50 P 5/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
ENTERING A GEOGRAPHIC STEP
WRITE a step altitude into the scratchpad.
The format is position/altitude (or FL). The position can be a waypoint or waypoint/distance to
waypoint. The waypoint/distance is an along track offset waypoint.
ENTER it in [1L] to [4L] field.
The entry of the initial geographic step point requires both a valid waypoint and altitude entries.
When a step has been entered, the flight crew may change the position and the altitude
independently. The flight crew cannot modify the position and the altitude in a single entry: To
modify both, they should modify the position first, and then the altitude.
CHECK the predictions
When reaching the step climb or descent pseudo-waypoint (S/C or S/D):
REQUEST climb or descent clearance.
ADJUST the FCU altitude to the STEP ALT, and PUSH.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
PRO-NOR-SRP-01-50 P 6/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
The DIST/TIME field may display the following messages:
‐ ABOVE MAX if the step altitude exceeds the MAX ALT.
‐ IGNORED if the start step point is less than 50 NM from the top of descent.
‐ STEP NOW when the aircraft is within 20 NM of the step point.
If the aircraft overflies the step waypoint without commencing a climb or a descent, the
system deletes the step from the vertical F-PLN automatically (a “STEP DELETED”
message is displayed on the MCDU scratchpad), and recomputes the predictions.
A step is not deleted if the FCU altitude is moved only partially towards the step altitude.
The flight phase remains “cruise” whenever a step is initiated.
Note:
For an altitude restriction defined at a waypoint less than 50 NM before the top of
descent and lower than the CRZ FL, it is recommended to enter an altitude constraint
rather than a step.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PRO-NOR-SRP-01-50 P 7/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
IMMEDIATE CHANGE OF LEVEL IN CRUISE
Ident.: PRO-NOR-SRP-01-50-00003997.0001001 / 14 FEB 11
Applicable to: ALL
When the pilot changes his flight level without inserting a step:
‐ If the FCU -selected altitude is above the previous CRZ FL , the CRZ FL on the PROG page
changes to the new flight level.
‐ If the FCU -selected altitude is lower than the previous CRZ FL and if the distance to DEST is
more than 200 NM, the CRZ FL on the PROG page changes.
In that case Mach target is managed as follows:
• At the start of the descent, the Mach target is the managed Mach number at the initial cruise
flight level.
• When the aircraft reaches the new flight level, the Mach target switches either to the Mach
number for the lower CRZ FL , or to the speed for the lower CRZ FL if the aircraft reaches the
crossover altitude. This logic prevents the aircraft from exceeding VMO during descent.
‐ If the FCU -selected altitude is lower than the previous CRZ FL and the aircraft is within 200 NM of
its destination, the system activates the descent phase.
The pilot may reactivate the cruise phase by entering a new cruise flight level in the PROG page.
PREPARATION FOR DESCENT AND APPROACH
Applicable to: ALL
Ident.: PRO-NOR-SRP-01-50-B-00003998.0001001 / 09 DEC 09
GENERAL
The preparation for descent and approach consists of :
‐ Entering PERF and WIND data
‐ Defining the lateral and vertical F-PLN
‐ Checking the tuning (auto or manual) of the appropriate navaids
After receiving the arrival information, the flight crew should use the following procedure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E to F →
PRO-NOR-SRP-01-50 P 8/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Ident.: PRO-NOR-SRP-01-50-B-00003999.0001001 / 22 MAY 12
REVISION OF LATERAL F-PLN
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-NOR-SRP-01-50 P 9/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
PERFORM a lateral revision at destination
SELECT an ARRIVAL
SELECT an APPROACH, a STAR, a TRANSITION, a VIA.
When the pilot selects successive items, the page are automatically sequenced. But pressing
"NEXT PAGE" key brings up the APPR and STAR page successively.
CHECK the temporary revision including the missed approach.
INSERT the temporary revision, [6R] key.
Ident.: PRO-NOR-SRP-01-50-B-00004000.0001001 / 22 MAY 12
REVISION OF VERTICAL FLIGHT PLAN
CHECK that the speed and altitude constraints as displayed on the ND . (Use the CSTR
pusbutton).
ENTER any additional speed or altitude constraints using the vertical revision page.
In order not to be too fast when commencing the approach, you may insert a speed constraint at
the FAF (Final Approach Fix).
When all computations are completed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-NOR-SRP-01-50 P 10/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
REVIEW the flight plan, using the approach chart.
When the destination runway changes and if the previously selected STAR is compatible with the
new runway, the system selects it automatically in the temporary F-PLN . If the flight crew has
entered any revision or constraint on this STAR, it will not be transferred.
The pilot must reenter it in order to retain it for this approach.
Ident.: PRO-NOR-SRP-01-50-B-00004001.0002001 / 14 FEB 11
ENTERING THE WINDS FOR DESCENT
Refer to DSC-22_20-30-20-25 Wind - Temperature - QNH - General.
Ident.: PRO-NOR-SRP-01-50-B-00004002.0002001 / 22 MAY 12
PRESELECTING A MANAGED SPEED/MACH
As long as the descent phase is not active, the PERF DES page may either be used to select a
speed, or a Mach number, or both, to replace the optimum descent speed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-NOR-SRP-01-50 P 11/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
The Flight Guidance Computer then uses the entered speed, instead of the optimum speed for
computing the descent profile.
When the system switches to the descent phase, it sets the MANAGED target speed to the
entered speed. From there, the speed may only be modified by using the FCU selector knob.
Once in descent phase, the pilot cannot modify the MANAGED speed again.
PROCEDURE
PRESS the PERF on MCDU.
SELECT the “NEXT PHASE” prompt.
WRITE the descent speed into the scratchpad and ENTER it.
The 3L field displays the imposed managed speed value.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-NOR-SRP-01-50 P 12/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Ident.: PRO-NOR-SRP-01-50-B-00004003.0003001 / 16 NOV 11
MODIFICATION OF THE CABIN RATE
PROCEDURE
PRESS the MCDU's PERF.
WRITE the new cabin rate in the scratchpad.
ENTER it in the [4R] field.
Ident.: PRO-NOR-SRP-01-50-B-00004004.0010001 / 22 MAY 12
ENTERING THE APPROACH DATA
From PERF DES page, SELECT “NEXT PHASE” [ 6R ] key to display the APPR page.
ENTER QNH , TEMP , WIND at destination (magnetic north reference), minimum in the RADIO or
BARO fields.
(The PFD displays the entered BARO or RADIO minimum value, only when the distance to
destination is less than 250 NM).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-NOR-SRP-01-50 P 13/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
CHECK and, if necessary, MODIFY
‐ LDG CONF (landing configuration),
‐ VAPP (the FM-computed value may be modified),
‐ TRANS ALT (transition altitude).
The scratchpad displays “ENTER DEST DATA” if the approach page is not completed when the
aircraft is 180 NM from destination.
SELECT “NEXT PHASE” in order to display the GO AROUND page.
CHECK and, if necessary, MODIFY the THR RED ALT and the ACC ALT.
Ident.: PRO-NOR-SRP-01-50-B-00004005.0001001 / 22 MAY 12
SELECTING THE RADIO NAVAIDS
CHECK or SELECT the NAVAIDS appropriate for the approach.
For an ILS procedure, the ILS will be autotuned.
NDBs must be manually entered.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-NOR-SRP-01-50 P 14/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Note:
When the destination has a VOR /DME , ENTER it manually in the VOR field. ENTER
its identifier in the BRG /DIST field of the PROG page. This allows you to perform a
permanent NAV accuracy check.
Ident.: PRO-NOR-SRP-01-50-B-00004006.0003001 / 08 DEC 16
COST INDEX FOR LONG-RANGE CRUISE
The flight crew can use the table below to find an approximate Cost Index value that is calculated
for cruise at long-range cruise speed. This value is valid for CRZ FL = OPT ALT ± 1 000 ft.
AIRCRAFT
ENGINE
A318/A319/A320/A321
CFM 56-5-A1/A3
CFM 56-5-A4/A5
CFM 56-5-B1/B2/B3
CFM 56-5-B4 (A321)
CFM 56-5-B4 (A320)
CFM 56-5-B4/P
CFM 56-5-B5/B6/B7
CFM 56-5-B5/2P CFM
56-5-B6/2P CFM 56-5-B7/2P
CFM 56-5-B8/B9
CFM LEAP-1A
PW6122/PW6124
PW1100G-JM
V2500-A1
V2522-A5/V2524-A5/ V2527M-A5
V2530-A5/V2533-A5
V2527-A5/V2527E-A5
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
kg/min
45
40
65
65
55
25
25
CILRC
100 lb/h
60
55
85
85
75
35
35
30
40
15
40
20
40
45
50
50
40
20
55
30
55
60
70
70
55
PRO-NOR-SRP-01-50 P 15/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SRP-01-50 P 16/16
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Descent
DESCENT INITIATION
Ident.: PRO-NOR-SRP-01-60-00004007.0001001 / 14 FEB 11
Applicable to: ALL
The top of descent, displayed on the F-PLN page (T/D ) and on the ND ( ), is a position that the
system calculates, assuming that the aircraft will begin its descent in DES mode with managed
speed, and that the system will guide the aircraft along the descent profile computed with all the
vertical F-PLN data (ALT CSTR, ECON or AUTO MACH/SPD, SPD CSTR, SPD LIMIT) to reach
VAPP at 1 000 ft AGL.
Note:
The ND does not display the top of descent
when HDG (or TRACK) mode is engaged.
PROCEDURES
When the aircraft reaches the top of descent (F/D) :
SELECT the altitude target.
PUSH the ALT selector knob. DES mode engages.
CHECK the FMA annunciators.
DESCENT MONITORING
Applicable to: ALL
Ident.: PRO-NOR-SRP-01-60-A-00004008.0007001 / 06 JUN 16
DES MODE ENGAGED
When DES mode is engaged, NAV mode is engaged, and the system takes into account all
altitude and speed constraints of the F-PLN.
The key parameter for monitoring the descent is the vertical deviation (VDEV ) displayed on the
PFD and on the PROG page, which indicates whether the aircraft is on, above, or below the
descent profile.
PROCEDURE
SET the ATC -cleared altitude on the FCU (considering also what is the safe altitude).
If the lowest safe altitude is higher than the ATC -cleared altitude, check with ATC that this
constraint applies.
If it is confirmed, SET the FCU altitude to the safe altitude until it is safe to go to the
ATC-cleared altitude.
MONITOR vertical deviation (VDEV ) on the PFD and the PROG page.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
PRO-NOR-SRP-01-60 P 1/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
MONITOR the speed change that occurs, when the aircraft reaches a speed change symbol
(magenta ball) under managed speed.
MONITOR the FMA (ALT *, ALT CST*, ALT , ALT CST), when the aircraft reaches level
symbols.
If the aircraft is on the descent profile:
The aircraft is considered to be on the vertical profile, when it is within 50 ft of it. VDEV is
close to zero, and the system predicts that it will match constraints until the aircraft levels off
at the next FCU altitude.
MONITOR the predicted descent point after the next level-off.
A/THR adjusts thrust for the particular segment. The first FMA column may display “THR
IDLE” or “SPEED”.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-60 P 2/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
If the aircraft is above the descent profile:
VDEV is down on the PFD and positive on the PROG page.
A/THR sets IDLE thrust and the AP increases speed by calling for down elevator. If the
aircraft reaches the upper limit of the managed speed range, the aircraft diverges and
maintains the upper limit speed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-60 P 3/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Procedure
SELECT a descent speed higher than the upper limit when possible.
MONITOR the intercept symbol
When this symbol reaches the next ALT CSTR waypoint, “MORE DRAG” appears on the
PFD, indicating that speedbrakes must be extended in order to match the next altitude
constraint. This is an advisory message.
Note:
With DPO , when above the descent profile, the flight crew may have to extend
the speed brakes in order to go back on the descent profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-60 P 4/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
If an altitude constraint is predicted to be missed by more than 250 ft, the vertical
revision page shows ALT ERROR at the waypoint.
If a speed constraint is predicted to be missed by more than 10 kt:
SELECT an appropriate speed.
RESUME managed speed when the aircraft is back on the descent path.
If the aircraft is below the descent profile:
VDEV is up on the PFD and negative on the PROG page. The system maintains the target
speed (managed or selected speed).
MONITOR the intercept symbol ([ ]) on the ND and any leveling off at the next ALT CSTR.
If the aircraft is flying at an altitude that is higher than both the descent speed
limit altitude and the destination elevation +5 000 ft:
The FMGS maintains the V/S at -1 000 ft/min and the target speed, until the aircraft
reaches the altitude constraint or intercepts the descent profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-60 P 5/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
If the aircraft is flying at an altitude that is lower than either the descent speed
limit altitude, or the destination elevation +5 000 ft:
The FMGS maintains the V/S at -500 ft/min and the target speed, until the aircraft
reaches the altitude constraint or intercepts the descent profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-60 P 6/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
If the rate of descent has to be increased (ATC requirement):
SELECT OP DES mode
Increase the target speed or extend the speedbrakes.
Ident.: PRO-NOR-SRP-01-60-A-00004009.0002001 / 22 MAY 12
OP DES , V/S OR FPA MODE ENGAGED
‐ In either case, the aircraft is no longer guided on the descent profile and altitude constraints
are disregarded. If NAV mode is engaged the ND displays a white circle on waypoint with an
altitude constraint. If NAV mode is disengaged, the circle is removed.
‐ The PFD still shows VDEV for reference purposes.
‐ The target altitude is always the FCU selected altitude (shown in blue).
On the ND , level-off symbol is blue (no constraint). If NAV mode is engaged and the speed
target managed, speed constraints are considered.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-60 P 7/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
When HDG or TRK mode is engaged, vertical position may also be assessed on the ND using
the energy circle. It is displayed as a green arc oriented on the current track and centered on the
aircraft current position.
Note:
Altitude and speed predictions displayed on the F-PLN page assume an immediate
return to DES mode.
PROCEDURE
SET the FCU altitude as cleared by ATC, while considering the applicable safe altitude.
If the next safe altitude is higher than the ATC -cleared altitude, check with the ATC to verify
that this constraint applies.
If confirmed, set the FCU altitude to the safe altitude, until it is safe to fly at the cleared altitude.
MONITOR the speed target, when the aircraft reaches the speed change symbol.
MONITOR the FMA ALT *, ALT, upon reaching the level symbol.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-60 P 8/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
When in HDG /TRK mode, MONITOR the energy circle on the ND.
The MCDU F-PLN page presents SPD /ALT constraint-matching predictions, which assume that
DES mode is immediately re-engaged.
CHECK the predictions before re-engaging DES mode (in order to resume the descent profile).
Note:
VDEV is available on the PFD even in HDG mode; it is a valuable tool for monitoring
the descent, as long as crosstrack error (XTK) is less than 5 NM.
The aircraft automatically decelerates for approach, only if it flies over the DECEL
pseudo waypoint with NAV mode engaged (or LOC *, LOC).
EXPEDITE DESCENT (IF INSTALLED)
Ident.: PRO-NOR-SRP-01-60-00004010.0001001 / 22 MAY 12
Applicable to: ALL
When ATC requires a rapid descent:
DEPRESS THE EXPED pushbutton
Flight guidance (FG) pitches the aircraft to acquire and maintain 0.80/340. FG orders a pitch
rate that produces no more than 0.15 g. The pilot can use this mode to initiate an emergency
descent. To resume normal descent, PUSH the ALT selection knob or engage any other vertical
mode.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C
PRO-NOR-SRP-01-60 P 9/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
MONITORING THE NAVIGATION IN THE TERMINAL CONTROL AREA
Ident.: PRO-NOR-SRP-01-60-00004012.0002001 / 14 FEB 11
Applicable to: ALL
If the MCDU “AREA RNP IS XX.X” message or “PROCEDURE RNP IS XX.X” message is displayed,
the pilot will manually-entered RNP value in the REQUIRED field of the PROG page and clear or
modify it, if it is not in accordance with the RNP value specified in the area (NAV or approach chart).
TOO STEEP PATH
Ident.: PRO-NOR-SRP-01-60-00004013.0007001 / 22 MAY 12
Applicable to: ALL
“TOO STEEP PATH AHEAD” appears on the MCDU scratchpad, when the system predicts this
situation, and TOO STEEP PATH is displayed on the F-PLN page.
When the aircraft is crossing the first waypoint of a TOO STEEP PATH, the system computes a
flyable descent profile (with an idle segment). The VDEV makes a jump because it is related to a new
profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D to E →
PRO-NOR-SRP-01-60 P 10/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
PROCEDURE
When passing the first waypoint of the TOO STEEP PATH:
MONITOR VDEV and predictions at the next CSTR waypoint.
If required, EXTEND the speedbrakes before seeing the “MORE DRAG” message.
CONSIDER using a holding pattern, if necessary.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-NOR-SRP-01-60 P 11/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
HOLDING PATTERN
Ident.: PRO-NOR-SRP-01-60-00004014.0001001 / 09 OCT 12
Applicable to: ALL
A hold may be required during the descent, and may be manually inserted.
PROCEDURE
PRESS the F-PLN key.
SELECT the lateral revision page.
SELECT the HOLD prompt.
CHECK the HOLDING data, and MODIFY it if necessary.
CHECK the temporary flight plan and INSERT the holding pattern in it.
Note:
If the holding fix is close to the DECEL pseudo waypoint and the speed is managed,
manually activate the approach phase to change the managed target speed to approach
speed (VAPP). This will avoid having an increase of speed not appropriate.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PRO-NOR-SRP-01-60 P 12/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
MANUAL TERMINATION
Ident.: PRO-NOR-SRP-01-60-00004016.0001001 / 09 DEC 09
Applicable to: ALL
You should not use DES mode when entering a leg with manual termination. Manual termination,
which is defined as a track or a heading with no termination, is always part of a database procedure.
The computed descent flight profile may not be adequate when flying this type of leg.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to G
PRO-NOR-SRP-01-60 P 13/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-NOR-SRP-01-60 P 14/14
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Approach
INITIAL APPROACH
Ident.: PRO-NOR-SRP-01-70-00004017.0002001 / 17 MAR 11
Applicable to: ALL
UPON REACHING THE INITIAL APPROACH AREA
‐ Approach phase will activate automatically when flying over the DECEL pseudo waypoint with
NAV , APPR NAV or LOC * or LOC mode engaged.
‐ You will activate manually the approach phase on the PERF page if:
• HDG or TRK mode is engaged, or
• You are flying a go around, or
• An early deceleration is required
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-NOR-SRP-01-70 P 1/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
MANAGED SPEED
CHECK that managed speed is active: MONITOR the target speed.
During the approach, the autothrust limits the speed of the current configuration. (GD, S, F,
VAPP).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PRO-NOR-SRP-01-70 P 2/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
If ATC requires a specific speed:
SWITCH to selected speed (turn and pull the speed selector knob on the FCU).
ADJUST the aircraft configuration accordingly.
If ATC orders successive step descents down to the final approach flight path:
Use the V/S or FPA mode.
MONITOR VDEV.
NAV ACCURACY
As required by the SOP.
Without installed GPS and when no DME is available for the accuracy check, use HIGH/LOW on
the PROG page.
In this case, consider a “HIGH” to be equivalent to a positive crosscheck.
ATC CLEARANCE
MODIFY the F-PLN , RAD NAV , and PERF APPR data to agree with the latest clearance and
landing information.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-NOR-SRP-01-70 P 3/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
ILS/MLS/GLS/FLS APPROACH
Applicable to: ALL
Ident.: PRO-NOR-SRP-01-70-A-00004018.0001001 / 17 MAR 11
INTERMEDIATE/FINAL APPROACH (ILS APPROACH ENTERED IN THE F-PLN)
The preferred technique for flying an ILS approach is to fly a decelerated approach using the
AP /FD s, the LOC and G/S modes, A/THR in the SPEED mode, managed speed target is
recommended.
DECELERATED APPROACH
The decelerated approach technique brings the aircraft down to 1 000 ft, at VAPP . In most
cases, the interception of the final descent path is achieved with CONF 1 at S speed.
(*)
The approach must be stabilized at approach speed (minimum ground speed) in the
landing configuration before reaching 1 000 ft AGL.
Ident.: PRO-NOR-SRP-01-70-A-00004019.0009001 / 17 MAR 11
APPROACH MODE ACTIVATION (LOC -G/S)
When cleared by ATC and when appropriate:
DEPRESS the APPR pushbutton to arm the APPR mode for the approach entered in the flight
plan.
Note:
If a NON PRECISION approach is selected in the active flight plan and if the flight
crew manually tunes an ILS on the RAD NAV page, the MCDU and the PFD display
"CHECK APPR SELECTION". This message is a reminder to the flight crew that,
although an ILS is tuned on RAD NAV page, the available approach guidance modes
are APP NAV -FINAL when the APPR pushbutton is pressed in on the FCU.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-NOR-SRP-01-70 P 4/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
The FCU APPR pushbutton arms or engages LOC and G/S modes, if:
‐ An ILS approach is entered in the flight plan, or
‐ No approach, or only a runway, is entered in the flight plan, and an ILS is manually-tuned on
the RAD NAV page, or
‐ Both RMP s are set to NAV , and an ILS is selected.
Ident.: PRO-NOR-SRP-01-70-A-00004020.0002001 / 17 MAR 11
AUTOLAND
CHECK that the FMA displays the aircraft capability (CAT 2 or CAT 3) for the intended ILS
approach.
MONITOR the radio automatic callout.
At 350 ft RA:
CHECK that “LAND” is displayed on the FMA.
CHECK ILS course.
If LAND is not displayed or if the ILS course is not correct, do not perform an autoland. The
flight crew should perform a go-around, if visual references are not sufficient.
Between 50 and 40 ft RA:
CHECK that “FLARE” is displayed on the FMA.
At approximately 30 ft RA:
CHECK that “IDLE” is displayed on the FMA, and that autothrust starts to reduce thrust toward
IDLE.
At 10 ft, “RETARD” callout comes up:
MOVE the thrust levers to IDLE.
Autothrust disconnects.
At touchdown:
CHECK that “ROLL OUT” appears on the FMA.
Note:
In the case of tailwind during an automatic rollout, it is recommended to use manual
braking without delay or automatic braking for an optimised runway centerline
tracking.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-70 P 5/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
At the end of the Rollout:
Disconnect the autopilot.
If the flight crew does not disconnect the AP at the end of the rollout, and uses the nosewheel
steering handwheel to taxi the aircraft off the runway, the following will occur:
‐ The AP will try to steer the aircraft back to the runway centerline, if the nosewheel steering
handwheel is released and the aircraft heading is less than 20 ° off the runway centerline.
‐ The AP will automatically disconnect, if the aircraft heading is 20 ° or more off the runway
centerline.
Ident.: PRO-NOR-SRP-01-70-A-00004021.0001001 / 17 MAR 11
MANUAL LANDING
At DH:
DISCONNECT the APs. SPEED mode remains engaged.
At 20 ft “RETARD” automatic call out comes up:
MOVE the thrust levers to IDLE if they are not there already. (The A/THR disconnects).
At touch down:
“ROLL OUT” appears on the FMA and the yaw bar comes up on the PFD.
Note:
The retard call out is only a reminder when a manual landing is performed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-70 P 6/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Ident.: PRO-NOR-SRP-01-70-A-00004022.0011001 / 22 MAY 12
STANDARD ILS AUTOMATIC APPROACH
Ident.: PRO-NOR-SRP-01-70-A-00004023.0001001 / 26 NOV 13
EARLY SELECTION OF APPROACH MODE LOC -G/S
Pressing the APPR pushbutton arms LOC and G/S.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-NOR-SRP-01-70 P 7/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
When the aircraft is above 5 000 ft AGL , the Radio altimeter signals may not be valid. As long as
the Radio altimeter signals are invalid, the FMA displays CAT 1.
When the aircraft is cleared for an ILS/MLS /GLS approach:
PRESS the APPR pb on the FCU.
When the aircraft is below 5 000 ft AGL:
Check that the FMA displays the correct capability for the intended approach.
Ident.: PRO-NOR-SRP-01-70-A-00004024.0002001 / 29 MAY 13
GLIDESLOPE INTERCEPTION FROM ABOVE
If the aircraft is above the glideslope, the system will not capture the G/S automatically.
The pilot must bring the aircraft onto the glideslope beam, and select an appropriate V/S to
intercept it. Refer to PRO-NOR-SOP-18-C Approach using LOC G/S Guidance - General.
Ident.: PRO-NOR-SRP-01-70-A-00004025.0001001 / 17 MAR 11
DATA LOCK
When the aircraft reaches 700 ft RA with APPR mode (LOC and G/S ) armed or engaged, the ILS
FREQ and course are frozen in the receiver.
This function (ILS tune inhibit) is available, when at least one AP /FD is engaged. Any attempt to
change the ILS frequency or CRS , via the MCDU or RMP, does not affect the receiver.
If the speed is managed, the system does not accept any modifications the pilot may enter on the
PERF APPR page (surface wind, selected landing configuration, or VAPP) for speed guidance
purposes below this altitude.
When the aircraft reaches 400 ft RA, LAND mode engages. The flight crew can only disengage
this mode by engaging the GO AROUND mode.
Ident.: PRO-NOR-SRP-01-70-A-00004026.0001001 / 17 MAR 11
USE OF RMP S FOR ILS /DME
If both FMGC s fail, the flight crew can use the RMP s (Radio Management Panels 1 and 2) for
back up tuning. Either RMP controls ILS . Prior to select an ILS frequency on one of the RMP s,
the flight crew has to select “NAV ” button from RMP 1 and RMP 2.
If the ILS has a DME , the PFD will not display the DME distance. In this situation, the flight crew
will fly without DME information. If necessary, increase the Decision height (DH) accordingly.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-NOR-SRP-01-70 P 8/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
Ident.: PRO-NOR-SRP-01-70-A-00004027.0001001 / 22 MAY 12
LOCALIZER (LOC) BEAM CAPTURE
The flight crew must always monitor the capture of a LOC beam. During this evolution, the PFD
and ND must indicate that associated deviation indications move toward the centre of the scale.
To avoid performing a false capture, the flight crew must be careful not to arm the LOC too early.
The following graph shows the angle of interception versus distance to the runway threshold that
ensures that the aircraft will not overshoot the axis by more than one and a half dot.
The capture begins when the deviation is two dots or less. It is programmed to line the aircraft up
on the beam with a single overshoot, even if the intercept angle is large.
Note:
ICAO requires LOC beam to ensure a normal capture within 10 NM and plus or minus
35 ° from the course centerline. Some ILS systems just meet the requirement and are
subject to false capture outside these limits.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-NOR-SRP-01-70 P 9/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
SWITCHING FROM NON ILS TO ILS APPROACH
Ident.: PRO-NOR-SRP-01-70-00004028.0002001 / 17 MAR 11
Applicable to: ALL
If an ILS approach is possible when a non ILS was previously scheduled, use one of the following
procedures:
USE OF SECOND FLIGHT PLAN
Use a secondary flight plan to prepare the alternate ILS approach, time permitting.
COPY the ACTIVE flight plan.
REVISE the ARRIVAL: insert the ILS approach and the applicable STAR/VIA.
On the RAD NAV page, TUNE in the ILS manually.
REVISE the PERF APPR page.
CHANGE OF THE CLEARANCE
ATC changes the clearance from the non-ILS to the ILS approach.
If a secondary flight plan has been prepared:
ACTIVATE the SEC F-PLN and adjust.
Follow subsequent standard procedures.
If a secondary flight plan has not been prepared:
REVISE the ARRIVAL on the primary F-PLN, inserting the ILS approach.
REVISE the PERF APPR page.
Follow subsequent standard procedures.
CAUTION
If the pilot decides to fly the ILS approach without revising the arrival of
the primary flight plan (a non ILS approach is in the F-PLN ), LOC and G/S
modes will not be available when he presses the APPR pushbutton.
Consequently, he should:
• Manually TUNE in the ILS on the RAD NAV page: CHECK that the
"CHECK APPR SELECTION" message comes up.
• Press the ILS pushbutton and select ROSE ILS on the EIS CONTROL
panel.
• Use HDG , V/S or TRK , FPA modes to fly the ILS.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PRO-NOR-SRP-01-70 P 10/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
LANDING CATEGORIES
Ident.: PRO-NOR-SRP-01-70-00004038.0001001 / 16 NOV 11
Applicable to: ALL
Each FMGC computes its own landing category : CAT 1, CAT 2, CAT 3 single, and CAT 3 dual and
displays the corresponding landing category on the FMAs.
Each category depends upon the availability of aircraft systems and functions.
When the landing capability downgrades, a triple click aural warning is activated.
FAIL-OPERATIONAL AUTOMATIC LANDING SYSTEM
An automatic landing system is fail-operational if, in the event of a failure below alert height, the
remaining part of the automatic system allows the aircraft to complete the approach, flare, and
landing. A CAT 3 DUAL system is a fail-operational automatic landing system.
Note:
In the event of a failure, the automatic landing system operates as a fail-passive system.
FAIL-PASSIVE AUTOMATIC LANDING SYSTEM
An automatic landing system is fail-passive if, in the event of a failure, there is no significant
out-of-trim condition or deviation of flight path or attitude, but the landing is not completed
automatically. A CAT3 single system is a fail-passive automatic landing system.
Note:
With a fail-passive automatic landing system the pilot assumes control of the aircraft after
a failure.
Below 100 ft (radio altimeter), the FMGS freezes the landing capability until LAND mode is
disengaged or both APs are off.
Therefore a failure occurring below 100 ft does not change the category of the system.
ALERT HEIGHT
The alert height is the height above touch down, above which a CAT3 autoland would be
discontinued and a missed approach executed, if a failure occurred in either the airplane systems
or the relevant ground equipments.
Below the alert height, if such a failure occurs, the flare, touchdown and roll out may be
accomplished using the remaining automatic system.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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D
PRO-NOR-SRP-01-70 P 11/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
WARNINGS FOR ILS APPROACH
Ident.: PRO-NOR-SRP-01-70-00004039.0002001 / 17 MAR 17
Applicable to: ALL
AUTOLAND WARNING
With “LAND” or “FLARE” green on the FMA and at least one AP engaged, the AUTOLAND red
light appears on the glareshield when the aircraft is below 200 ft RA and one of the following
events occurs:
‐ The autopilots are lost, or
‐ The aircraft gets too far off the beam (LOC or G/S flash on PFD), or
‐ Loss of LOC signal above 15 ft, or loss of glide signal above 100 ft (transmitter or receivers).
‐ The difference between both radio altimeter indications is greater than 15 ft.
WARNING OF EXCESSIVE BEAM DEVIATION
This warning is a flashing of the LOC and G/S scales on the PFD and ND ROSE ILS. It occurs
whenever:
‐ G/S deviation is greater than 1 dot (above 100 ft RA).
‐ LOC deviation is greater than 1/4 dot (above 15 ft RA).
WARNING ASSOCIATED WITH ILS "LANDING CAPABILITY"
Any downgrading in the aircraft’s capability for automatic approach and landing sounds a
triple-click aural warning.
FAILURE OF BOTH LOCALIZER AND GLIDESLOPE RECEIVERS
The PFD and ND (rose ILS mode) display red LOC and G/S flags (if the ILS pushbutton has
been pressed green). LOC and G/S scales disappear from the PFD.
If LOC or G/S modes are engaged and at least one AP /FD is engaged
‐ The AP disengages.
‐ The FD reverts to its HDG -V/S or TRK -FPA modes.
FAILURE OF LOCALIZER OR GLIDESLOPE TRANSMITTER (WHEN CAPTURED)
‐ The corresponding index is lost.
‐ The LOC and G/S scales flash.
‐ The corresponding FD bar flashes.
Above 200 ft RA , if the transmitter failure lasts less than 7 s, the FMA retains the LOC and G/S
modes (or the LAND mode) and the AP s are able to regain these modes. If the failure lasts
longer than 7 s, the AP disengages and the FD reverts to its basic modes. Below 200 ft RA , if
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-NOR-SRP-01-70 P 12/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
SYSTEMS RELATED PROCEDURES - FMS
the transmitter failure occurs, the AUTOLAND warning appears, indicating that the crew must
perform a GO AROUND (if insufficient visual references) with one or 2 APs engaged.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-NOR-SRP-01-70 P 13/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
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GLG A318/A319/A320/A321 For A/C: HC-CRU
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PRO-NOR-SRP-01-70 P 14/14
22 MAR 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
Go-Around
MONITORING THE GO-AROUND
Ident.: PRO-NOR-SRP-01-80-00004054.0002001 / 09 DEC 09
Applicable to: ALL
Engage the GO-AROUND phase and GO-AROUND modes by setting the thrust levers to the TOGA
position, if at least CONF1 is selected.
When the GO-AROUND phase is engaged, the previously-flown approach is automatically strung
back into the flight plan at the end of the missed approach procedure.
In the GO-AROUND phase, the system makes no predictions. Consequently, CLB and DES modes
are not available, and the flight crew must monitor constraints.
When the aircraft leaves the GO-AROUND phase, all predictions and modes become available
again. During a GO-AROUND phase, the managed speed is Green Dot.
HEADING/TRACK PRESET FUNCTION IN GO-AROUND PHASE
The flight crew can use the heading/track preset, when LOC *, LOC , LAND, FINAL or GA is
engaged.
SET the appropriate heading, or track value, in the window of the FCU.
When necessary, PULL the HDG/TRK selection knob to engage the mode on the preset value.
GO-AROUND PROFILE
Ident.: PRO-NOR-SRP-01-80-00004055.0014001 / 22 MAY 12
Applicable to: ALL
WITH FD ON:
Apply SOP procedures
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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PRO-NOR-SRP-01-80 P 1/4
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
MISSED APPROACH: TRY AGAIN
Ident.: PRO-NOR-SRP-01-80-00004057.0008001 / 14 FEB 11
Applicable to: ALL
If the pilot intends to fly another approach to the destination:
‐ The flight plan has all the necessary data for the missed approach
‐ Green Dot is the target speed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-NOR-SRP-01-80 P 2/4
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
When cleared by the ATC to follow the missed approach procedure:
ENGAGE NAV mode, or
TURN and PULL the HDG selector knob to set a heading
HDG , or TRK , or NAV modes can only be engaged above 100 ft.
When entering the initial approach area:
Activate the approach phase on the MCDU's PERF GO AROUND page
If the APPR phase is not activated:
‐ Managed approach speed will not be available
‐ The system will not furnish predictions
‐ BARO /RADIO minima displays will not appear on the PFD.
MISSED APPROACH: DIVERT
Ident.: PRO-NOR-SRP-01-80-00004058.0001001 / 14 FEB 11
Applicable to: ALL
If the crew decides to divert to the alternate:
ENABLE ALTN, preferably at the TO waypoint.
When cleared to a waypoint:
PERFORM a DIRECT TO.
The system automatically reverts to CLB phase, and modifies the target speed from Green Dot
to initial speed.
The system automatically sets the CRZ FL to the defaulted alternate CRZ FL (FL 220 or 310),
and retains the previous cost index.
The pilot may adjust these as necessary.
Note:
Diversion may also be initiated by entering a NEW DEST in the LAT REV page at the
TO waypoint, or by using the secondary F-PLN, if prepared. Refer to DSC-22_20-60-30
General.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
PRO-NOR-SRP-01-80 P 3/4
24 JAN 17
PROCEDURES
NORMAL PROCEDURES
A318/A319/A320/A321
SYSTEMS RELATED PROCEDURES - FMS
FLIGHT CREW
OPERATING MANUAL
TASK SHARING DURING A GO-AROUND
Ident.: PRO-NOR-SRP-01-80-00004059.0002001 / 20 JUL 15
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
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E
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24 JAN 17
PROCEDURES
SPECIAL OPERATIONS
Intentionally left blank
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-SPO-20 Flight Without Cabin Pressurization
General.....................................................................................................................................................................A
Oxygen Requirements............................................................................................................................................. B
Flight Planning and Execution.................................................................................................................................C
Systems................................................................................................................................................................... D
Performance Data....................................................................................................................................................E
Flight Planning from Brake Release to Landing......................................................................................................F
Ground Distance/Air Distance Conversion..............................................................................................................G
PRO-SPO-40 Extended Range Operations
PRO-SPO-40-10 General
General.....................................................................................................................................................................A
PRO-SPO-40-20 Operational Limitations
Definitions.................................................................................................................................................................A
Area of Operation.................................................................................................................................................... B
PRO-SPO-40-30 Dispatch Consideration
MMEL....................................................................................................................................................................... A
ETOPS Fuel Scenarios........................................................................................................................................... B
ETOPS Critical Fuel Reserves................................................................................................................................C
ETOPS Fuel Requirements.....................................................................................................................................D
Weather Minima.......................................................................................................................................................E
PRO-SPO-40-40 Diversion During Extended Range Operations
Diversion Decision Making...................................................................................................................................... A
Diversion Performance Data................................................................................................................................... B
Guidelines for Diversion Procedure........................................................................................................................ C
PRO-SPO-40-50 Procedures
General.....................................................................................................................................................................A
Normal Procedures.................................................................................................................................................. B
Abnormal and Emergency Procedures................................................................................................................... C
PRO-SPO-40-60 Performance
General.....................................................................................................................................................................A
Maximum Diversion Distance.................................................................................................................................. B
ETOPS Fuel Requirement from Critical Point to Landing - All Engines - Cruise at LRC........................................C
ETOPS Fuel Requirement from Critical Point to Landing - One Engine Out - Cruise at 350kt...............................D
ETOPS Fuel Requirement from Critical Point to Landing - One Engine Out - Cruise at 320kt............................... E
ETOPS Fuel Requirement from Critical Point to Landing - Example......................................................................F
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-SPO-PLP-TOC P 1/2
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PRO-SPO-45 Engine Intermix Operations
Continued from the previous page
Engine Intermix Type 1........................................................................................................................................... A
Engine Intermix Type 2........................................................................................................................................... B
PRO-SPO-50 Reduced Vertical Separation Minimum - RVSM
General.....................................................................................................................................................................A
Required Equipments/Functions for RVSM.............................................................................................................B
RVSM Normal Procedure........................................................................................................................................C
RVSM Abnormal and Emergency Procedure......................................................................................................... D
PRO-SPO-51 Required Navigation Performance (RNP)
General.....................................................................................................................................................................A
RNAV 10 / RNP 10................................................................................................................................................. B
RNAV 5 / BRNAV....................................................................................................................................................C
RNAV 1 RNAV 2 / P-RNAV - Terminal RNAV....................................................................................................... D
RNP 4...................................................................................................................................................................... E
RNP 2 in Oceanic and Remote Continental Area...................................................................................................F
RNP 2 in Domestic Area.........................................................................................................................................G
RNP 1 / Terminal RNP 1- Basic RNP 1................................................................................................................. H
RNP APCH / RNAV(GNSS)......................................................................................................................................I
PRO-SPO-60 Operations on Narrow Runways
General.....................................................................................................................................................................A
Limitations................................................................................................................................................................ B
Procedures...............................................................................................................................................................C
Performance.............................................................................................................................................................D
PRO-SPO-85 ILS PRM Approach
Overview.................................................................................................................................................................. A
Break out Turn and Climb Procedure..................................................................................................................... B
Break out Turn and Descent Procedure................................................................................................................. C
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PRO-SPO-PLP-TOC P 2/2
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT WITHOUT CABIN PRESSURIZATION
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PRO-SPO-20-00001883.0001001 / 12 NOV 15
Applicable to: ALL
Flight without cabin pressurization can result of:
‐ Dispatch under MEL
‐ Departure following a structural damage
‐ Depressurization in flight
The flight crew must decide the flight level and the airspeed depending on:
‐ The cause of the depressurization
‐ The distance to fly
‐ The topographic conditions
‐ The meteorological conditions, and
‐ The passengers on board the aircraft.
Revenue flight is permitted without cabin pressurization, provided that the oxygen requirements
below are achieved.
After a MEL dispatch with both PACKs inoperative, the flight without cabin pressurization is permitted
provided the flight is performed without passengers.
OXYGEN REQUIREMENTS
Ident.: PRO-SPO-20-00001884.0001001 / 21 MAR 17
Applicable to: ALL
CREW MEMBERS
See FAR 121.329 or AIR-OPS CAT.IDE.A.235
PASSENGERS
For flight at cabin pressure altitudes above 10 000 ft, up to and including 14 000 ft, there must be
enough oxygen to supply 10 % of the passengers for the flight at those altitudes that lasts more
than 30 min.
For flight at cabin pressure altitudes above 14 000 ft, up to and including 15 000 ft, there must be
enough oxygen for 30 % of the passengers.
For flight at cabin pressure altitudes above 15 000 ft, there must be enough oxygen for all
passengers.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PRO-SPO-20 P 1/8
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT WITHOUT CABIN PRESSURIZATION
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLANNING AND EXECUTION
Applicable to: ALL
Ident.: PRO-SPO-20-A-00001981.0001001 / 21 MAR 17
ALTITUDE
Flight route planning should consider the above-stated restriction in cabin altitude. If cabin
altitude exceeds 9 550 ± 350 ft, the EXCESS CAB ALT warning on the ECAM will be activated.
When above 14 000 ft, the passenger oxygen masks will drop automatically. Therefore, the
recommended maximum altitude for prolonged flight is FL 100. The minimum altitude should be
selected by respecting :
‐ The Minimum Safe Altitude (MSA),
‐ Turbulence, which is uncomfortable for passengers and,
‐ Low Outside Air Temperature (OAT), which can be uncomfortable for passengers when the
cabin is ventilated by ram air only.
Ident.: PRO-SPO-20-A-00001983.0001001 / 21 MAR 17
AIRSPEED
If decompression is due to structural damage, consider airspeed reduction. Use slats and flaps, as
necessary, to establish low speed conditions. In addition, turbulent conditions are uncomfortable
for passengers, and gust response should be minimized by reducing airspeed.
Ident.: PRO-SPO-20-A-00001984.0001001 / 21 MAR 17
CLIMB AND DESCENT RATE
Takeoff must be performed normally, and the rate of climb must be limited to about 500 ft/min, to
ease the pressure change felt by passengers and crew.
Likewise, the rate of descent must be limited to about 1 000 ft/min, except for the final approach
which must be performed normally. Notify the ATC of any performance deficiency by a remark in
the flight plan.
Ident.: PRO-SPO-20-A-00001985.0004001 / 21 MAR 17
EMER DESCENT IN CASE OF RAPID DEPRESSURIZATION
In the event of depressurization, oxygen is supplied to passengers through an individual mask.
The capacity of the units is such that the aircraft must descend and remain below the following
profile.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PRO-SPO-20 P 2/8
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT WITHOUT CABIN PRESSURIZATION
SYSTEMS
Ident.: PRO-SPO-20-00001990.0002001 / 23 JUN 15
Applicable to: ALL
FAILURE OCCURRING IN FLIGHT
Apply the abnormal and emergency procedures required by ECAM.
FAILURE PRESENT AT DISPATCH
If flight with both packs inoperative:
In that case, the flight must be performed with no passengers.
PACK 1 and 2.......................................................................................................................OFF
RAM AIR................................................................................................................................. ON
Note:
If the "AVIONICS SMOKE" procedure has to be applied, the following flight time
limitations have to be considered to protect the avionic equipment :
At ISA +40 : 0.5 h
At ISA +30 : 1.5 h
At ISA +20 : 4 h
At ISA +10 and below : No limitation.
MAX FL ....................................................................................................................100 or MSA
If both CAB PRESS systems are inoperative, or if there is structural damage:
TEST OF THE MANUAL OPERATION OF THE OUTFLOW VALVE ON GROUND:
PACK 1 pb-sw and PACK 2 pb-sw ..................................................................................... OFF
OUTFLOW VALVE FULLY OPEN...................................................................................CHECK
Check that the outflow valve is fully open on the CAB PRESS SD page
RPCU CB (X23 ON 122VU)............................................................................................... PULL
MODE SEL pb ................................................................................................................... MAN
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FCOM
← C to D →
PRO-SPO-20 P 3/8
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT WITHOUT CABIN PRESSURIZATION
MAN V/S CTL ....................................................................................................................... DN
Check that the outflow valve is fully closed on the CAB PRESS SD page
MAN V/S CTL ....................................................................................................................... UP
Check that the outflow valve is fully open on the CAB PRESS SD page
MODE SEL pb .................................................................................................................. AUTO
RPCU CB (X23 ON 122VU).............................................................................................. PUSH
PACK 1 pb-sw and PACK 2 pb-sw .......................................................................................ON
MAX FL ....................................................................................................................100 or MSA
Between FL 80 and FL 150, oxygen must be provided for 2 % of the passengers. This is
provided by the portable oxygen system. When it is no longer available, descend to FL 80. For
performance at FL 80/250 kt : Use data for FL 100/LRC (Refer to PER-CRZ-CRT-30 LONG
RANGE CRUISE - ISA) and increase fuel consumption by 6 %.
TAKEOFF
Limit the aircraft's rate of climb to about 500 ft/min.
If both CAB PRESS systems are inoperative, or if there is structural damage:
WHEN IN CLEAN CONFIGURATION:
MODE SEL pb ........................................................................................................ MAN
V/S CTL sw ......................................................................................................AS RQRD
Use V/S CTL pb to set the outflow valve opening to 50 %.
OUTFLOW VALVE HALF OPEN.......................................................................... CHECK
The outflow valve opening is limited to 50 %, to prevent the cabin air suction effect.
CLIMB
Note:
The EXCESS CAB ALT warning may occur.
Use the ECAM CLR pb to clear the warning.
DESCENT
Limit the aircraft's rate of descent to about 1 000 ft/min. Perform the final approach normally.
PERFORMANCE DATA
Ident.: PRO-SPO-20-00001991.0002001 / 10 JAN 11
Applicable to: ALL
The following table enables the fuel consumption and the time needed from takeoff to landing to be
determined in case of flight without cabin pressurization.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
PRO-SPO-20 P 4/8
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT WITHOUT CABIN PRESSURIZATION
The table is established for :
‐ Takeoff
‐ Climb from 1 500 ft at 250 kt
‐ Long range cruise speed at FL 100
‐ Descent to 1 500 ft at 250 kt
‐ Approach and landing : IMC procedure 120 kg or 260 lb (6 min)
‐ ISA temperature
‐ CG = 25 %
‐ Normal air conditioning
‐ Anti ice OFF
The table (Refer to PRO-SPO-20 Ground Distance/Air Distance Conversion) gives the conversion
from ground distance to air distance
Following tables have been calculated using databases for CFM 56–5–B /P. If the engines fitted on
the aircraft are not /P, the fuel consumption has to be increased by 3 %.
Note:
For each degree Celcius above ISA temperature apply a correction of 0.01 (kg/°C/NM) or
0.022 (lb/°C/NM).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-SPO-20 P 5/8
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT WITHOUT CABIN PRESSURIZATION
FLIGHT PLANNING FROM BRAKE RELEASE TO LANDING
Ident.: PRO-SPO-20-00001992.0022001 / 10 JAN 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F
PRO-SPO-20 P 6/8
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT WITHOUT CABIN PRESSURIZATION
GROUND DISTANCE/AIR DISTANCE CONVERSION
Ident.: PRO-SPO-20-00001994.0001001 / 10 JAN 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G
PRO-SPO-20 P 7/8
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT WITHOUT CABIN PRESSURIZATION
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-SPO-20 P 8/8
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - GENERAL
GENERAL
Ident.: PRO-SPO-40-10-00002029.0001001 / 23 JUN 15
Applicable to: ALL
The system design and the reliability of the engine installation of this airplane comply with the criteria
for Extended Twin Operations (ETOPS ) flights set forth in AMC 20-6 rev. 2 (EASA) or FAR 25.1535
(FAA), when the aircraft is configured, maintained and operated in accordance with the Airbus CMP
(Configuration, Maintenance and Procedure) document.
This statement of ability does not constitute an approval to conduct Extended-Range Operations.
The ETOPS EXTENDED OPERATIONS Chapter of the AFM APPENDICES AND SUPPLEMENTS
Section refers to the approved Standard for Extended-Range Operations and the applicable
limitations, procedures and performance references.
The operator is responsible for showing that he is complying with the regulation of his nation and for
obtaining operational approval from his national authorities. The operator may amend this chapter, as
needed.
The airplane must be configured in accordance with the Airbus Standard for Extended-Range
Operations. However, the authorities may under certain conditions allow the operator to conduct
ETOPS flights with limited maximum diversion time (for example, 75 min diversion time in a benign
area of operation) without showing full compliance with these standards.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-SPO-40-10 P 1/2
24 JAN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - GENERAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-SPO-40-10 P 2/2
24 JAN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - OPERATIONAL LIMITATIONS
DEFINITIONS
Ident.: PRO-SPO-40-20-00002031.0001001 / 23 JUN 15
Applicable to: ALL
For the purpose of EU-OPS 1-245 and FAR 121-161, Extended-Range Operations are those
intended to be conducted over a route that contains a point beyond 60 min from an adequate airport
at the selected one-engine-inoperative speed in still air and ISA (or prevailing delta ISA) conditions.
An adequate airport is an airport which satisfies the aircraft performance requirements applicable
at the expected landing weight, and sufficiently equipped to be safely used. In particular, at the
anticipated time of use, it should be available and equipped with the necessary services, including
ATC, weather information, navaids and emergency services.
An ETOPS (en-route) alternate airport is a confirmed adequate airport which satisfies the dispatch
weather minima requirements for ceiling and visibility within the required validity period.
AREA OF OPERATION
Ident.: PRO-SPO-40-20-00002032.0001001 / 21 MAR 17
Applicable to: ALL
The ETOPS area of operations is the airspace within which the distance to an ETOPS adequate
airport is less than the ETOPS Max Diversion distance.
The ETOPS maximum diversion distance from an adequate airport must be determined for ISA
(or prevailing delta ISA ) and no-wind conditions, taking into account aircraft performance with one
engine inoperative and the remaining engine operating at MCT.
To determine the ETOPS maximum diversion distance from an adequate airport, the operator must
define a One Engine Inoperative diversion speed for performance computation.
The same approved one-engine-inoperative diversion speed (Refer to PER-OEI-GEN STRATEGY)
must be considered for :
‐ Establishing the area of operation,
‐ Calculating the single-engine fuel planning,
‐ Conducting the diversion in case of engine failure (conditions permitting).
The operator has to define an aircraft weight at diversion that is considered for the ETOPS Maximum
Diversion Distance calculation. This aircraft weight can be taken as a representative but conservative
value of the aircraft gross weight at the critical point of the route or at the various critical points of all
the routes included in a given sector.
The approved one-engine-inoperative descent and cruise speed must be chosen so that the
associated net flight path clears the en-route obstacles with the regulatory margin. However, a
speed other than the approved one-engine-inoperative speed may be used as the basis for obstacle
clearance as long as the fuel required with that speed is covered by the critical fuel scenario.
Refer to PER-OEI-GEN STRATEGYfor these two one-engine-inoperative speeds.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
PRO-SPO-40-20 P 1/2
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - OPERATIONAL LIMITATIONS
When the one-engine-inoperative diversion speed is chosen, the maximum distance from a diversion
airport, can be directly determined for different maximum diversion times, with the help of the tables
provided in this section. The area of possible ETOPS operation can then be drawn on plotting charts.
Another way to determine the maximum distance to a diversion airport is to read the
one-engine-inoperative cruise TAS (for the reference gross weight and at the FL for best TAS ) in
the cruise tables (Refer to PER-OEI-GEN STRATEGY) taking into consideration the appropriate
speed strategy and the minimum altitude for clearing possible obstacles. The maximum distance the
aircraft can travel to a diversion airport is this one-engine-inoperative-TAS multiplied by the maximum
allowed diversion time granted to the operator.
Operators whose authorities require that an approved one-engine-inoperative speed be published in
the Flight Manual must use this approved speed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-SPO-40-20 P 2/2
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - DISPATCH CONSIDERATION
MMEL
Ident.: PRO-SPO-40-30-00002035.0001001 / 03 DEC 13
Applicable to: ALL
The MMEL has been approved taking into consideration the duration of the average ETOPS flight
and the maximum diversion time granted to the airframe/engine combination.
The MMEL published by Airbus and approved by the EASA can be used to establish the airline MEL,
which must be approved by the operator's national authorities.
This MEL will probably be adapted to the airline network, environment and organization.
Other determining parameters will be :
• The maximum and the average diversion times on the route.
• The equipment of the enroute alternates.
• The navigation and communication facilities.
• The average meteorological conditions.
ETOPS FUEL SCENARIOS
Ident.: PRO-SPO-40-30-00012899.0001001 / 23 JUN 15
Applicable to: ALL
According to EASA AMC20-6 rev 2 and FAA 121.646 for establishing the ETOPS critical fuel
reserves, the operator must consider three diversion scenarios:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
PRO-SPO-40-30 P 1/6
24 JAN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - DISPATCH CONSIDERATION
‐ Pressurization Failure + Engine Failure
‐ Pressurization Failure
Same Flight Profile as above, but all engines operating and Diversion Cruise Speed* set to LRC.
‐ Engine Failure
Same Flight Profile as above, but standard descent speed and Diversion Cruise at the FL **
appropriate to gross engine out ceiling at the selected ETOPS diversion speed.
‐ FAA Fuel Requirements
For the first two scenarios, involving depressurization, the required block fuel must be calculated
in accordance with the operator’s ETOPS fuel policy and using the regulatory ETOPS critical fuel
reserves Refer to PRO-SPO-40-30 ETOPS Critical Fuel Reserves.
Depending on the approved one-engine-inoperative speed selected for the single-engine diversion
strategy, either of these two scenarios may result in the higher fuel requirement.
The scenario resulting in the higher fuel requirement is called the ETOPS critical fuel scenario, and
the associated minimum block fuel requirement is the ETOPS critical fuel plan.
Note that, it is not necessary to calculate the 3rd scenario (engine failure), as this scenario is never
critical, due to the higher diversion flight level.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-SPO-40-30 P 2/6
24 JAN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - DISPATCH CONSIDERATION
ETOPS CRITICAL FUEL RESERVES
Ident.: PRO-SPO-40-30-00012901.0001001 / 23 JUN 15
Applicable to: ALL
For the computation of the ETOPS critical fuel reserves and of the complete ETOPS critical fuel
planning according to EASA AMC 20-6 rev 2 and FAR 121.646, the diversion fuel must include the
following fuel provisions:
‐
‐
‐
‐
‐
‐
‐
‐
Fuel burn-off from the critical point to the end of descent at the alternate airport
Fuel for 15 min of holding at 1 500 ft and green dot speed at the alternate
Fuel for an instrument approach and landing
Fuel to account for errors in wind forecasting (5 % wind speed factor on actual forecast wind
speeds or 5 % fuel if actual forecast wind speeds are not used)
Fuel to account for aircraft deterioration (use a demonstrated performance factor or 5 %)
Fuel to account for any Configuration Deviation List (CDL ) or MEL item
Fuel to account for Icing Effects (if forecast) for the critical mission
Fuel to account for APU use (only for the one-engine-inoperative scenario, if APU is operative)
WIND ERRORS
A 5 % wind speed factor (i.e. an increment to headwind or a decrement to tailwind) on the actual
forecast wind should be used to account for potential errors. However if the operator is not using
the actual forecast wind based on a wind model acceptable to the certification authorities then 5 %
of the fuel for the critical scenario is required as a reserve fuel.
ICING
The most critical scenario must be compensated for the greater of:
A. The effect of airframe icing during 10 % of the time during which icing is forecast, including ice
accumulation on unprotected surfaces, and the fuel used by engine and wing anti-ice during
this period.
B. Fuel for engine and wing anti-ice for the entire time during which icing is forecast.
Note:
The ETOPS icing fuel reserve is always limited by (B)
Unless a reliable icing forecast is available, icing may be presumed to occur when the Total Air
Temperature (TAT) is less than +10 °C, or if the outside air temperature is between 0 °C and
-20 °C with a relative humidity of 55 % or more.
APU
Fuel consumption of 80 kg/h / or 176 lb/h (APU GEN ON, APU BLEED OFF).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PRO-SPO-40-30 P 3/6
24 JAN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - DISPATCH CONSIDERATION
In view of our experience, Airbus recommends that the operator includes a contingency fuel
provision from departure to the Critical Point (CP), when computing the ETOPS critical fuel
planning.
ETOPS FUEL REQUIREMENTS
Ident.: PRO-SPO-40-30-00012902.0001001 / 17 NOV 11
Applicable to: ALL
The operator must compare the entire ETOPS critical fuel planning for the ETOPS critical fuel
scenario with the standard fuel planning computed in accordance with the company fuel policy and
applicable operational requirements. The higher of the two fuel requirements must be considered as
the minimum required block fuel for the flight.
WEATHER MINIMA
Ident.: PRO-SPO-40-30-00002046.0001001 / 23 JUN 15
Applicable to: ALL
Weather forecasts for en-route alternates must meet the operator’s applicable weather minimum
requirements.
This paragraph provides the applicable minima required by EASA (EU-OPS 1/AMC 20-6 rev. 2) and
FAA (AC120-42B).
A. EASA DISPATCH WEATHER MINIMA (EU-OPS 1/AMC 20-6 REV. 2)
An airplane cannot be dispatched unless the meteorological forecasts at ETOPS en-route
alternate airports meet the weather minima listed here for a period commencing at the earliest
potential time of landing and ending one hour after the latest expected time of landing:
Approach Type
Precision approach
Non-Precision or Circling approach
CAT II/CAT III approach
Min ETOPS Ceiling
DH /DA +200 ft
MDH /MDA +400 ft
Specific approval required
Min ETOPS Visibility
Authorised visibility +800 m
Authorised visibility +1 500 m
Specific approval required
B. FAA DISPATCH WEATHER MINIMA (AC 120-42B)
An airplane cannot be dispatched unless the meteorological forecasts at ETOPS en-route
alternate airports meet the weather minima listed here for a period commencing at the earliest
potential time of landing and ending at the latest expected time of landing:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to E →
PRO-SPO-40-30 P 4/6
24 JAN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Approach Type
Two or more instrument approaches
Single Precision approach
or Non-Precision approach
or Circling approach
CAT II approach
CAT III approach
EXTENDED RANGE OPERATIONS - DISPATCH CONSIDERATION
Min ETOPS Ceiling
Higher of the two
(M)DH /DA +200 ft
Min ETOPS Visibility
Higher of the two authorised visibility +800 m
(M)DH /DA +400 ft
Authorised visibility +1 600 m
300 ft
200 ft
1 200 m or RVR1 200 m
800 m or RVR550 m
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PRO-SPO-40-30 P 5/6
24 JAN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - DISPATCH CONSIDERATION
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-SPO-40-30 P 6/6
24 JAN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
EXTENDED RANGE OPERATIONS - DIVERSION
DURING EXTENDED RANGE OPERATIONS
FLIGHT CREW
OPERATING MANUAL
DIVERSION DECISION MAKING
Ident.: PRO-SPO-40-40-00002048.0001001 / 21 MAR 17
Applicable to: ALL
The technical criteria governing a re-routing or diversion decision can be classified into four
categories, as follows :
‐ Loss of MNPS capability, before entering the MNPS area (as applicable).
‐ Weather minima at diversion airport(s) going below the company/crew en-route minima, before
reaching the ETOPS Entry Point, or diversion airport(s) becoming unsuitable for any reason.
‐ Failure cases requiring a diversion to the nearest airport (cases leading to a LAND ASAP message
on the ECAM and/or in the QRH).
‐ Failure cases resulting in increased fuel consumption, exceeding the available fuel reserves.
Comments and Recommendations
• Electrical generation
If one IDG fails, a diversion is required in case of :
‐ Blue hydraulic circuit low level, low pressure or overheat, or
‐ APU no start, or
‐ APU or APU generator inoperative, or
‐ Second IDG failure.
• Fuel system
Some failure cases may lead to fuel gravity feeding which implies flight at lower altitude or to some
fuel being unusable. The flight crew's evaluation of the actual situation and the fuel remaining may
lead to the decision that a diversion is required.
• Hydraulic system :
If low level, low pressure or overheat on blue hydraulic circuit, a diversion is required in case of :
‐ One IDG failure, or
‐ APU no start, or
‐ APU/APU GEN failure.
• APU :
If APU/APU GEN fails, a diversion is required in case of :
‐ Blue hydraulic circuit low level, low pressure or overheat, or
‐ One IDG failure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-SPO-40-40 P 1/2
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
EXTENDED RANGE OPERATIONS - DIVERSION
DURING EXTENDED RANGE OPERATIONS
FLIGHT CREW
OPERATING MANUAL
DIVERSION PERFORMANCE DATA
Ident.: PRO-SPO-40-40-00002049.0001001 / 21 MAR 17
Applicable to: ALL
Chapter PER-OEI-GEN contains three single engine descent and cruise procedures:
1. The standard strategy,
2. The obstacle strategy,
3. Fixed speed strategies (ETOPS).
For ETOPS operations, any one of the above diversion strategies can be used provided that the
selected strategy and speed schedule are used in :
• Establishing the area of operation (maximum diversion distance),
• Calculating the diversion fuel requirements for the single-engine ETOPS fuel scenario,
• Demonstrating the applicable obstacle clearance requirements (net flight path and net ceiling).
During the diversion, the flight crew is expected to use the planned speed schedule.
However, based on the evaluation of the actual situation, the pilot in command has the authority to
deviate from this planned one-engine-inoperative speed.
GUIDELINES FOR DIVERSION PROCEDURE
Ident.: PRO-SPO-40-40-00002050.0001001 / 21 MAR 17
Applicable to: ALL
‐
‐
‐
‐
‐
‐
Complete the related failure procedure,
Inform ATC,
Initiate the descent,
Determine which en route alternate is the most suitable (per company procedure),
Divert to the chosen en route alternate,
Comply with the pre-planned diversion strategy and speed schedule, or adjust the speed
schedule, as dictated by the evaluation of the actual situation.
Note:
For detailed guidelines and procedures for conducting the diversion (lateral and vertical
navigation), Refer to DSC-22_20-60-30 - How to Execute a Diversion.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B to C
PRO-SPO-40-40 P 2/2
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
EXTENDED RANGE OPERATIONS - PROCEDURES
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PRO-SPO-40-50-00002051.0001001 / 26 JUN 17
Applicable to: ALL
For ETOPS flights, the flight crew must apply the below procedures, in addition to the SOP (refer
to chapter PRO-NOR-SOP) and the ABNORMAL and EMERGENCY procedures (refer to chapter
PRO-ABN).
NORMAL PROCEDURES
Applicable to: ALL
Ident.: PRO-SPO-40-50-A-00021794.0002001 / 26 JUN 17
COCKPIT PREPARATION
FUEL
Before each ETOPS flight, the flight crew must check that the fuel crossfeed valve is operating
correctly :
FUEL X FEED ..........................................................................................................................ON
On the ECAM FUEL page, check that the fuel crossfeed valve is open (indication is inline
green).
FUEL X FEED......................................................................................................................... OFF
Check that the fuel crossfeed valve is closed.
ABNORMAL AND EMERGENCY PROCEDURES
Ident.: PRO-SPO-40-50-00002053.0007001 / 21 MAR 17
Applicable to: ALL
ELECTRICAL EMERGENCY CONFIGURATION
The flight crew must complete the ECAM procedure using the following:
AIR CONDITIONING
As cockpit and cabin temperature control is lost, it is recommended to open the cockpit door.
PRESSURIZATION
If one engine (or one bleed system) is failed, forward cargo ventilation must be closed to avoid
CAB PR EXCESS CAB ALT from being triggered on the ECAM during descent or cruise.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C →
PRO-SPO-40-50 P 1/2
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - PROCEDURES
FUEL
As all fuel pumps are lost, the engines are fed by gravity. Refer to GRVTY FUEL FEEDING
Procedure.
ENGINE ANTI-ICE
Engine anti-ice valves are permanently open, although the ECAM memo ENG A. ICE is not
displayed on the ECAM (except if the ENG A. ICE pushbutton is at ON).
WING ANTI-ICE
If only one ENG BLEED is available, PACK 1 must be switched OFF, to avoid having both
packs and wing anti-ice supplied by a single bleed source.
BLUE HYDRAULIC CIRCUIT LOW LEVEL OR LOW PRESSURE OR OVERHEAT
Start the APU to ensure availability of the APU generator.
ENGINE OR IDG FAILURE
Start the APU and use the APU electrical channel.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PRO-SPO-40-50 P 2/2
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - PERFORMANCE
GENERAL
Ident.: PRO-SPO-40-60-00002054.0001001 / 25 AUG 15
Applicable to: ALL
The two following cases result in a fuel consumption increase:
‐ RAT extended
‐ In electrical emergency configuration, the engine anti-ice valves are permanently open.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PRO-SPO-40-60 P 1/10
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - PERFORMANCE
MAXIMUM DIVERSION DISTANCE
Ident.: PRO-SPO-40-60-00002055.0035001 / 21 MAR 17
Applicable to: ALL
The following computation conditions have been used in accordance with the interpretation of the
EU-OPS 1.245 and FAR 121.161:
‐ ISA conditions
‐ No wind
‐ Optimum diversion level after engine failure
‐ Single engine diversion speed schedule.
Note:
SPEED
SCHEDULE
MCT /VMO
MCT/320 kt
Obstacles have not to be considered to determine if a route is or is not an ETOPS route.
A/C WEIGHT
AT CRITICAL
POINT (KG)
50 000
55 000
60 000
65 000
70 000
75 000
50 000
55 000
60 000
65 000
70 000
75 000
MAXIMUM DIVERSION DISTANCE
FL FOR
DIVERSION TIME (MIN)
DIVERSION
60
90
120
150
160
160
160
160
160
160
160
160
160
160
160
160
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
414
413
412
410
408
405
412
412
412
410
408
405
B
616
614
612
608
605
600
613
613
612
608
605
600
818
815
812
807
802
795
814
814
812
807
802
795
1 017
1 012
1 007
1 000
992
1 015
1 012
1 007
1 000
992
180
1 219
1 213
1 206
1 198
1 188
1 215
1 213
1 206
1 198
1 188
PRO-SPO-40-60 P 2/10
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - PERFORMANCE
ETOPS FUEL REQUIREMENT FROM CRITICAL POINT
TO LANDING - ALL ENGINES - CRUISE AT LRC
Ident.: PRO-SPO-40-60-00002056.0018001 / 21 MAR 17
Applicable to: ALL
Assumptions:
‐ EMER descent
‐ Long range cruise at FL 100
‐ Final descent 250 kt
‐ Holding 15 min at FL 15
‐ IFR procedure
Not included: 5 % correction on wind value - Anti icing if icing is forecast - performance factor.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PRO-SPO-40-60 P 3/10
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - PERFORMANCE
ETOPS FUEL REQUIREMENT FROM CRITICAL POINT
TO LANDING - ONE ENGINE OUT - CRUISE AT 350KT
Ident.: PRO-SPO-40-60-00002057.0017001 / 21 MAR 17
Applicable to: ALL
Assumptions:
‐ EMER descent
‐ Cruise 350 kt at FL 100
‐ Final descent 250 kt
‐ Holding 15 min at FL 15
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
PRO-SPO-40-60 P 4/10
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - PERFORMANCE
‐ IFR procedure
‐ APU fuel burn.
Not included: 5 % correction on wind value - Anti icing if icing is forecast - performance factor.
ETOPS FUEL REQUIREMENT FROM CRITICAL POINT
TO LANDING - ONE ENGINE OUT - CRUISE AT 320KT
Ident.: PRO-SPO-40-60-00002058.0018001 / 21 MAR 17
Applicable to: ALL
Assumptions:
‐ EMER descent
‐ Cruise 320 kt at FL 100
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E →
PRO-SPO-40-60 P 5/10
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
‐
‐
‐
‐
EXTENDED RANGE OPERATIONS - PERFORMANCE
Final descent 250 kt
Holding 15 min at FL 15
IFR procedure
APU fuel burn.
Not included: 5 % correction on wind value - Anti icing if icing is forecast - performance factor.
ETOPS FUEL REQUIREMENT FROM CRITICAL POINT TO LANDING - EXAMPLE
Ident.: PRO-SPO-40-60-00014769.0001001 / 21 MAR 17
Applicable to: ALL
Note:
The following data and graphs are for example only, and are not for operational use. Even if
the data in the following example is in “kg”, the same method can be applied for “lb”.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← E to F →
PRO-SPO-40-60 P 6/10
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - PERFORMANCE
Assumptions:
‐ Aircraft weight at critical point: 65 000 kg
‐ Diversion speed: 320 kt
‐ Diversion time: 120 min
‐ Distance from Critical point to diversion airport: 700 NM
‐ Wind: 50 kt headwind
‐ Forecasted icing condition on diversion: 40 min
‐ Aircraft perf factor: 5 %
For the determination of the ETOPS fuel requirement, the greatest fuel quantity of the two following
scenarios must be considered (the scenario Engine failure only, without pressurization failure, is
never limiting):
1. Pressurization failure - One Engine Inoperative - 320 kt
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-SPO-40-60 P 7/10
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - PERFORMANCE
‐ Determine the corrected wind for diversion taking into account the 5 % wind speed factor: 50 x
1.05 = 52.5 kt
‐ Enter the ETOPS Fuel from Critical Point to Landing - One Engine Out - Cruise at 320kt graph
to determine the corresponding fuel consumption: 6 900 kg
‐ Determine the final ETOPS fuel requirement, sum of perf factor fuel, icing fuel and fuel
determined the step before:
• Fuel for icing condition (Total anti-ice scenario is limiting): 3.5 % x 40 / 120 = 1.17 %
• Fuel for perf factor: 5 %
• Final ETOPS fuel requirement: 6 900 x 1.0117 x 1.05 = 7 330 kg
2. Pressurization failure - All Engines Operative - LRC speed
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-SPO-40-60 P 8/10
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - PERFORMANCE
‐ Determine the corrected wind for diversion taking into account the 5 % wind speed factor: 50 x
1.05 = 52.5 kt
‐ Enter the ETOPS Fuel from Critical Point to Landing - All Engines - Cruise at LRC graph to
determine the corresponding fuel consumption: 6 700 kg
‐ Determine the final ETOPS fuel requirement, sum of perf factor fuel, icing fuel and fuel
determined the step before:
• Fuel for icing condition (total anti-ice scenario is limiting): 6 % x 40 / 120 = 2 %
• Fuel for perf factor: 5 %
• Final ETOPS fuel requirement: 6 700 x 1.02 x 1.05 = 7 176 kg
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PRO-SPO-40-60 P 9/10
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
EXTENDED RANGE OPERATIONS - PERFORMANCE
The final ETOPS fuel requirement for this diversion is 7 330 kg. The limiting scenario is a
pressurization failure and One Engine Out at a diversion speed of 320 kt.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
PRO-SPO-40-60 P 10/10
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
ENGINE INTERMIX OPERATIONS
FLIGHT CREW
OPERATING MANUAL
ENGINE INTERMIX TYPE 1
Applicable to: ALL
Ident.: PRO-SPO-45-A-00002059.0001001 / 30 JUN 14
The following information provides the conditions and procedures necessary in order to temporarily
operate an A318/A319/A320/A321 aircraft when a CFM56–5B Single Annular Combustor (SAC)
engine is intermixed with a CFM56–5B Double Annular Combustor (DAC) engine.
This engine intermix configuration is indicated in the cockpit with the following placard: “CAUTION:
ENGINE INTERMIX TYPE 1” or "CAUTION: ENGINE INTERMIX".
Ident.: PRO-SPO-45-A-00002060.0001001 / 07 DEC 10
ENGINE PARAMETERS
Engine parameters differ significantly, when the engines are at idle:
EGT
: Up to 250 °C higher on the DAC engine.
FUEL FLOW : Up to 25 % higher on the DAC engine.
N1
: Higher on the DAC engine.
N2
: Lower on ground on the DAC engine; higher in flight on the DAC engine.
Ident.: PRO-SPO-45-A-00002061.0001001 / 07 DEC 10
CROSSBLEED ENG START
The DAC engine has insufficient acceleration capability to sustain idle speed with a large bleed
offtake, when it operates with only 20 injectors. Therefore, it is necessary to preset a 30 % N1 on
the supplying engine before launching the start sequence.
Ident.: PRO-SPO-45-A-00004068.0001001 / 07 DEC 10
TAKEOFF PROCEDURE
‐ The PF must progressively adjust engine thrust in two steps:
• Step 1 : Idle to 50 % N1.
Brakes released, when the 50 % N1 is stabilized on both engines.
• Step 2 : Both engines N1 to takeoff thrust.
This procedure enables a significantly slower acceleration from ground idle to N1 = 50 % for the
double annular combustor.
‐ Other standard operating procedures apply for takeoff.
Ident.: PRO-SPO-45-A-00002062.0001001 / 07 DEC 10
ENGINE RESPONSE
In flight, when the aircraft is in clean configuration, the DAC engine may accelerate from idle more
slowly than the SAC engine. This is particularly evident, if the acceleration follows a deceleration.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PRO-SPO-45 P 1/4
19 JUN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ENGINE INTERMIX OPERATIONS
There is no significant effect on aircraft handling. This difference in engine response disappears
when the slats are extended.
Ident.: PRO-SPO-45-A-00004067.0001001 / 09 OCT 12
ENGINE RELIGHT
The DAC engine relight envelope is more restrictive than the SAC engine relight envelope.
Therefore, in case of engine intermix, the flight crew must use the DAC engine relight procedure
with the corresponding chart (See chart below).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PRO-SPO-45 P 2/4
19 JUN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
ENGINE INTERMIX OPERATIONS
FLIGHT CREW
OPERATING MANUAL
ENGINE INTERMIX TYPE 2
Applicable to: ALL
Ident.: PRO-SPO-45-B-00012731.0007001 / 06 MAR 17
The following information provides the necessary conditions and procedures in order to temporarily
operate an A318/A319/A320/A321 with engine intermix configuration between two different SAC
engines among CFM56–5Bx classic, the CFM56–5Bx/P, the CFM56-5Bx/3 and the CFM56-5Bx/P “TI
HPC kit”.
FADEC intermix configuration 5BM software (installed on CFM56-5B classic) with FADEC 5BR
software is indicated in the cockpit with the following placard: “CAUTION: ENGINE INTERMIX TYPE
2”.
Note:
When FADEC Standard “5BR” or subsequent is installed on both engines, engine thrust
behavior is harmonized (transient thrust dissymmetry no longer exist). Therefore, a placard
is not necessary and is not displayed.
Ident.: PRO-SPO-45-B-00012732.0001001 / 07 DEC 10
ENGINE PARAMETERS
In the case of only one operative pack configuration (only one pack OFF):
‐ N1 : At idle up to 9 % higher on the CFM56-5B/3 TI engine, on ground or in flight in clean
configuration.
‐ N2 : At idle up to 11 % higher on the CFM56-5B/3 TI engine, on ground or in flight in clean
configuration.
Ident.: PRO-SPO-45-B-00012733.0001001 / 07 DEC 10
TAKEOFF PROCEDURE
In the case of only one operative pack configuration, due to the difference in N2 at idle between
engines, the following takeoff procedure is recommended:
‐ The PF progressively adjusts engine thrust in two steps:
• Step 1 : From idle to about 50 % N1 on brakes.
• Step 2 : From both engines at similar N1 to takeoff thrust after brakes release.
‐ Other standard operative procedures apply for takeoff.
Ident.: PRO-SPO-45-B-00012734.0007001 / 14 MAY 12
ENGINE RESPONSE
In the case of only one operative pack configuration, due to the difference in N2 at idle between
engines, the CFM56–5B/3 TI engine may accelerate from idle to high thrust faster than the
CFM56–5B/P SAC engine when the aircraft is on ground or in flight in clean configuration. There is
no significant effect on aircraft handling.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PRO-SPO-45 P 3/4
19 JUN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
ENGINE INTERMIX OPERATIONS
FLIGHT CREW
OPERATING MANUAL
The difference in engine response disappears in flight when the slats are extended.
Note:
Depending on the FADEC standard, the flight crew may observe a different deceleration
between the two engines (CFM56–5B/P engine is faster to decelerate) when the aircraft
is above FL 100 and in unsymmetrical bleed configuration or with the APU BLEED ON.
Ident.: PRO-SPO-45-B-00016162.0010001 / 02 MAY 17
ENGINE RELIGHT
For SAC-TI engine the maximum altitude for the engine relight envelope is reduced, compared
with the SAC engine relight envelope. Therefore, in case of engine intermix, the flight crew must
use the SAC-TI engine relight envelope below.
Engine Relight Envelope
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PRO-SPO-45 P 4/4
19 JUN 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
REDUCED VERTICAL SEPARATION MINIMUM - RVSM
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PRO-SPO-50-00020828.0001001 / 17 MAR 17
Applicable to: ALL
The A318/A319/A320/A321 aircraft systems are designed to comply with the design criteria of the
EASA and FAA regulations (documents references provided in the AFM ) for the RVSM capability.
In addition, operators must obtain an operational approval from their national airworthiness
authorities, in order to operate within the RVSM airspace. The EASA and FAA regulations
(documents references provided in the AFM) also indicate the requirements for obtaining operational
approval.
REQUIRED EQUIPMENTS/FUNCTIONS FOR RVSM
Ident.: PRO-SPO-50-00020955.0002001 / 17 MAR 17
Applicable to: ALL
RVSM regulations require the following equipment/functions in order to be operative:
‐ 2 ADR s + 2 DMCs
‐ 1 transponder
‐ 1 Autopilot function
‐ 1 FCU channel (for altitude target selection and OP CLB /OP DES mode engagement)
‐ 2 PFD functions (for altitude indication)
‐ 1 FWC (for altitude alert function).
RVSM NORMAL PROCEDURE
Ident.: PRO-SPO-50-00020830.0002001 / 17 MAR 17
Applicable to: ALL
For flights in RVSM airspace, the flight crew must apply the standard procedures, in addition to the
following RVSM procedures.
FLIGHT PREPARATION
L2
L1
L2
L1
L2
The flight crew must take into account the conditions that may affect operations in RVSM airspace,
including:
RVSM APPROVAL.................................................................................................................CHECK
Verify that the aircraft is approved for RVSM operations.
WEATHER.............................................................................................................................. CHECK
Review the weather forecasted for the flight route. If severe turbulence is expected, this may affect
the ability to maintain aircraft altitude.
REQUIRED EQUIPMENT FOR RVSM..................................................................................CHECK
Check that the required equipment is operative (MEL).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to C →
PRO-SPO-50 P 1/4
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L1
L2
L1
REDUCED VERTICAL SEPARATION MINIMUM - RVSM
The flight crew should review the maintenance logs and forms, in order to ensure that the
equipment required for RVSM is satisfactory.
ALTITUDES............................................................................................................................ CHECK
Check that the difference between each altitude indication (in the QNH reference) displayed on
PFDs and the airport elevation is less than 75 ft.
Check that the difference between the two primary altitude indications on the PFDs is less than the
tolerance specified in SOP. Refer to PRO-NOR-SOP-06 Glareshield - EFIS Control Panel.
IN FLIGHT
BEFORE ENTERING RVSM AIRSPACE
L2
L1
L2
REQUIRED EQUIPMENT FOR RVSM .....................................................................OPERATIVE
If any of the required equipment fails before the aircraft enters RVSM airspace, the flight crew
must request new clearance, to avoid this airspace.
ALTITUDES........................................................................................................................ CHECK
Check on the PFDs that the difference between altitude indications (in the standard baro
setting) is less than the specified tolerance in the table below.
If only two ADR s are operative, the altimeter indications on PFD and standby altimeter should
be recorded. This information may be useful in case of subsequent PFD altitude discrepancy, or
loss of both remaining ADRs.
L1
Flight Level
FL 50
FL 100
FL 200
FL 300
FL 390
Speed or
Mach Number
250 kt
250 kt
300 kt
M 0.78
M 0.78
Comparison of Altitude Indication (ft)
Difference between ADR Difference between ADR
Difference between
1 and ADR 2 (on PFDs) 3 and ADR 1/2 (on PFDs) STBY ALTI and ADRs
50 (15 m)
65 (20 m)
130 (40 m)
55 (17 m)
80 (24 m)
185 (56 m)
90 (27 m)
135 (41 m)
295 (90 m)
130 (40 m)
195 (59 m)
390 (119 m)
130 (40 m)
195 (59 m)
445 (136 m)
IN RVSM AIRSPACE
L2
L1
L2
L1
L2
AP.......................................................................................................................KEEP ENGAGED
Ensure that autopilot is engaged for cruise, and for flight level changes.
AP GUIDANCE.............................................................................................................. MONITOR
During flight level transitions, do not exceed or go below the assigned flight level by more than
150 ft.
Approximately every hour:
ALTITUDES..................................................................................................................CHECK
Check that the difference between the altitude indications on PFD s is less than the
specified tolerance. For more information, See table in "Before Entering RVSM airspace".
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PRO-SPO-50 P 2/4
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REDUCED VERTICAL SEPARATION MINIMUM - RVSM
Regular check of the flight deck instruments should be sufficient.
L1
AT THE END OF THE FLIGHT
ANY MALFUNCTIONS or DEVIATIONS............................................................................. REPORT
L2
Report any malfunction of the systems that enable the aircraft to maintain altitude, including:
‐ Any malfunction or loss of required equipment
‐ Any deviation involving the functions that enable the aircraft to maintain altitude.
RVSM ABNORMAL AND EMERGENCY PROCEDURE
Ident.: PRO-SPO-50-00020831.0002001 / 17 MAR 17
Applicable to: ALL
ATC............................................................................................................................................ NOTIFY
When the aircraft is in RVSM airspace, the flight crew must notify the ATC of the following situations,
because they may affect the aircraft's ability to maintain the flight level:
‐ The failure of both autopilots
‐ The loss of altimeter system redundancy (only one PFD indication remaining)
‐ An excessive discrepancy in altitude indications, and no way to identify the valid indication
‐ The failure of any other equipment, that affects the aircraft's ability to maintain flight level
‐ The encounter of greater than moderate turbulence.
If the flight crew cannot notify the ATC or obtain the ATC clearance before deviating from the
assigned flight level, they should follow the established contingency procedure and obtain the ATC
clearance as soon as possible.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
PRO-SPO-50 P 3/4
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REDUCED VERTICAL SEPARATION MINIMUM - RVSM
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PRO-SPO-50 P 4/4
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REQUIRED NAVIGATION PERFORMANCE (RNP)
GENERAL
Applicable to: ALL
Ident.: PRO-SPO-51-A-00015857.0001001 / 20 MAR 17
GENERAL
The Performance Based Navigation (PBN ) concept implies that the aircraft follows the defined
track with a requested navigation performance. The PBN includes RNAV and RNP operations.
For RNAV and RNP operations, an operational approval from the airline's national authorities may
be required.
The AFM provides regulatory compliances associated with PBN operations.
Ident.: PRO-SPO-51-A-00015859.0001001 / 09 SEP 14
RNAV/RNP CAPABILITY
Before the aircraft enters an RNAV /RNP airspace, RNAV /RNP capability is based on:
‐ The required RNAV /RNP equipment that is described in each RNAV /RNP section of the FCOM
‐ Navigation Accuracy HIGH displayed on the MCDU PROG page
‐ Any specific local requirements published in the Aeronautical Information Publication (AIP).
When the aircraft flies in RNAV /RNP airspace, RNAV /RNP capability is based on:
‐ Navigation Accuracy HIGH displayed on the MCDU PROG page
‐ Any specific local requirements published in the Aeronautical Information Publication (AIP).
RNAV 10 / RNP 10
Applicable to: ALL
Ident.: PRO-SPO-51-B-00015854.0001001 / 09 SEP 14
GENERAL
RNAV 10 operations correspond to RNP 10 operations.
In RNAV 10 airspace, the aircraft is expected to fly for a long period of time outside radio navaid
coverage.
Ident.: PRO-SPO-51-B-00015855.0001001 / 09 SEP 14
REQUIRED RNAV 10 EQUIPMENT
The minimum navigation equipment required to enter RNAV 10 airspace is:
‐ Two FMGC s (or one FMGC and one BACK UP NAV )
‐ Two MCDUs
‐ Two IRS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
PRO-SPO-51 P 1/12
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REQUIRED NAVIGATION PERFORMANCE (RNP)
‐ Two ND s (the temporary display of ND information via the PFD /ND switch is permitted on one
side)
‐ One GPS if the flight time outside radio navaid coverage is longer than:
‐ 6.2 hr from the time of IRS ground alignment, or
‐ 5.7 hr from the time of the last FM position update.
Ident.: PRO-SPO-51-B-00015863.0001001 / 11 APR 17
PROCEDURE
MANAGEMENT OF DEGRADED NAVIGATION
If one of the following messages is displayed, the flight crew should resume
navigation with the FMGC that provides the correct position:
‐ GPS PRIMARY LOST on one ND /MCDU
‐ NAV ACCUR DOWNGRAD on one ND /MCDU.
If the GPS PRIMARY LOST message is displayed on both NDs/MCDUs, RNAV 10
operations can be continued:
‐ With no time restriction if radio navaids update is available
‐ For 5.7 hr from the time of the last position update if radio navaids update is not available.
After 5.7 hr, the navigation accuracy must be considered LOW regardless of the
navigation accuracy that is displayed on the MCDU PROG page.
If one of the following MCDU or ECAM messages is displayed, the flight crew should
crosscheck the position data using the POSITION MONITOR page, the IRS 1(2)(3)
pages, and the GPS MONITOR page in order to identify which FMGC position is
correct:
‐
‐
‐
‐
FMS 1/FMS 2 POS DIFF
CHECK IRS 1(2)(3)/FM POSITION
CHECK A/C POSITION
NAV FM/GPS POS DISAGREE
The flight crew should resume navigation with the FMGC that provides the correct position.
If NAV ACCUR DOWNGRAD is displayed on both sides:
‐ As per design FMS REQ ACCUR is set by default; this default value (e.g. 2 NM in cruise,
1 NM in terminal area) is more restrictive than overflown airspace required navigation
performance.
‐ Any change on FMS REQ ACCUR to be in accordance with airspace requirement is at
flight crew's discretion; and should be set back to default value when leaving intended
airspace.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PRO-SPO-51 P 2/12
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REQUIRED NAVIGATION PERFORMANCE (RNP)
If NAV ACCUR DOWNGRAD remains displayed, the flight crew should inform ATC that the
RNAV 10 capability is lost.
RNAV 5 / BRNAV
Applicable to: ALL
Ident.: PRO-SPO-51-C-00015851.0001001 / 20 MAR 17
GENERAL
RNAV 5 operations correspond to European BRNAV operations.
Ident.: PRO-SPO-51-C-00015852.0001001 / 06 JUL 17
REQUIRED RNAV 5 EQUIPMENT
The minimum navigation equipment required to enter RNAV 5 airspace is:
‐ One FMGC
‐ One MCDU
‐ One GPS or one DME receiver to update FM position
‐ Two ND s (the temporary display of ND information via the PFD /ND switch is permitted on one
side)
‐ One IRS.
Ident.: PRO-SPO-51-C-00015864.0001001 / 11 APR 17
PROCEDURE
MANAGEMENT OF DEGRADED NAVIGATION
If one of the following messages is displayed, the flight crew should resume
navigation with the FMGC that provides the correct position:
‐ GPS PRIMARY LOST on one ND /MCDU
‐ NAV ACCUR DOWNGRAD on one ND /MCDU.
If one of the following MCDU or ECAM messages is displayed, the flight crew should
check the navigation accuracy with navaid raw data via the MCDU PROG page in
order to identify which FMGC position is correct:
‐
‐
‐
‐
‐
GPS PRIMARY LOST on both ND s/MCDUs
FMS 1/FMS 2 POS DIFF
CHECK IRS 1(2)(3)/FM POSITION
CHECK A/C POSITION
NAV FM/GPS POS DISAGREE
The flight crew should resume navigation with the FMGC that provides the correct position.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
PRO-SPO-51 P 3/12
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REQUIRED NAVIGATION PERFORMANCE (RNP)
If NAV ACCUR DOWNGRAD is displayed on both sides:
‐ As per design FMS REQ ACCUR is set by default; this default value (e.g. 2 NM in cruise,
1 NM in terminal area) is more restrictive than overflown airspace required navigation
performance.
‐ Any change on FMS REQ ACCUR to be in accordance with airspace requirement is at
flight crew's discretion; and should be set back to default value when leaving intended
airspace.
If NAV ACCUR DOWNGRAD remains displayed, the flight crew should inform ATC that the
RNAV 5 capability is lost.
RNAV 1 RNAV 2 / P-RNAV - TERMINAL RNAV
Applicable to: ALL
Ident.: PRO-SPO-51-D-00015848.0001001 / 20 MAR 17
GENERAL
RNAV 1(2) operations correspond to P-RNAV TERMINAL RNAV operations.
The AIP may specify that GPS equipment is required.
Ident.: PRO-SPO-51-D-00015849.0001001 / 06 JUL 17
REQUIRED RNAV 1(2) EQUIPMENT
The minimum navigation equipment required to enter RNAV 1/RNAV2 airspace is:
‐ One FMGC
‐ One MCDU
‐ One GPS or one DME receiver to update the FM position
‐ Two IRS
‐ One FD in NAV mode
‐ Two ND s (the temporary display of ND information via the PFD /ND switch is permitted on one
side).
Ident.: PRO-SPO-51-D-00015865.0001001 / 20 MAR 17
PROCEDURE
BEFORE ENTERING RNAV 1(2) AIRSPACE
The FMS navigation database provides the terminal procedure (RNAV SID , RNAV STAR
, RNAV TRANSITION, etc.) of the flight plan. The flight crew must crosscheck the terminal
procedure from the published charts with the FMS navigation database on the F-PLN page
(waypoint sequences, tracks, distances, and altitude or speed constraints). The flight crew must
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D →
PRO-SPO-51 P 4/12
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REQUIRED NAVIGATION PERFORMANCE (RNP)
not modify the procedure that is provided by the navigation database, unless required by the
ATC (DIR TO, radar vectoring, insertion of waypoints from the navigation database).
MANAGEMENT OF DEGRADED NAVIGATION
If one of the following messages is displayed, the flight crew should resume
navigation with the FMGC that provides the correct position:
‐ GPS PRIMARY LOST on one ND /MCDU
‐ NAV ACCUR DOWNGRAD on one ND /MCDU.
If one of the following messages is displayed, the flight crew should check the
navigation accuracy with navaid raw data via the MCDU PROG page in order to
identify which FMGC position is correct:
‐
‐
‐
‐
‐
GPS PRIMARY LOST on both ND s/MCDUs
FMS 1/FMS 2 POS DIFF
CHECK IRS 1(2)(3)/FM POSITION
CHECK A/C POSITION
NAV FM/GPS POS DISAGREE
The flight crew should resume navigation with the FMGC that provides the correct position.
If NAV ACCUR DOWNGRAD is displayed on both sides:
The flight crew should inform the ATC that the RNAV 1(2) capability is lost.
RNP 4
Applicable to: ALL
Ident.: PRO-SPO-51-E-00015845.0001001 / 09 SEP 14
GENERAL
In this airspace, the aircraft is expected to fly for a long period of time outside radio navaid
coverage.
Ident.: PRO-SPO-51-E-00015846.0001001 / 09 SEP 14
REQUIRED RNP 4 EQUIPMENT
The minimum navigation equipment required to enter RNP 4 airspace is:
‐ Two FMGC s (or one FMGC and one BACK UP NAV )
‐ Two MCDUs
‐ Two IRS
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PRO-SPO-51 P 5/12
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REQUIRED NAVIGATION PERFORMANCE (RNP)
‐ One GPS
‐ Two ND s (the temporary display of ND information via the PFD /ND switch is permitted on one
side).
Ident.: PRO-SPO-51-E-00015866.0001001 / 11 APR 17
PROCEDURE
MANAGEMENT OF DEGRADED NAVIGATION
If one of the following messages is displayed, the flight crew should resume
navigation with the FMGC that provides the correct position:
‐ GPS PRIMARY LOST on one ND /MCDU
‐ NAV ACCUR DOWNGRAD on one ND /MCDU.
If one of the following MCDU or ECAM messages is displayed, the flight crew should
crosscheck the position data using the POSITION MONITOR page, the IRS 1(2)(3)
pages, and the GPS MONITOR page in order to identify which FMGC position is
correct:
‐
‐
‐
‐
‐
GPS PRIMARY LOST on both ND s/MCDUs
FMS 1/FMS 2 POS DIFF
CHECK IRS 1(2)(3)/FM POSITION
CHECK A/C POSITION
NAV FM /GPS POS DISAGREE
The flight crew should resume navigation with the FMGC that provides the correct position.
If NAV ACCUR DOWNGRAD is displayed on both sides:
‐ As per design FMS REQ ACCUR is set by default; this default value (e.g. 2 NM in cruise,
1 NM in terminal area) is more restrictive than overflown airspace required navigation
performance.
‐ Any change on FMS REQ ACCUR to be in accordance with airspace requirement is at
flight crew's discretion; and should be set back to default value when leaving intended
airspace.
If NAV ACCUR DOWNGRAD remains displayed, the flight crew should inform ATC that the
RNAV 4 capability is lost.
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PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REQUIRED NAVIGATION PERFORMANCE (RNP)
RNP 2 IN OCEANIC AND REMOTE CONTINENTAL AREA
Applicable to: ALL
Ident.: PRO-SPO-51-I-00021541.0001001 / 20 MAR 17
GENERAL
In this airspace, the aircraft is expected to fly for a long period of time outside radio navaid
coverage.
Ident.: PRO-SPO-51-I-00021542.0001001 / 20 MAR 17
REQUIRED RNP 2 IN OCEANIC AND REMOTE CONTINENTAL AREA EQUIPMENT
The minimum navigation equipment required to enter RNP 2 oceanic and remote continental
airspace is:
‐ Two FMGC s (or one FMGC and one BACK UP NAV )
‐ Two MCDUs
‐ Two IRS
‐ One GPS
‐ Two ND s (the temporary display of ND information via the PFD /ND switch is permitted on one
side).
Ident.: PRO-SPO-51-I-00021544.0001001 / 20 MAR 17
PROCEDURE
FLIGHT PREPARATION
RAIM /AIME availability should be confirmed for RNP 2 in oceanic and remote continental area
operations.
Refer to PRO-NOR-SOP-02 GPS PRIMARY Availability (If Installed)
MANAGEMENT OF DEGRADED NAVIGATION
If one of the following messages is displayed, the flight crew should resume
navigation with the FMGC that provides the correct position:
‐ GPS PRIMARY LOST on one ND /MCDU
‐ NAV ACCUR DOWNGRAD on one ND /MCDU.
If one of the following MCDU or ECAM messages is displayed, the flight crew should
crosscheck the position data using the POSITION MONITOR page, the IRS 1(2)(3)
pages, and the GPS MONITOR page in order to identify which FMGC position is
correct:
‐ GPS PRIMARY LOST on both ND s/MCDUs
‐ FMS 1/FMS 2 POS DIFF
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05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
REQUIRED NAVIGATION PERFORMANCE (RNP)
FLIGHT CREW
OPERATING MANUAL
‐ CHECK IRS 1(2)(3)/FM POSITION
‐ CHECK A/C POSITION
‐ NAV FM /GPS POS DISAGREE
The flight crew should resume navigation with the FMGC that provides the correct position.
If NAV ACCUR DOWNGRAD is displayed on both sides:
The flight crew should inform the ATC that the RNP 2 capability is lost.
RNP 2 IN DOMESTIC AREA
Applicable to: ALL
Ident.: PRO-SPO-51-J-00021545.0001001 / 20 MAR 17
REQUIRED RNP 2 IN DOMESTIC AREA EQUIPMENT
The minimum navigation equipment required to enter RNP 2 domestic airspace is:
‐ One FMGC
‐ One MCDU
‐ One GPS
‐ Two IRS
‐ Two ND s (the temporary display of ND information via the PFD /ND switch is permitted on one
side).
Ident.: PRO-SPO-51-J-00021546.0001001 / 20 MAR 17
PROCEDURE
FLIGHT PREPARATION
RAIM /AIME availability should be confirmed for RNP 2 in domestic area operations.
Refer to PRO-NOR-SOP-02 GPS PRIMARY Availability (If Installed)
MANAGEMENT OF DEGRADED NAVIGATION
If one of the following messages is displayed, the flight crew should resume
navigation with the FMGC that provides the correct position:
‐ GPS PRIMARY LOST on one ND /MCDU
‐ NAV ACCUR DOWNGRAD on one ND /MCDU.
If one of the following MCDU or ECAM messages is displayed, the flight crew should
check the navigation accuracy with navaid raw data via the MCDU PROG page in
order to identify which FMGC position is correct:
‐ GPS PRIMARY LOST on both ND s/MCDUs
‐ FMS 1/FMS 2 POS DIFF
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05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
REQUIRED NAVIGATION PERFORMANCE (RNP)
FLIGHT CREW
OPERATING MANUAL
‐ CHECK IRS 1(2)(3)/FM POSITION
‐ CHECK A/C POSITION
‐ NAV FM/GPS POS DISAGREE
The flight crew should resume navigation with the FMGC that provides the correct position.
If NAV ACCUR DOWNGRAD is displayed on both sides:
The flight crew should inform the ATC that the RNP 2 capability is lost.
RNP 1 / TERMINAL RNP 1- BASIC RNP 1
Applicable to: ALL
Ident.: PRO-SPO-51-F-00015842.0001001 / 20 MAR 17
GENERAL
RNP 1 operations correspond to RNP 1 Terminal operations.
Ident.: PRO-SPO-51-F-00015843.0001001 / 17 MAR 16
REQUIRED RNP 1 EQUIPMENT
The minimum navigation equipment required to enter RNP 1 airspace is:
‐ One FMGC
‐ One MCDU
‐ One GPS
‐ Two IRS
‐ One FD in NAV mode
‐ Two ND s (the temporary display of ND information via the PFD /ND switch is permitted on one
side).
Ident.: PRO-SPO-51-F-00015867.0001001 / 20 MAR 17
PROCEDURE
FLIGHT PREPARATION
RAIM/AIME availability should be confirmed for RNP 1 operations.
Refer to PRO-NOR-SOP-02 GPS PRIMARY Availability (If Installed)
BEFORE ENTERING RNP 1 AIRSPACE
The FMS navigation database provides the terminal procedure (RNAV SID , RNAV STAR ,
RNAV TRANSITION, etc.) of the flight plan. The flight crew must check the terminal procedure
from the published charts with the FMS navigation database on the F-PLN page (waypoint
sequences, tracks, distances, and altitude or speed constraints). The flight crew must not
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PRO-SPO-51 P 9/12
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
REQUIRED NAVIGATION PERFORMANCE (RNP)
FLIGHT CREW
OPERATING MANUAL
modify the procedure that is provided by the navigation database, unless required by the ATC
(DIR TO, radar vectoring, insertion of waypoints from the navigation database).
MANAGEMENT OF DEGRADED NAVIGATION
If one of the following messages is displayed, the flight crew should resume
navigation with the FMGC that provides the correct position:
‐ GPS PRIMARY LOST on one ND /MCDU
‐ NAV ACCUR DOWNGRAD on one ND /MCDU.
If one of the following MCDU or ECAM messages is displayed, the flight crew should
check the navigation accuracy with navaid raw data via the MCDU PROG page in
order to identify which FMGC position is correct:
‐
‐
‐
‐
‐
GPS PRIMARY LOST on both ND s/MCDUs
FMS 1/FMS 2 POS DIFF
CHECK IRS 1(2)(3)/FM POSITION
CHECK A/C POSITION
NAV FM/GPS POS DISAGREE
The flight crew should resume navigation with the FMGC that provides the correct position.
If NAV ACCUR DOWNGRAD is displayed on both sides:
The flight crew should inform the ATC that the RNP 1 capability is lost.
RNP APCH / RNAV(GNSS)
Applicable to: ALL
Ident.: PRO-SPO-51-G-00015839.0001001 / 20 MAR 17
GENERAL
RNP APCH operations correspond to RNAV (GNSS ) or RNAV (GPS) operations.
Ident.: PRO-SPO-51-G-00015840.0001001 / 11 JUL 17
REQUIRED RNP APCH EQUIPMENT
The minimum equipment required to start RNP APCH operations is:
‐ One FMGC
‐ One GPS
‐ Two IRS
‐ One MCDU
‐ One FD
‐ One PFD on the PF side
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PRO-SPO-51 P 10/12
05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REQUIRED NAVIGATION PERFORMANCE (RNP)
‐ Two ND s (the temporary display of ND information via the PFD /ND switch is permitted on PM
side)
‐ Two FCU channels.
Ident.: PRO-SPO-51-G-00015868.0001001 / 09 SEP 14
PROCEDURE
Refer to PRO-NOR-SOP-18-C Approach using FINAL APP Guidance - General
Refer to PRO-NOR-SOP-18-C Approach using FPA Guidance - General
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PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REQUIRED NAVIGATION PERFORMANCE (RNP)
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05 SEP 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
OPERATIONS ON NARROW RUNWAYS
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PRO-SPO-60-00002094.0002001 / 03 JAN 11
Applicable to: ALL
This chapter gives the limitations, procedures and performance for operations from/to runways with a
width below 45 m .
This chapter does not constitute an operational approval to operate on narrow runways.
Such authorization must be obtained by the operator from the appropriate authorities.
LIMITATIONS
Ident.: PRO-SPO-60-00006122.0002001 / 21 MAR 17
Applicable to: ALL
Minimum runway width...................................................................................................................30 m
The dispatch from/to narrow runways is not allowed in case of :
‐ Nose wheel steering inoperative
‐ One brake or more inoperative
Autoland is not allowed.
PROCEDURES
Ident.: PRO-SPO-60-00006123.0003001 / 21 MAR 17
Applicable to: ALL
Diversion to a 45 m wide runway is recommended in case of :
‐ Rudder jam
‐ Rudder pedal jam
‐ Yaw damper system fault
‐ Rudder Travel Limit system fault
‐ All failures leading to the loss of the nose wheel steering (HYD Yellow system loss, double
hydraulic failure, double BSCU fault, double LGCIU fault)
Maximum demonstrated crosswind for takeoff and landing:
Dry runway........................................................................38 kt (gust included) for takeoff and landing
Wet runway.......................................................................33 kt (gust included) for takeoff and landing
Contaminated runway....................................................... 10 kt (gust included) for takeoff and landing
Note:
These maximum demonstrated crosswind values are based on the assumption that the
crew have been trained accordingly.
Operations on icy runways have not been demonstrated.
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PRO-SPO-60 P 1/2
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
OPERATIONS ON NARROW RUNWAYS
FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
Ident.: PRO-SPO-60-00006124.0001001 / 23 JUN 15
Applicable to: ALL
For runways with a width above or equal to 40 m ., the basic takeoff performance remains
unchanged.
For runways with a width below 40 m , the VMCG must be increased by the values indicated in the
following table :
Runway Width
▵ VMCG(kt)
30 m
+ 2.5
35 m
+ 1.5
40 m
+0
No correction is required, when takeoff performance is determined by using the applicable approved
data.
The minimum V1 values, published in the Refer to PER-TOF-TOD-25-10 SPEEDS LIMITED BY
VMCG/VMCA, must be increased by 3 kt .
When using the takeoff performance for contaminated runways Refer to PER-TOF-CTA-10
GENERAL, the resulting V1 must be crosschecked with the corrected minimum V1.
Further decrease the takeoff weight by 3 t per knot increase in V1.
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PRO-SPO-60 P 2/2
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
ILS PRM APPROACH
FLIGHT CREW
OPERATING MANUAL
OVERVIEW
Ident.: PRO-SPO-85-00020844.0001001 / 17 MAR 17
Applicable to: ALL
The Precision Runway Monitor (PRM) system enables simultaneous close parallel ILS approaches.
The air traffic controllers use the PRM system to monitor the aircraft position. If necessary, the ATC
orders a break out, turn and climb or descent.
To perform PRM operations:
‐ The air traffic controllers and the flight crew must satisfy specific training requirements
‐ The ATC and the aircraft equipment must comply with specific requirements.
BREAK OUT TURN AND CLIMB PROCEDURE
Ident.: PRO-SPO-85-00020845.0001001 / 17 MAR 17
Applicable to: ALL
Simultaneously:
AP.................................................................................................................................................... OFF
BREAK OUT LEFT(RIGHT), HDG___, ALT___................................................................ ANNOUNCE
THRUST LEVERS.............................................................................................TOGA, and back to CL
L2 The SRS GA and the GA TRK modes engage. The THR CLB mode engages.
The speed is managed. The speed target is the aircraft speed at SRS GA engagement.
The FMS GO-AROUND phase becomes active. Therefore, the FMS reinserts the approach.
L1 TURN LEFT(RIGHT) AND CLIMB
L2 As the situation is urgent, the flight crew should temporarily disregard the FD orders.
Then
HDG___..................................................................................................................... TURN AND PULL
The GA TRK mode disengages, and the HDG mode engages.
L1 ALT___.......................................................................................................................TURN AND PULL
L2 The SRS GA mode disengages, and the OP CLB mode engages. The speed target becomes the
FMS speed target of the CLIMB phase.
L1 SPEED................................................................................................................... PULL AND ADJUST
L2 For the initial break out procedure, adjust the speed (e.g. 160 kt), in order to avoid a significant
acceleration, and an increase in workload.
L1
L2
L1
When established on the break out path:
AP................................................................................................................................................ON
L2
Before engaging the AP , ensure that the FD bar orders correspond to the aircraft current path.
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PRO-SPO-85 P 1/4
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
L1
ILS PRM APPROACH
SPEED..............................................................................................................SELECT AS RQRD
FLAPS..............................................................................................................................AS RQRD
GEAR...............................................................................................................................AS RQRD
TCAS MODE SEL................................................................................................TA/RA AS RQRD
BREAK OUT TURN AND DESCENT PROCEDURE
Ident.: PRO-SPO-85-00020846.0001001 / 17 MAR 17
Applicable to: ALL
Simultaneously:
AP.................................................................................................................................................... OFF
TURN LEFT(RIGHT) AND MAINTAIN RATE OF DESCENT
BREAK OUT LEFT(RIGHT), HDG___, ALT___................................................................ ANNOUNCE
L2 As the situation is urgent, the flight crew should temporarily disregard the FD orders.
Then
HDG___..................................................................................................................... TURN AND PULL
The HDG mode engages. The vertical mode reverts to the V/S mode. The vertical speed target is the
aircraft vertical speed at V/S engagement.
L1 ALT___.......................................................................................................................TURN AND PULL
L2 This action defines an altitude target. The OP DES mode and the THR IDLE mode engage. The
speed target does not change.
L1 V/S..........................................................................................................................................MONITOR
L1
L2
CAUTION
Depending on the speed target, the vertical speed may become excessive. If the
rate of descent exceeds 1 000 ft/min, engage the V/S mode and limit the rate of
descent to 1 000 ft/min.
When established on the break out path:
AP................................................................................................................................................ON
L2
Before engaging the AP , ensure that the FD bar orders correspond to the aircraft current path.
L1
When cleared by ATC:
ALT___................................................................................................................................... TURN
L2
Select an altitude target for go-around, in accordance with the ATC clearance.
L1
THRUST LEVERS...................................................................................... TOGA, and back to CL
L2
The SRS GA and the GA TRK modes engage. The THR CLB mode engages.
The speed is managed. The speed target is the aircraft speed at SRS GA engagement.
The FMS GO-AROUND phase becomes active.
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PRO-SPO-85 P 2/4
22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
ILS PRM APPROACH
FLIGHT CREW
OPERATING MANUAL
L1
L2
L1
HDG___................................................................................................................................... PULL
The GA TRK mode disengages, and the HDG mode engages. The SRS GA mode remains
engaged, until ALT* engagement.
SPEED..............................................................................................................SELECT AS RQRD
FLAPS..............................................................................................................................AS RQRD
GEAR...............................................................................................................................AS RQRD
TCAS MODE SEL................................................................................................TA/RA AS RQRD
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22 MAR 17
PROCEDURES
SPECIAL OPERATIONS
A318/A319/A320/A321
ILS PRM APPROACH
FLIGHT CREW
OPERATING MANUAL
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22 MAR 17
LIMITATIONS
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LIMITATIONS
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TABLE OF CONTENTS
LIM-INT Introduction
LIM-AG Aircraft General
LIM-AIR Air Bleed/Cond/Press/Vent
LIM-AFS Auto Flight System
LIM-APU Auxiliary Power Unit
LIM-COM Communication
LIM-ENG Engines
LIM-F_CTL Flight Controls
LIM-FUEL Fuel
LIM-ICE_RAIN Ice and Rain Protection
LIM-LG Landing Gear
LIM-NAV Navigation
LIM-OXY Oxygen
LIM-SURV Surveillance
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19 JUN 17
LIMITATIONS
PRELIMINARY PAGES
A318/A319/A320/A321
TABLE OF CONTENTS
FLIGHT CREW
OPERATING MANUAL
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LIMITATIONS
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
M
(1)
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU Title
DU identification
LIM-AFS-20
Automatic Landing in Johannesburg
00013685.0001001
Criteria: A320
Applicable to: ALL
Impacted DU: NONE
LIM-AFS-20
Autoland Databases with Honeywell ADIRU
00016880.0070001
Criteria: P3510, P3790, P4087, P4419, P4425, P6125, P6985, P7397, P9333, SA
Applicable to: ALL
Impacted DU: NONE
DU date
25 APR 13
25 NOV 15
(1) Evolution code : N=New, R=Revised, E=Effectivity
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22 MAR 17
LIMITATIONS
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
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22 MAR 17
LIMITATIONS
INTRODUCTION
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LIMITATIONS
INTRODUCTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Introduction...............................................................................................................................................................A
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LIMITATIONS
INTRODUCTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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LIMITATIONS
INTRODUCTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
INTRODUCTION
Ident.: LIM-INT-00019839.0001001 / 04 SEP 17
Applicable to: ALL
This FCOM chapter contains operational limitations, related to the aircraft and associated systems.
All references to airspeed, Mach and altitude relate to indicated airspeed, indicated Mach, and
pressure altitude, unless otherwise noted.
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05 SEP 17
LIMITATIONS
INTRODUCTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
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LIMITATIONS
AIRCRAFT GENERAL
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LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
LIM-AG-F_CTL Flight Maneuvering Load Acceleration Limits
Flight Maneuvering Load Acceleration Limits......................................................................................................... A
LIM-AG-OPS Operational Parameters
Environmental Envelope.......................................................................................................................................... A
Airport Operations and Wind Limitations.................................................................................................................B
LIM-AG-SPD Speeds
Cockpit Window Open Maximum Speed.................................................................................................................A
Maximum Flaps/Slats Speeds................................................................................................................................. B
Maximum Operating Speed VMO/MMO................................................................................................................. C
Maximum Speeds with the Landing Gear Extended.............................................................................................. D
Maximum Tire Speed.............................................................................................................................................. E
Minimum Control Speeds........................................................................................................................................ F
Taxi Speed.............................................................................................................................................................. G
Wipers Maximum Operating Speed........................................................................................................................ H
LIM-AG-WGHT Weights
Weight Limitations....................................................................................................................................................A
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LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT MANEUVERING LOAD ACCELERATION LIMITS
FLIGHT MANEUVERING LOAD ACCELERATION LIMITS
Ident.: LIM-AG-F_CTL-00020793.0001001 / 17 MAR 17
Applicable to: ALL
Clean configuration...........................................................................................................-1 g to +2.5 g
Other configurations............................................................................................................. 0 g to +2 g
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A
LIM-AG-F_CTL P 1/2
22 MAR 17
LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT MANEUVERING LOAD ACCELERATION LIMITS
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LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
OPERATIONAL PARAMETERS
FLIGHT CREW
OPERATING MANUAL
ENVIRONMENTAL ENVELOPE
Ident.: LIM-AG-OPS-00021818.0043001 / 19 JUL 17
Applicable to: ALL
AIRPORT OPERATIONS AND WIND LIMITATIONS
Applicable to: ALL
Ident.: LIM-AG-OPS-ARPT_WIND-00020145.0001001 / 17 MAR 17
RUNWAY SLOPE
Runway slope (mean)................................................................................................................ ±2 %
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LIM-AG-OPS P 1/4
05 SEP 17
LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
OPERATIONAL PARAMETERS
FLIGHT CREW
OPERATING MANUAL
Ident.: LIM-AG-OPS-ARPT_WIND-00020135.0009001 / 17 MAR 17
RUNWAY ALTITUDE
Runway altitude....................................................................................................................14 100 ft
Ident.: LIM-AG-OPS-ARPT_WIND-00020146.0002001 / 17 MAR 17
NOMINAL RUNWAY WIDTH
Nominal runway width................................................................................................................ 45 m
Minimal runway width................................................................................................................. 30 m
Ident.: LIM-AG-OPS-ARPT_WIND-00020148.0001001 / 17 MAR 17
WIND FOR TAKEOFF AND LANDING
Maximum demonstrated crosswind (takeoff and landing).................................. 38 kt (gust included)
Note:
‐ The maximum demonstrated crosswind value is not an Airplane Flight Manual (AFM)
limitation : It is the maximum crosswind condition experienced during the aircraft
certification campaign.
‐ Airbus recommends that operators should not intentionally operate in crosswinds that
exceed this value.
Ident.: LIM-AG-OPS-ARPT_WIND-00020157.0003001 / 17 MAR 17
TAILWIND TAKEOFF
Maximum tailwind for takeoff......................................................................................................15 kt
Ident.: LIM-AG-OPS-ARPT_WIND-00020159.0003001 / 21 MAR 17
TAILWIND LANDING
Maximum tailwind for landing ................................................................................................... 15 kt
Note:
For maximum tailwind for automatic landing and rollout, Refer to LIM-AFS-20 Maximum
Wind Conditions for ILS/MLS (If Installed) CAT II or CAT III and for GLS (If Installed) CAT
I.
Ident.: LIM-AG-OPS-ARPT_WIND-00020168.0002001 / 22 MAR 17
Note:
For landing with a tailwind greater than 10 kt, use FLAPS FULL only.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
LIM-AG-OPS P 2/4
05 SEP 17
LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
OPERATIONAL PARAMETERS
FLIGHT CREW
OPERATING MANUAL
Ident.: LIM-AG-OPS-ARPT_WIND-00020166.0001001 / 04 JUL 17
PASSENGER AND CARGO DOORS OPERATION
The following are the wind limitations for passenger and cargo doors operation:
‐ The maximum wind for passenger door operation is 65 kt
‐ The maximum wind for FWD and AFT cargo door operation is 40 kt (or 50 kt, if the aircraft nose
is into the wind, or if the FWD and AFT cargo doors are on the leeward side)
‐ The FWD and AFT cargo doors must be closed before the wind speed exceeds 65 kt.
Ident.: LIM-AG-OPS-ARPT_WIND-00020046.0003001 / 17 MAR 17
MAXIMUM RECOMMENDED CROSSWIND ON WET AND CONTAMINATED RUNWAYS
Runway Surface Conditions
Runway State or / and Runway Contaminant
Damp
Wet
Up to 3 mm (1/8'') of water
Slush
Up to 3 mm (1/8'')
Dry snow
Up to 3 mm (1/8'')
Wet snow
Up to 3 mm (1/8'')
Frost
Compacted snow
OAT at or below -15 °C
Dry snow
More than 3 mm (1/8''), up to 100 mm (4'')
Wet snow
More than 3 mm (1/8''), up to 30 mm (6/5'')
Compacted snow
OAT above -15 °C
Dry snow over compacted snow
Wet snow over compacted snow
Slippery when wet
Water
More than 3 mm (1/8''), up to 12.7 mm (1/2'')
Slush
More than 3 mm (1/8''), up to 12.7 mm (1/2'')
Ice (cold & dry)
(1)
ESF: Estimated Surface Friction
(2)
PIREP: Pilot Report of Braking Action
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
ESF(1) or
PIREP(2)
Maximum Crosswind for Maximum Crosswind for
Takeoff (Gust included) Landing (Gust included)
Good
38 kt
38 kt
Good to
Medium
29 kt
29 kt
Medium
25 kt
25 kt
Medium
to Poor
20 kt
20 kt
Poor
15 kt
15 kt
←B→
LIM-AG-OPS P 3/4
05 SEP 17
LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
OPERATIONAL PARAMETERS
The maximum crosswind values given in the above table are recommended values
based on computations.
Ident.: LIM-AG-OPS-ARPT_WIND-00014451.0001001 / 22 MAY 12
TAKEOFF LIMITATIONS ON CONTAMINATED RUNWAYS
Takeoff is not recommended on the following runway conditions:
‐ Wet ice
‐ Water on top of Compacted Snow
‐ Dry Snow or Wet Snow over Ice
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FCOM
←B
LIM-AG-OPS P 4/4
05 SEP 17
LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
SPEEDS
FLIGHT CREW
OPERATING MANUAL
COCKPIT WINDOW OPEN MAXIMUM SPEED
Ident.: LIM-AG-SPD-00001904.0001001 / 17 MAR 17
Applicable to: ALL
Maximum speed............................................................................................................................200 kt
MAXIMUM FLAPS/SLATS SPEEDS
Ident.: LIM-AG-SPD-00020087.0001001 / 17 MAR 17
Applicable to: ALL
Flaps Lever
Position
0
1
2
3
FULL
Configuration on
Slat/Flap Display
1
1+F
2
3
FULL
Max Speed
Flight Phase
VMO /MMO
230 kt
215 kt
200 kt
185 kt
177 kt
CRUISE
HOLDING
TAKEOFF
TAKEOFF/APPROACH
TAKEOFF/APPROACH/LANDING
LANDING
MAXIMUM OPERATING SPEED VMO/MMO
Ident.: LIM-AG-SPD-00019991.0002001 / 17 MAR 17
Applicable to: ALL
VMO.............................................................................................................................................. 350 kt
MMO............................................................................................................................................ M 0.82
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FCOM
A to C →
LIM-AG-SPD P 1/4
22 MAR 17
LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
SPEEDS
FLIGHT CREW
OPERATING MANUAL
MAXIMUM SPEEDS WITH THE LANDING GEAR EXTENDED
Ident.: LIM-AG-SPD-00001901.0001001 / 17 MAR 17
Applicable to: ALL
Maximum speed with the landing gear extended (VLE)..................................................280 kt /M 0.67
Maximum speed at which the landing gear may be extended (VLO extension) ............. 250 kt /M 0.60
Maximum speed at which the landing gear may be retracted (VLO retraction) .............. 220 kt /M 0.54
MAXIMUM TIRE SPEED
Ident.: LIM-AG-SPD-00001902.0001001 / 17 MAR 17
Applicable to: ALL
Maximum ground speed............................................................................................................... 195 kt
MINIMUM CONTROL SPEEDS
Ident.: LIM-AG-SPD-00020161.0015001 / 17 MAR 17
Applicable to: ALL
MINIMUM CONTROL SPEED FOR LANDING (VMCL)
VMCL........................................................................................................................................ 113 kt
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to F →
LIM-AG-SPD P 2/4
22 MAR 17
LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
SPEEDS
FLIGHT CREW
OPERATING MANUAL
MINIMUM CONTROL SPEEDS IN THE AIR (VMCA ) AND ON THE GROUND (VMCG)
Altitude
(ft)
-2 000
0
2 000
4 000
6 000
8 000
10 000
12 000
14 100
VMCA
(kt IAS)
112
110
108
108
107
104
100
97
94
CONF 1 + F
112
111
109
109
108
105
101
99
95
VMCG (kt IAS)
CONF 2
110
109
107
107
106
103
99
97
93
CONF 3
109
109
107
107
105
103
99
96
93
When the Thrust Bump is used, consider the following VMCA / VMCG:
Altitude
(ft)
-2 000
0
2 000
4 000
6 000
8 000
10 000
12 000
14 100
VMCA
(kt IAS)
111
110
108
108
108
105
102
99
95
CONF 1 + F
112
111
109
109
109
106
103
100
97
VMCG (kt IAS)
CONF 2
110
109
107
107
107
104
101
98
95
CONF 3
109
109
107
107
106
104
101
97
95
TAXI SPEED
Ident.: LIM-AG-SPD-00019838.0001001 / 17 MAR 17
Applicable to: ALL
When the taxi weight is higher than 76 000 kg (167 550 lb):
CAUTION
Do not exceed a taxi speed of 20 kt during a turn.
WIPERS MAXIMUM OPERATING SPEED
Ident.: LIM-AG-SPD-00001903.0001001 / 17 MAR 17
Applicable to: ALL
Maximum speed............................................................................................................................230 kt
L2
Note:
This limitation is applicable when the wipers are sweeping. It is not applicable if the wipers
are not sweeping for any reasons.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← F to H
LIM-AG-SPD P 3/4
22 MAR 17
LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
SPEEDS
FLIGHT CREW
OPERATING MANUAL
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LIM-AG-SPD P 4/4
22 MAR 17
LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
WEIGHTS
FLIGHT CREW
OPERATING MANUAL
WEIGHT LIMITATIONS
Ident.: LIM-AG-WGHT-00001893.0268001 / 18 MAR 11
Applicable to: ALL
Maximum taxi weight......................................................................................... 77 400 kg (170 637 lb)
Maximum takeoff weight (brake release)........................................................... 77 000 kg (169 755 lb)
Maximum landing weight................................................................................... 66 000 kg (145 505 lb)
Maximum zero fuel weight.................................................................................62 500 kg (137 788 lb)
Minimum weight...................................................................................................37 230 kg (82 079 lb)
In exceptional cases (in flight turn back or diversion), an immediate landing at weight above
maximum landing weight is permitted, provided the pilot follows the overweight landing procedure.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
LIM-AG-WGHT P 1/2
22 MAR 17
LIMITATIONS
AIRCRAFT GENERAL
A318/A319/A320/A321
WEIGHTS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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FCOM
LIM-AG-WGHT P 2/2
22 MAR 17
LIMITATIONS
AIR BLEED/COND/PRESS/VENT
Intentionally left blank
LIMITATIONS
AIR BLEED/COND/PRESS/VENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
General.....................................................................................................................................................................A
APU Bleed Use with HP Air Start Unit................................................................................................................... B
Avionics Ventilation..................................................................................................................................................C
Cabin Pressure........................................................................................................................................................ D
Packs Use with LP Air Conditioning Unit................................................................................................................E
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
LIM-AIR-PLP-TOC P 1/2
22 MAR 17
LIMITATIONS
AIR BLEED/COND/PRESS/VENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
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FCOM
LIM-AIR-PLP-TOC P 2/2
22 MAR 17
LIMITATIONS
AIR BLEED/COND/PRESS/VENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: LIM-AIR-00020807.0001001 / 17 MAR 17
Applicable to: ALL
With passengers on board, it is not recommended to exceed 20 min without air conditioning supply.
The lack of fresh air supply will significantly reduce the cabin’s air quality.
APU BLEED USE WITH HP AIR START UNIT
Ident.: LIM-AIR-00020084.0001001 / 17 MAR 17
Applicable to: ALL
The flight crew must not use bleed air from the APU BLEED and from the HP Air Start Unit at the
same time, to prevent any adverse effect on the Bleed Air System.
AVIONICS VENTILATION
Ident.: LIM-AIR-00020086.0001001 / 17 MAR 17
Applicable to: ALL
During ground operations and depending on the Outside Air Temperature (OAT), the flight crew must
limit the time that the aircraft electric power supply is used, in normal avionics ventilation system
configuration, as follows:
OAT ≤ 49 °C
49 °C < OAT ≤ 55 °C
55 °C < OAT ≤ 60 °C
60 °C < OAT ≤ 64 °C
No limitation
2h
1h
0.5 h
CABIN PRESSURE
Ident.: LIM-AIR-00020085.0003001 / 17 MAR 17
Applicable to: ALL
Maximum positive differential pressure...................................................................................... 9.0 PSI
Maximum negative differential pressure....................................................................................-1.0 PSI
Safety relief valve setting........................................................................................................... 8.6 PSI
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to D →
LIM-AIR P 1/2
22 MAR 17
LIMITATIONS
AIR BLEED/COND/PRESS/VENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
Maximum differential pressure (Δp) and safety valve setting tolerance = ± 7 hPa (0.1 PSI).
PACKS USE WITH LP AIR CONDITIONING UNIT
Ident.: LIM-AIR-00020083.0001001 / 17 MAR 17
Applicable to: ALL
The flight crew must not use conditioned air from the packs and from the LP Air Conditioning Unit at
the same time, to prevent any adverse effect on the Air Conditioning system.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E
LIM-AIR P 2/2
22 MAR 17
LIMITATIONS
AUTO FLIGHT SYSTEM
Intentionally left blank
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
LIM-AFS-10 General
Autopilot Function.................................................................................................................................................... A
Flight Management Function................................................................................................................................... B
Use of NAV Mode................................................................................................................................................... C
Use of FLS .....................................................................................................................................................D
Navigation Database Validation...............................................................................................................................E
LIM-AFS-20 Automatic Approach, Landing and Rollout
ILS Category II.........................................................................................................................................................A
Special Authorization CAT II (SA CAT II)............................................................................................................... B
Other than Standard CAT II (OTS CAT II)............................................................................................................. C
ILS Category III Fail Passive (Single).....................................................................................................................D
ILS Category III Fail Operational (Dual)..................................................................................................................E
Engine-Out............................................................................................................................................................... F
Maximum Wind Conditions for ILS/MLS CAT II or CAT III and for GLS CAT I..................................... G
Automatic Landing................................................................................................................................................... H
Automatic Landing in Johannesburg........................................................................................................................ I
Autoland Databases with Honeywell ADIRU........................................................................................................... J
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FCOM
LIM-AFS-PLP-TOC P 1/2
05 SEP 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
LIM-AFS-PLP-TOC P 2/2
05 SEP 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
AUTOPILOT FUNCTION
Applicable to: ALL
Ident.: LIM-AFS-10-10-00019567.0001001 / 17 MAR 17
The autopilot can be used with the following minimum values:
Ident.: LIM-AFS-10-10-00019753.0001001 / 17 MAR 17
At takeoff
100 ft AGL or 5 s after liftoff
Ident.: LIM-AFS-10-10-00019568.0001001 / 03 AUG 17
In non-precision approach using F-LOC or F-G/S (FLS
200 ft AGL
function)
In non-precision approach using FINAL APP , NAV FPA , NAV
250 ft AGL
V/S , TRK FPA , HDG V/S , LOC V/S , LOC FPA
Ident.: LIM-AFS-10-10-00019746.0005001 / 09 JUN 17
In circling approach
500 ft AGL for aircraft category C (600 ft AGL for
aircraft category D).
Ident.: LIM-AFS-10-10-00019747.0001001 / 17 MAR 17
ILS /MLS approach when CAT1 is displayed on the FMA
GLS approach when AUTOLAND is not displayed on the FMA
ILS /MLS approach when CAT2 or CAT3 (single or dual) is
displayed on the FMA
Ident.: LIM-AFS-10-10-00019750.0001001 / 17 MAR 17
After a manual go-around
160 ft AGL
160 ft AGL
0 ft AGL if autoland
100 ft AGL
Ident.: LIM-AFS-10-10-00019751.0001001 / 06 JUL 17
In all other phases
500 ft AGL
The AP or FD in OP DES or DES mode can be used in approach. However, its use is only permitted if the FCU selected
altitude is set to, or above, the higher of the two: MDA /MDH or 500 ft AGL.
FLIGHT MANAGEMENT FUNCTION
Applicable to: ALL
Ident.: LIM-AFS-10-20-00020069.0001001 / 17 MAR 17
FMGS lateral and vertical navigation is certified for:
‐ After takeoff, en route, and terminal area operations
‐ Navigation within RNAV /RNP airspace
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B →
LIM-AFS-10 P 1/6
05 SEP 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
‐ Instrument approach procedures (except ILS , LOC , LOC B/C , LDA , SDF, GLS , MLS
and FLS final approaches)
‐ Missed approach procedures.
The FLS function is certified for:
‐ RNAV , RNAV (GNSS ), GPS , VOR , VOR /DME , NDB , NDB /DME instrument approach
procedures, using FMS navigation for lateral and vertical navigation
‐ LOC , ILS (GS out), or LOC B/C instrument approaches, using FMS navigation for vertical
navigation, associated with LOC or LOC B/C for lateral navigation.
Approval of the FMGS is based on the assumption that the navigation database is validated for
intended use.
Obstacle clearance and adherence to airspace constraints remains a flight crew responsibility.
Fuel, time predictions/performance information is provided for advisory purposes only.
TAKEOFF IN GPS PRIMARY
For certain airports, where the difference between the local coordinate system and WGS 84
(geodesic standard used by GPS , FMS) is not negligible, a map shift may occur after takeoff.
The flight crew must deselect the GPS for takeoff from these airports, until a safe altitude is
reached.
Ident.: LIM-AFS-10-20-00020070.0002001 / 17 MAR 17
NAVIGATION PERFORMANCE
The navigation accuracy depends on:
‐ IRS drift, or
‐ One of the following:
• Radio navaid availability, or
• Elapsed time since last computation of radio navaid position.
RNP accuracy with GPS PRIMARY is:
With AP ON (1)
(1)
With AP OFF
and FD ON (1)
With AP OFF
and FD OFF
0.51 NM
0.3 NM with F-LOC
deviation
Not authorized without
F-LOC deviation
En route
In terminal area
0.5 NM
0.51 NM
In approach
0.3 NM
0.3 NM
1 NM
1 NM
1.1 NM
‐ In NAV (all phases), or
‐ In F-LOC (approach phase)
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FCOM
←B→
LIM-AFS-10 P 2/6
05 SEP 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Ident.: LIM-AFS-10-20-00020389.0001001 / 17 MAR 17
DEGRADED SITUATION
If GPS PRIMARY LOST is displayed on the PFD , the navigation accuracy remains sufficient
for RNP operations provided that, the RNP value is checked or entered on the MCDU and HIGH
ACCURACY is displayed.
USE OF NAV MODE
Applicable to: ALL
Ident.: LIM-AFS-10-30-00020334.0001001 / 17 MAR 17
AFTER TAKEOFF
NAV mode may be used after takeoff provided that:
‐ GPS PRIMARY is available, or
‐ The flight crew checked the FMGS takeoff updating.
Ident.: LIM-AFS-10-30-00020335.0001001 / 17 MAR 17
IN TERMINAL AREA
NAV mode may be used in terminal area provided that:
‐ GPS PRIMARY is available, or
‐ the appropriate RNP is checked or entered on the MCDU, and HIGH accuracy is displayed, or
‐ FMS navigation is crosschecked with navaid raw data.
Ident.: LIM-AFS-10-30-00020336.0001001 / 17 MAR 17
APPROACH BASED ON RADIO NAVAIDS
A navaids approach may be performed in NAV , APP NAV or FINAL APP , with AP or FD
engaged, provided that:
‐ If GPS PRIMARY is available, the reference navaid may be unserviceable, or the airborne
radio equipment may be inoperative, or not installed, provided that an operational approval is
obtained
‐ If GPS PRIMARY is not available, the reference navaid and the corresponding airborne radio
equipment must be serviceable, tuned and monitored during the approach.
Note:
FLS is the recommended managed lateral and vertical guidance mode for radio
navaids approach.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C →
LIM-AFS-10 P 3/6
05 SEP 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Ident.: LIM-AFS-10-30-00020337.0001001 / 17 MAR 17
RNAV APPROACH
An RNAV (RNP ) approach may be performed, with GPS PRIMARY not available, only if the radio
navaid coverage supports the RNP value and HIGH accuracy is displayed on the MCDU with the
specified RNP, and an operational approval is obtained.
An RNAV (GNSS) approach may be performed provided that GPS PRIMARY is available.
Refer to Guidance Modes per Approach Types
Note:
FLS is the recommended managed lateral and vertical guidance mode for RNAV
approach.
USE OF FLS
Ident.: LIM-AFS-10-00020808.0001001 / 17 MAR 17
Applicable to: ALL
APPROACH BASED ON RADIO NAVAIDS
A navaids approach may be flown with the FLS provided that:
‐ F-APP capability is displayed on FMA
In this case, the reference navaids may be unserviceable, or the airborne radio equipment may
be inoperative, or not installed, provided that an operational approval is obtained.
‐ F-APP + RAW capability is displayed on FMA.
In this case, the reference navaids and the corresponding airborne radio equipment must be
serviceable, tuned and monitored during the approach.
An ILS (G/S out), LOC , or LOC -B/C approach may be flown with the lateral LOC (LOC -B/C )
mode and with the F-G/S mode of FLS function provided that:
‐ F-APP capability is displayed on FMA
In this case, the reference navaids may be unserviceable, or the airborne radio equipment may
be inoperative, or not installed, provided that an operational approval is obtained.
‐ F-APP + RAW capability is displayed on FMA.
In this case, the reference navaids and the corresponding airborne radio equipment must be
serviceable, tuned and monitored during the approach.
RNAV (GNSS) APPROACH
An RNAV (GNSS ) approach with LNAV minimum may be flown with the FLS provided that the
F-APP capability is displayed on FMA.
An RNAV (GNSS )approach with LNAV /VNAV minimum must be flown with the FLS provided that
the F-APP capability is displayed on FMA.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
LIM-AFS-10 P 4/6
05 SEP 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
NAVIGATION DATABASE VALIDATION
Applicable to: ALL
Ident.: LIM-AFS-10-40-00021656.0002001 / 08 AUG 17
RNAV (GNSS ) APPROACHES AND APPROACHES BASED ON VOR /NDB
To fly an approach in lateral managed mode or lateral and vertical managed mode, the approach
stored in the Navigation database must be either:
‐ Produced by an approved supplier compliant with ED76/DO200A requirements, or
‐ Validated and approved by the Operator.
Note:
RNAV (GNSS ) approaches lateral trajectories are geometrically based on waypoints
coordinates. Thus, validating waypoints coordinate ensure no coding error on the
approach and correct lateral trajectory. Observed lateral track degree of difference
between MCDU F-PLN page display and charts may come from inconsistency between
FMS MagVar and charted MagVar, which has no effect on lateral trajectory.
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FCOM
E
LIM-AFS-10 P 5/6
05 SEP 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
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LIM-AFS-10 P 6/6
05 SEP 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
AUTOMATIC APPROACH, LANDING AND ROLLOUT
FLIGHT CREW
OPERATING MANUAL
ILS CATEGORY II
Ident.: LIM-AFS-20-00020136.0001001 / 17 MAR 17
Applicable to: ALL
Minimum decision height...................................................................................................... 100 ft AGL
At least one autopilot must be engaged in APPR mode, and CAT 2 or CAT 3 SINGLE or CAT 3
DUAL must be displayed on the FMA.
For manual landing, AP should be disconnected no later than 80 ft AGL.
SPECIAL AUTHORIZATION CAT II (SA CAT II)
Ident.: LIM-AFS-20-00020138.0001001 / 17 MAR 17
Applicable to: ALL
Minimum decision height...................................................................................................... 100 ft AGL
At least one autopilot must be engaged in APPR mode, and CAT 2 or CAT 3 SINGLE or CAT 3
DUAL must be displayed on the FMA.
With HUD , the flight crew must use the HUD to monitor the approach and perform an automatic
landing or a manual landing. If the flight crew performs an automatic approach without automatic
landing, the autopilot must be disengaged no later than at 80 ft AGL.
Without HUD, the flight crew must perform an automatic landing.
OTHER THAN STANDARD CAT II (OTS CAT II)
Ident.: LIM-AFS-20-00020139.0001001 / 17 MAR 17
Applicable to: ALL
Minimum decision height...................................................................................................... 100 ft AGL
At least one autopilot must be engaged in APPR mode, and CAT 2 or CAT 3 SINGLE or CAT 3
DUAL must be displayed on the FMA.
With HUD , the flight crew must use the HUD to monitor the approach and perform an automatic
landing or a manual landing. If the flight crew performs an automatic approach without automatic
landing, the autopilot must be disengaged no later than at 80 ft AGL.
Without HUD, the flight crew must perform an automatic landing.
ILS CATEGORY III FAIL PASSIVE (SINGLE)
Ident.: LIM-AFS-20-00020140.0001001 / 17 MAR 17
Applicable to: ALL
Minimum decision height........................................................................................................ 50 ft AGL
A/THR must be used in selected or managed speed.
At least one autopilot must be engaged in APPR mode, and CAT 3 SINGLE or CAT 3 DUAL must be
displayed on the FMA.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to D
LIM-AFS-20 P 1/4
22 MAR 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AUTOMATIC APPROACH, LANDING AND ROLLOUT
ILS CATEGORY III FAIL OPERATIONAL (DUAL)
Ident.: LIM-AFS-20-00020141.0008001 / 17 MAR 17
Applicable to: ALL
Alert height............................................................................................................................ 100 ft AGL
A/THR must be used in selected or managed speed.
Both autopilots must be engaged in APPR mode, and CAT 3 DUAL must be displayed on the FMA.
CAT III with DH:
Minimum Decision Height.................................................................................................20 ft AGL
CAT III without DH:
Minimum Runway Visual Range..............................................................................................75 m
ENGINE-OUT
Ident.: LIM-AFS-20-00020142.0001001 / 17 MAR 17
Applicable to: ALL
CAT II and CAT III fail passive autoland are only approved in configuration FULL, and if engine-out
procedures are completed before reaching 1 000 ft in approach.
MAXIMUM WIND CONDITIONS FOR ILS/MLS CAT II OR CAT III AND FOR GLS CAT I
Ident.: LIM-AFS-20-00020144.0001001 / 17 MAR 17
Applicable to: ALL
Headwind :
Tailwind :
Crosswind :
Note:
30 kt
10 kt
20 kt
Wind limitation is based on the surface wind reported by ATC . If the wind displayed on
the ND exceeds the above-noted autoland limitations, but the tower reports a surface wind
within the limitations, then the autopilot can remain engaged. If the tower reports a surface
wind beyond limitations, only CAT I automatic approach without autoland can be performed.
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LIM-AFS-20 P 2/4
22 MAR 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
AUTOMATIC APPROACH, LANDING AND ROLLOUT
FLIGHT CREW
OPERATING MANUAL
AUTOMATIC LANDING
Applicable to: ALL
Ident.: LIM-AFS-20-10-00020149.0001001 / 17 MAR 17
ILS /MLS CAT II and CAT III autoland and GLS CAT I autoland are approved in CONF 3 and CONF FULL.
Ident.: LIM-AFS-20-10-00020150.0001001 / 17 MAR 17
Automatic landing is demonstrated:
- With CAT II and CAT III ILS /MLS beam and CAT I GLS beam.
Ident.: LIM-AFS-20-10-00020151.0001001 / 17 MAR 17
- With a glide slope angle between -2.5 ° and -3.15 °
Ident.: LIM-AFS-20-10-00020152.0003001 / 17 MAR 17
- With an airport elevation at or below 9 200 ft
Ident.: LIM-AFS-20-10-00020155.0001001 / 17 MAR 17
Automatic landing is not allowed below -1 000 ft pressure altitude.
Ident.: LIM-AFS-20-10-00020156.0001001 / 17 MAR 17
Automatic rollout performance is approved on dry and wet runways, but performance on snow-covered or icy runways was
not demonstrated.
Ident.: LIM-AFS-20-10-00020158.0001001 / 17 MAR 17
Automatic landing system performance is demonstrated with CAT II or CAT III ILS /MLS airport installation. However,
automatic landing in CAT I or better weather conditions is possible on CAT I ground installations or on CAT II/III ground
installations when ILS/MLS sensitive areas are not protected, if the following precautions are taken:
‐ The airline checked that the ILS /MLS beam quality, and the effect of the terrain profile before the runway have no
adverse effect on AP /FD guidance. Particularly, the effect of terrain profile within 300 m before the runway threshold
must be evaluated
‐ The flight crew is aware that LOC or G/S beam fluctuations, independent of the aircraft system, may occur. The PF is
prepared to immediately disconnect the autopilot, and to take the appropriate action, should not satisfactory guidance
occur
‐ At least CAT2 capability is displayed on the FMA and the flight crew uses CAT II/III procedures
‐ Visual references are obtained at an altitude appropriate for the CAT I approach. If not, a go-around must be
performed.
AUTOMATIC LANDING IN JOHANNESBURG
Ident.: TDU / LIM-AFS-20-00013685.0001001 / 25 APR 13
Applicable to: ALL
Impacted DU: NONE
Automatic landing is not permitted on Johannesburg 03R/21L runways.
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LIM-AFS-20 P 3/4
22 MAR 17
LIMITATIONS
AUTO FLIGHT SYSTEM
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
AUTOMATIC APPROACH, LANDING AND ROLLOUT
AUTOLAND DATABASES WITH HONEYWELL ADIRU
Ident.: TDU / LIM-AFS-20-00016880.0070001 / 25 NOV 15
Applicable to: ALL
Impacted DU: NONE
The below table provides for each concerned airport, the dates when the following limitations begin:
‐ AUTOLAND is not allowed
‐ ROLLOUT is not allowed.
CAT II approaches without AUTOLAND are still allowed.
Airport code
PAFA
PANC
Note:
Airport Location
FAIRBANKS INTL AK USA
ANCHORAGE INTL AK USA
Month/Year
September 2016
June 2018
This limitation is applicable until end of 2020. From 2021, without a revision of this
limitation, AUTOLAND and ROLLOUT will not be allowed on any airport.
The above limitations do not apply if three new ADIRU with updated magnetic variation tables are
installed and Operators ensure previous standards are not installed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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22 MAR 17
LIMITATIONS
AUXILIARY POWER UNIT
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LIMITATIONS
AUXILIARY POWER UNIT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
General.....................................................................................................................................................................A
APU Start/Shutdown during Refueling/Defueling.................................................................................................... B
Operational Envelope.............................................................................................................................................. C
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LIM-APU-PLP-TOC P 1/2
05 SEP 17
LIMITATIONS
AUXILIARY POWER UNIT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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LIMITATIONS
AUXILIARY POWER UNIT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL
Applicable to: ALL
Ident.: LIM-APU-10-00020088.0001001 / 17 MAR 17
APU START
After three consecutive APU start attempts, the flight crew must wait 60 min before a new start
attempt.
Ident.: LIM-APU-10-00020089.0001001 / 17 MAR 17
ROTOR SPEED
Maximum N speed................................................................................................................... 107 %
Ident.: LIM-APU-10-00020090.0002001 / 17 MAR 17
EGT
Maximum EGT for APU start (below 25 000 ft)...................................................................... 900 °C
Maximum EGT for APU start (above 25 000 ft)......................................................................982 °C
Maximum EGT for APU running (with 5 s confirmation for shutdown).................................... 682 °C
Maximum EGT for APU running (for immediate shutdown).................................... 700 °C to 742 °C
APU START/SHUTDOWN DURING REFUELING/DEFUELING
Ident.: LIM-APU-00020091.0001001 / 17 MAR 17
Applicable to: ALL
During refuel/defuel procedures, APU starts or shutdown are permitted with the following restrictions:
‐ If the APU failed to start or following an automatic APU shutdown, do not start the APU
‐ If a fuel spill occurs, perform a normal APU shutdown.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
LIM-APU P 1/2
05 SEP 17
LIMITATIONS
AUXILIARY POWER UNIT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OPERATIONAL ENVELOPE
Applicable to: ALL
Ident.: LIM-APU-20-00019832.0026001 / 17 MAR 17
Ident.: LIM-APU-20-00021771.0001001 / 04 JUL 17
APU BLEED
Max altitude to assist engine start....................................................................................... 20 000 ft
Max altitude for air conditioning and pressurization (single pack operation)........................ 20 000 ft
Max altitude for air conditioning and pressurization (dual pack operation)...........................15 000 ft
Use of APU bleed air for wing anti-ice is not permitted.
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COMMUNICATION
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COMMUNICATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
GSM Onboard ................................................................................................................................................ A
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COMMUNICATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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LIMITATIONS
COMMUNICATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GSM ONBOARD
Ident.: LIM-COM-00020293.0001001 / 17 MAR 17
Applicable to: ALL
The use of mobile phones is prohibited in the toilets and the cockpit.
It is prohibited to use the GSM Onboard System:
‐ Below 3 000 m AGL (approximately 10 000 ft)
‐ In some geographical areas (refer to the “Regional Operation Data for the Onboard Mobile
Telephony System” document for the identification of these geographical areas).
Note:
The GSM Onboard System is able to identify the above-mentioned flight conditions. If the
system identifies any of these conditions, it automatically turns off.
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LIM-COM P 1/2
19 JUN 17
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COMMUNICATION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
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19 JUN 17
LIMITATIONS
ENGINES
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ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Thrust Setting/EGT Limits....................................................................................................................................... A
Shaft Speeds........................................................................................................................................................... B
Oil.............................................................................................................................................................................C
Starter...................................................................................................................................................................... D
Reverse Thrust........................................................................................................................................................ E
Reduced Thrust Takeoff.......................................................................................................................................... F
Soft Go-Around .............................................................................................................................................. G
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22 MAR 17
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ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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LIMITATIONS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
THRUST SETTING/EGT LIMITS
Ident.: LIM-ENG-00019960.0004001 / 20 MAR 17
Applicable to: ALL
Operating Conditions
All engines operative
Takeoff and Go-around
One engine inoperative
Maximum Continuous Thrust (MCT)
On ground
Starting
In flight
(1)
(1)
Time Limit
5 min
10 min
Not limited
EGT Limit
950 °C
915 °C
725 °C
Includes TOGA, FLEX, and DERATE thrust modes.
SHAFT SPEEDS
Ident.: LIM-ENG-00020355.0002001 / 20 MAR 17
Applicable to: ALL
Maximum N1 .............................................................................................................................. 104 %
Note:
The N1 limit depends on the ambient conditions and on the configuration of the engine air
bleed. These parameters may limit N1 to a value that is less than the above-mentioned N1
value (Refer to PER-THR-MTO MAXIMUM TAKEOFF).
Maximum N2 .............................................................................................................................. 105 %
OIL
Ident.: LIM-ENG-00020354.0001001 / 20 MAR 17
Applicable to: ALL
OIL TEMPERATURE
Maximum continuous temperature......................................................................................... 140 °C
Maximum transient temperature (15 min).............................................................................. 155 °C
Minimum starting temperature................................................................................................ -40 °C
Minimum temperature before takeoff...................................................................................... -10 °C
OIL QUANTITY
Minimum oil quantity................................................................. Refer to PRO-NOR-SOP-04 ECAM
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A to C →
LIM-ENG P 1/4
22 MAR 17
LIMITATIONS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OIL PRESSURE
MIN/MAX Oil Pressure (ECAM Indication)
STARTER
Ident.: LIM-ENG-00020356.0001001 / 20 MAR 17
Applicable to: ALL
‐
‐
‐
‐
A standard automatic start that includes up to three start attempts, is considered one cycle
For ground starts (automatic or manual), a 20 s pause is required between successive cycles
A 15 min cooling period is required, subsequent to four failed cycles
The starter must not be run when N2 is above 20 %.
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FCOM
← C to D
LIM-ENG P 2/4
22 MAR 17
LIMITATIONS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
REVERSE THRUST
Ident.: LIM-ENG-00020357.0002001 / 20 MAR 17
Applicable to: ALL
Selection of the reverse thrust is prohibited in flight.
Backing the aircraft with reverse thrust is not permitted.
Maximum reverse should not be used below 70 kt.
REDUCED THRUST TAKEOFF
Applicable to: ALL
Ident.: LIM-ENG-10-00020358.0020001 / 20 MAR 17
FLEX TAKEOFF
Takeoff at reduced thrust, so-called as FLEX takeoff, is permitted only if the airplane meets all
performance requirements at the takeoff weight, with the operating engines at the thrust available
for the flexible temperature (TFLEX).
Takeoff at reduced thrust is permitted with any inoperative item affecting the performance only if
the associated performance shortfall has been applied to meet the above requirements.
FLEX takeoff is not permitted on contaminated runways.
TFLEX cannot be:
‐ Higher than TMAXFLEX, equal to ISA + 70 °C.
‐ Lower than the flat temperature (TREF).
‐ Lower than the actual OAT.
Ident.: LIM-ENG-10-00020359.0001001 / 20 MAR 17
DERATED TAKEOFF
Selection of TOGA thrust is not permitted when a derated takeoff is performed, except when
requested in any abnormal or emergency procedures.
The use of reduced thrust takeoff (FLEX takeoff) is not permitted in association with derated
takeoff.
The use of derated takeoff is permitted regardless of the runway condition (dry, wet, or
contaminated).
SOFT GO-AROUND
Ident.: LIM-ENG-00020363.0001001 / 20 MAR 17
Applicable to: ALL
The use of soft go-around is prohibited with one engine inoperative.
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LIM-ENG P 3/4
22 MAR 17
LIMITATIONS
ENGINES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
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LIM-ENG P 4/4
22 MAR 17
LIMITATIONS
FLIGHT CONTROLS
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LIMITATIONS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Flight Maneuvering Load Acceleration Limits......................................................................................................... A
Maximum Altitude Flaps/Slats Extended.................................................................................................................B
Maximum Flaps/Slats Speeds.................................................................................................................................C
Use of Flight Controls............................................................................................................................................. D
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LIM-F_CTL-PLP-TOC P 1/2
22 MAR 17
LIMITATIONS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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LIM-F_CTL-PLP-TOC P 2/2
22 MAR 17
LIMITATIONS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT MANEUVERING LOAD ACCELERATION LIMITS
Ident.: LIM-F_CTL-00020162.0001001 / 17 MAR 17
Applicable to: ALL
Refer to LIM-AG-F_CTL Flight Maneuvering Load Acceleration Limits.
MAXIMUM ALTITUDE FLAPS/SLATS EXTENDED
Ident.: LIM-F_CTL-00020160.0001001 / 17 MAR 17
Applicable to: ALL
Maximum operating altitude with slats and/or flaps extended..................................................20 000 ft
MAXIMUM FLAPS/SLATS SPEEDS
Ident.: LIM-F_CTL-00020163.0001001 / 17 MAR 17
Applicable to: ALL
Refer to LIM-AG-SPD Maximum Flaps/Slats Speeds.
USE OF FLIGHT CONTROLS
Ident.: LIM-F_CTL-00020000.0001001 / 17 MAR 17
Applicable to: ALL
CAUTION
Rapid and large alternating control inputs, especially in combination with large
changes in pitch, roll or yaw (e.g. large sideslip angles) may result in structural
failures at any speed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
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LIM-F_CTL P 1/2
22 MAR 17
LIMITATIONS
FLIGHT CONTROLS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
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LIM-F_CTL P 2/2
22 MAR 17
LIMITATIONS
FUEL
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LIMITATIONS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Certified Fuel............................................................................................................................................................A
Fuel Mixability.......................................................................................................................................................... B
Fuel Temperature.................................................................................................................................................... C
Fuel Temperature Limits when JP4 and JET B Fuels are Used............................................................................ D
Maximum Allowed Fuel Imbalance..........................................................................................................................E
Minimum Fuel Quantity for Takeoff......................................................................................................................... F
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LIMITATIONS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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LIMITATIONS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CERTIFIED FUEL
Ident.: LIM-FUEL-00019707.0001001 / 17 MAR 17
Applicable to: ALL
The fuel system is certified with: JET A, JET A1, JET B, JP4, JP5, JP8, N° 3 JET, RT, and TS-1, in
accordance with engine manufacturers and fuel specifications.
FUEL MIXABILITY
Ident.: LIM-FUEL-00012852.0001001 / 03 JAN 11
Applicable to: ALL
The various types of fuel can be mixed in all proportions.
The freezing point of a fuel mixture varies, based on non-linear laws. If required, determine the fuel
freezing point of the fuel mixture.
FUEL TEMPERATURE
Ident.: LIM-FUEL-00019708.0001001 / 17 MAR 17
Applicable to: ALL
MINI
MAXI
(1)
JET A1/JP8/
N°3 JET
-43 °C
JET A
-36 °C
(1)
JP5
RT
TS-1
JET B
-42 °C
-45 °C
-45 °C
-46 °C
54 °C
JP4
49 °C
-54 °C
For JET A only, if TAT reaches -34 °C, monitor the fuel temperature on the FUEL SD page, to
ensure that it remains above -36 °C.
FUEL TEMPERATURE LIMITS WHEN JP4 AND JET B FUELS ARE USED
Ident.: LIM-FUEL-00019709.0001001 / 17 MAR 17
Applicable to: ALL
If the wing fuel temperature exceeds 30 °C at engine start, the altitude must be limited to 35 000 ft
until the center tank is empty.
If the wing fuel temperature exceeds 40 °C at engine start, the altitude must be limited to 30 000 ft
until the center tank is empty.
If the wing fuel temperature exceeds 49 °C at engine start, the altitude must be limited to 25 000 ft
until the center tank is empty.
Reason : At high altitude with high fuel temperature, the pressure supplied by the center tank
pumps becomes lower than the pressure supplied by the wing tank pumps.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to D
LIM-FUEL P 1/4
22 MAR 17
LIMITATIONS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
MAXIMUM ALLOWED FUEL IMBALANCE
Ident.: LIM-FUEL-00020435.0001001 / 17 MAR 17
Applicable to: ALL
The following tables indicate the maximum allowed wing imbalance at takeoff, in flight, and at
landing.
FUEL IMBALANCE AT TAKEOFF
INNER TANKS (OUTER TANKS BALANCED)
Tank Fuel Quantity
(Heavier Tank)
Full
3 000 kg (6 613 lb)
1 450 kg (3 196 lb)
Maximum Asymmetry
500 kg (1 102 lb)
1 050 kg (2 314 lb)
1 450 kg (3 196 lb)
The variation is linear between these values.
OUTER TANKS (INNER TANKS BALANCED)
Maximum Asymmetry
370 kg (815 lb)
FUEL IMBALANCE IN FLIGHT AND AT LANDING
INNER TANKS (OUTER TANKS BALANCED)
Tank Fuel Quantity
(Heavier Tank)
Full
4 300 kg (9 479 lb)
2 250 kg (4 960 lb)
Maximum Asymmetry
1 500 kg (3 306 lb)
1 600 kg (3 527 lb)
2 250 kg (4 960 lb)
The variation is linear between these values, and there is no limitation below 2 250 kg
(4 960 lb).
OUTER TANKS
Maximum Asymmetry
(1)
690 kg (1 521 lb)(1)
The maximum fuel imbalance in the outer wing fuel tanks (one full/one empty) is allowed provided
that:
‐ The fuel quantity of the outer and inner wing fuel tanks of one side is equal to the fuel quantity of
the outer and inner wing fuel tanks on the other side, or
‐ On the side of the lighter outer tank, the fuel quantity of the inner tank is more than the fuel
quantity of the opposite inner tank. The difference between the fuel quantity in the inner tanks
should not be more than 3 000 kg (6 613 lb).
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E→
LIM-FUEL P 2/4
22 MAR 17
LIMITATIONS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
In exceptional conditions (i.e. fuel system failure), the above-mentioned values for
maximum fuel imbalance may be exceeded without significant effect to the aircraft
handling qualities. The aircraft remains fully controllable in all flight phases.
MINIMUM FUEL QUANTITY FOR TAKEOFF
Ident.: LIM-FUEL-00019771.0001001 / 17 MAR 17
Applicable to: ALL
Minimum fuel quantity for takeoff.............................................................................1 500 kg (3 307 lb)
The ECAM alerts that are related to fuel low level in the wing tanks (FUEL WING TK LO LVL, etc.)
must not appear for takeoff.
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LIM-FUEL P 3/4
22 MAR 17
LIMITATIONS
FUEL
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
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22 MAR 17
LIMITATIONS
ICE AND RAIN PROTECTION
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LIMITATIONS
ICE AND RAIN PROTECTION
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OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Definition of Icing Conditions...................................................................................................................................A
Definition of Severe Ice Accretion...........................................................................................................................B
Definition of Thin Hoarfrost..................................................................................................................................... C
Rain Repellent ................................................................................................................................................D
Wipers Maximum Operating Speed........................................................................................................................ E
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LIMITATIONS
ICE AND RAIN PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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LIMITATIONS
ICE AND RAIN PROTECTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DEFINITION OF ICING CONDITIONS
Ident.: LIM-ICE_RAIN-00020608.0001001 / 17 MAR 17
Applicable to: ALL
‐ Icing conditions exist when the OAT (on ground or after takeoff) or the TAT (in flight) is at or below
10 °C and visible moisture in any form is present (such as clouds, fog with visibility of one nautical
mile or less, rain, snow, sleet or ice crystals).
‐ Icing conditions also exist when the OAT on the ground and for takeoff is at or below 10 °C and
operating on ramps, taxiways or runways where surface snow, standing water or slush may be
ingested by the engines, or freeze on engines, nacelles or engine sensor probes.
DEFINITION OF SEVERE ICE ACCRETION
Ident.: LIM-ICE_RAIN-00020609.0001001 / 17 MAR 17
Applicable to: ALL
Ice accretion is considered severe when the ice accumulation on the airframe reaches approximately
5 mm (0.2 in) thick or more.
DEFINITION OF THIN HOARFROST
Ident.: LIM-ICE_RAIN-00020610.0001001 / 17 MAR 17
Applicable to: ALL
Thin hoarfrost is typically a white crystalline deposit which usually develops uniformly on exposed
surfaces on cold and cloudless nights.
It is so thin that surface features (lines or markings) can be distinguished beneath it.
RAIN REPELLENT
Ident.: LIM-ICE_RAIN-00020224.0001001 / 17 MAR 17
Applicable to: ALL
The flight crew should only use the rain repellent in the case of moderate to heavy rain.
WIPERS MAXIMUM OPERATING SPEED
Ident.: LIM-ICE_RAIN-00020225.0001001 / 17 MAR 17
Applicable to: ALL
Refer to LIM-AG-SPD Wipers Maximum Operating Speed.
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LIM-ICE_RAIN P 1/2
22 MAR 17
LIMITATIONS
ICE AND RAIN PROTECTION
A318/A319/A320/A321
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OPERATING MANUAL
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LANDING GEAR
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LIMITATIONS
LANDING GEAR
A318/A319/A320/A321
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OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Braking System........................................................................................................................................................A
Brake Temperature.................................................................................................................................................. B
Maximum Speeds with the Landing Gear Extended.............................................................................................. C
Maximum Tire Speed.............................................................................................................................................. D
Nosewheel Steering (NWS).....................................................................................................................................E
Taxi with Deflated or Damaged Tires......................................................................................................................F
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LANDING GEAR
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BRAKING SYSTEM
Ident.: LIM-LG-00020233.0001001 / 17 MAR 17
Applicable to: ALL
The braking system is not designed to hold the aircraft in a stationary position when a high thrust
level is applied on at least one engine.
During ground procedures that require a thrust increase with braking, the flight crew must ensure that
the aircraft remains stationary, and must be ready to immediately retard the thrust levers to IDLE.
BRAKE TEMPERATURE
Ident.: LIM-LG-00020255.0001001 / 17 MAR 17
Applicable to: ALL
Maximum brake temperature for takeoff (brake fans off).....................................................300 °C
MAXIMUM SPEEDS WITH THE LANDING GEAR EXTENDED
Ident.: LIM-LG-00020237.0001001 / 17 MAR 17
Applicable to: ALL
Refer to LIM-AG-SPD Maximum Speeds with the Landing Gear Extended.
MAXIMUM TIRE SPEED
Ident.: LIM-LG-00020238.0001001 / 17 MAR 17
Applicable to: ALL
Refer to LIM-AG-SPD Maximum Tire Speed.
NOSEWHEEL STEERING (NWS)
Ident.: LIM-LG-00020236.0001001 / 17 MAR 17
Applicable to: ALL
For NWS angle limit, Refer to DSC-20-30 Taxiing.
Towbarless operation on the nose landing gear (towing and pushback) is approved when using the
accepted towbarless towing vehicles listed in the Airbus WISE ISI 09.11.00001, with the following
information:
Maximum NWS angle..................................................................................................................... 85 °
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LIM-LG P 1/2
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LIMITATIONS
LANDING GEAR
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FLIGHT CREW
OPERATING MANUAL
TAXI WITH DEFLATED OR DAMAGED TIRES
Ident.: LIM-LG-00020235.0001001 / 01 JUN 17
Applicable to: ALL
To vacate the runway or taxi at low speed with tire(s) deflated (not damaged), all of the following
limitations apply:
‐ If maximum one tire per gear is deflated (consider three gears)
Maximum taxi speed during turn................................................................................................. 7 kt
‐ If two tires are deflated on the same main gear (maximum one main gear)
Maximum taxi speed................................................................................................................... 3 kt
‐ For the nosewheel steering (NWS) angle
Maximum NWS angle................................................................................................................. 30 °
In addition, if tire damage is suspected, the flight crew must ask for an aircraft inspection prior to
vacate the runway or taxi. If the ground crew suspects that a tire burst may damage the landing gear,
maintenance action is due.
For more information, Refer to FCTM/PR-AEP-LG Taxi with Deflated or Damaged Tires.
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NAVIGATION
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NAVIGATION
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Inertial Reference System (IRS)..............................................................................................................................A
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INERTIAL REFERENCE SYSTEM (IRS)
Ident.: LIM-NAV-00020081.0001001 / 17 MAR 17
Applicable to: ALL
IR GROUND ALIGNMENT
Ground alignment of the IRS is possible in latitudes between 73 ° North and 73 ° South.
MAGNETIC (MAG) REFERENCE
If all ADIRUs have the same magnetic variation table:
In NAV mode, the IR will not provide valid magnetic heading and magnetic track angle:
‐ North of 73 ° North, and
‐ South of 60 ° South.
Flying at latitudes beyond these limits is prohibited.
If one ADIRU has a different magnetic variation table:
In NAV mode, the IR will not provide valid magnetic heading and magnetic track angle:
‐ North of 60 ° North, between 30 ° West and 160 ° West, and
‐ North of 73 ° North, and
‐ South of 55 ° South.
Flying at latitudes beyond these limits is prohibited.
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OXYGEN
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OXYGEN
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Minimum Flight Crew Oxygen Pressure..................................................................................................................A
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OXYGEN
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FLIGHT CREW
OPERATING MANUAL
MINIMUM FLIGHT CREW OXYGEN PRESSURE
Ident.: LIM-OXY-00020232.0004001 / 17 MAR 17
Applicable to: ALL
REF Temperature (1)
2 Crewmembers
2 Crewmembers + 1 OBS
2 Crewmembers + 2 OBS
MIN Bottle
Pressure (PSI)(2)
(1)
REF Temperature :
‐ On ground
‐ In flight
(2)
°C
°F
:
:
-10
0
10
20
14
32
50
68
716
744
771
798
874
907
940
974
1 103 1 145 1 187 1 229
30
86
826
1 007
1 270
40
50
104
122
853
880
1 040 1 073
1 312 1 354
REF Temperature = (OAT + Cockpit TEMP) / 2
REF Temperature = CAB TEMP (°C) - 10 °C, or
REF Temperature = CAB TEMP (°F) - 18 °F
Minimum Bottle Pressure to Cover:
‐ Preflight checks
‐ The use of oxygen, when only one flight crewmember is in the cockpit
‐ Unusable quantity (to ensure regulator operation with minimum pressure)
‐ Normal system leakage
‐ The most demanding case among the following:
• Protection after loss of cabin pressure, with mask regulator on NORMAL (diluted oxygen):
▪ During emergency descent for all flight crewmembers and observers for 22 min
▪ During cruise at FL 100 for two flight crewmembers for 98 min.
• Protection against smoke with 100 % oxygen for all flight crewmembers and observers during
15 min at 8 000 ft cabin altitude.
Note:
The above times that are based on the use of a sealed mask may be shorter for
bearded crew (in terms of performance, pressure, or duration).
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SURVEILLANCE
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GPWS / Predictive GPWS ............................................................................................................................. A
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OPERATING MANUAL
GPWS / PREDICTIVE GPWS
Ident.: LIM-SURV-00019775.0001001 / 17 MAR 17
Applicable to: ALL
Aircraft navigation must not be based on the use of the terrain display .
The terrain display is intended to serve as a situation awareness tool only, and may not provide the
accuracy on which to solely base terrain avoidance maneuvering.
The predictive GPWS functions should be inhibited (TERR pushbutton to OFF, on the GPWS
panel) when the aircraft position is less than 15 NM from the airfield:
‐ For operations from/to runways not incorporated in the predictive GPWS database.
‐ For specific approach procedures, which were previously identified as potentially causing false
terrain alerts.
Only aircraft with Man-made Obstacle Function can display obstacles on ND and trigger alerts,
based on a dedicated database which includes artificial obstacles worldwide.
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LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETIN
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OPERATING MANUAL
(1)
M
Identification
OEB41 issue 3
Criteria: 22-1269
Applicable to: ALL
OEB46 issue 1
Criteria: 27-1238
Applicable to: ALL
(2)
T
W
W
(3)
E
N
N
Rev. Date
Title
15 OCT 15
Erroneous Alternate Fuel Predictions Upon Modification of a
Company Route in the Alternate Flight Plan
05 NOV 13
No Engagement of Guidance Mode
(1) Evolution code : N=New, R=Revised, E=Effectivity
(2) Type of OEB: R=Red, W=White
(3) Affects ECAM: Y=Yes, N=No
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PRELIMINARY PAGES
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M
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU Title
DU identification
DU date
No Temporary Documentary Unit
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GENERAL DESCRIPTION
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GENERAL DESCRIPTION
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General Description................................................................................................................................................. A
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GENERAL DESCRIPTION
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GENERAL DESCRIPTION
Applicable to: ALL
Ident.: OEB-GEN-A-00014181.0001001 / 23 NOV 11
An Operations Engineering Bulletin (OEB) is issued to rapidly inform operators of any deviations
from initial design objectives that have a significant operational impact. An OEB provides the
operators with technical information and temporary operational procedures that address these
deviations.
Ident.: OEB-GEN-A-00014182.0001001 / 23 NOV 11
TYPE OF OEB
OEBs can either be red or white, depending on their level of priority.
‐ RED OEBs are issued to indicate that non-compliance with the recommended procedures may
have a significant impact on the safe operation of the aircraft.
‐ WHITE OEBs are issued to indicate that non-compliance with the recommended procedures
may have a significant impact on aircraft operation.
Airbus strongly recommends that all Operators rapidly apply the OEB corrective actions as soon
as they become available, particularly for red OEBs.
Ident.: OEB-GEN-A-00014183.0001001 / 23 JUN 15
OEB CONTENT AND MANAGEMENT
An OEB:
‐ Is temporary and usually focuses on one operational subject only,
‐ Is included in the OEB section of both the FCOM and QRH . The procedural part of each white
or red OEB (OEB PROC ) is provided in the OEB section of the QRH, so that the flight crew can
easily access the procedures,
‐ Remains applicable until the appropriate corrective actions are completed.
Note:
After installation of the OEB corrective modification/Service Bulletins (SB): if an
Operator reinstalls any spare equipment for which there was an associated OEB , it is
Operator’s responsibility to ensure that this OEB be applied again for the applicable
aircraft.
OEB IN THE FCOM
The content of each OEB includes:
‐ The reason for issue,
‐ Technical explanations of the deviation from the initial design objectives,
‐ The operational impact if the flight crew does not apply the OEB procedure,
Continued on the following page
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GENERAL DESCRIPTION
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OPERATING MANUAL
GENERAL DESCRIPTION (Cont'd)
‐ The conditions for applying the OEB procedures :
• ECAM warning/caution affected by the OEB,
• Cockpit effects,
• Flight phases,
• Specific event.
‐ The OEB operational procedure(s) to be applied,
‐ The corrective actions that cancel the OEB (if available),
‐ The OEB REMINDER codes, (if applicable).
OEB IN THE QRH
Each FCOM OEB has an associated “OEB PROC ” in the OEB section of the QRH, that
includes:
‐ The title of the OEB PROC,
‐ The “ECAM ENTRY" field:
This section identifies whether or not one of the possible conditions for applying the OEB
PROC is an ECAM warning/caution.
The flight crew must disregard the ECAM procedure and/or STATUS of the ECAM alerts
listed in the "ECAM ENTRY" field and must apply the QRH ’s OEB procedure instead.
‐ The OEB operational procedure(s) that the flight crew must apply.
FCOM LIST OF EFFECTIVE OEB
The List of Effective Operations Engineering Bulletins (LEOEB ) enables to review all the
Operations Engineering Bulletins (OEB s) that are applicable to the fleet. Each time an OEB is
issued or revised, the LEOEB is updated.
The FCOM LEOEB consists of:
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Continued on the following page
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OEB-GEN P 2/6
22 MAR 17
OPERATIONS ENGINEERING BULLETINS
GENERAL DESCRIPTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL DESCRIPTION (Cont'd)
The "M" field that may provide the following Evolution Code:
‐ The "N" letter indicates a new OEB, or
‐ The "R" letter indicates a revised OEB, or
‐ The "E" letter indicates an aircraft validity change on the OEB.
The "Identification" field which identifies the OEB with its identification number.
Note:
The FCOM OEB and associated QRH OEB PROC have the same OEB number
in order to be consistent. However, the issue number of the QRH OEB PROC and
the FCOM OEB may be different, because a revision of an FCOM OEB does not
necessarily result in a revision of the corresponding QRH OEB PROC, that only
provides the procedure part.
The "T" field indicates the Type of OEB:
‐ The "W" letter indicates a white OEB, or
‐ The "R" letter indicates a red OEB.
Note:
OEB s are listed by type of OEB (RED OEB s first, then WHITE OEB s), and in
numerical order for each type of OEB . This enables the flight crew to easily review the
OEBs before flight.
The "E" field indicates whether or not the OEB affects ECAM procedure(s). This enables the
flight crew to easily review the OEB s before flight particularly for Operators that use the OEB
REMINDER function:
‐ The "Y" letter indicates that the OEB affects only ECAM procedure(s),
‐ The "N" letter indicates that at least one of the procedures provided in the OEB does not
affect ECAM procedure(s).
CAUTION
When Airbus provides the Operator with the LEOEB , the information
“AFFECTS ECAM : Y” ("E" field) does not necessarily mean that (for Operators
using the OEB REMINDER function) the Operator’s maintenance personnel
has activated the OEB REMINDER codes for this OEB onboard the aircraft.
It is the Operator’s responsibility to define a suitable process for providing the
flight crew with confirmation that the OEB REMINDER codes are activated for
the ECAM alerts affected by OEBs.
The "Rev Date" field indicates the date at which the OEB content was issued/changed
The "Title" field provides the OEB title.
Continued on the following page
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OPERATIONS ENGINEERING BULLETINS
GENERAL DESCRIPTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL DESCRIPTION (Cont'd)
QRH LIST OF EFFECTIVE OEB
The List of Effective Operations Engineering Bulletins (LEOEB ) enables to review all the
Operations Engineering Bulletins (OEB s) that are applicable to the fleet. Each time an OEB is
issued or revised, the LEOEB is updated.
The QRH LEOEB consists of:
The "Identification" field which identifies the OEB with its identification and issue number.
Note:
The FCOM OEB and associated QRH OEB PROC have the same OEB number
in order to be consistent. However, the issue number of the QRH OEB PROC and
the FCOM OEB may be different, because a revision of an FCOM OEB does not
necessarily result in a revision of the corresponding QRH OEB PROC, that only
provides the procedure part.
Red OEB identification number and title are in bold font. White OEB identification number and
title are in regular font. This enables the flight crew to easily review the OEBs before flight.
Note:
OEBs are listed in numerical order regardless of the type of OEB (red or white).
The "Title" field provides the OEB title and the "ECAM Entry " part of the OEB PROC. This
enable the flight crew to easily review the OEB s before flight particularly for Operators that use
the OEB REMINDER function.
Continued on the following page
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OPERATIONS ENGINEERING BULLETINS
GENERAL DESCRIPTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL DESCRIPTION (Cont'd)
CAUTION
When Airbus provides the Operator with the LEOEB , the information
“ECAM Entry ” does not necessarily mean that (for Operators using the OEB
REMINDER function) the Operator’s maintenance personnel has activated the
OEB REMINDER codes for this OEB onboard the aircraft.
It is the Operator’s responsibility to define a suitable process for providing the
flight crew with confirmation that the OEB REMINDER codes are activated for
the ECAM alerts affected by OEBs.
A vertical bar in the margin of the QRH LEOEB identifies that the OEB is either new, revised or
has an aircraft validity change.
Ident.: OEB-GEN-A-00014184.0001001 / 23 NOV 11
REVIEW OF THE OEB
In accordance with the Standard Operating Procedures, and before each flight, the flight crew
must review all OEB s that are applicable to their aircraft. If the OEB conditions are applicable, the
flight crew must apply the operational procedure(s) that is in the QRH OEB section.
Ident.: OEB-GEN-A-00014185.0001001 / 23 NOV 11
DISTRIBUTION
OEB are distributed to all affected Operators. The Operators shall provide flight crews with the
content of the OEB without delay.
Ident.: OEB-GEN-A-00014186.0001001 / 23 JUN 15
OEB REMINDER FUNCTION
The OEB reminder function provides operational help to the flight crew by enabling them to clearly
identify on the ECAM all procedures and STATUS messages superseded by an OEB procedure.
When a situation causes an ECAM warning/caution to trigger, a message informs the flight
crew in real time that there is an OEB for the displayed ECAM warning/caution and/or STATUS,
and as a result, that the ECAM procedure and/or STATUS is changed. In this case, a specific
ECAM message informs the flight crew to refer to the QRH. For more information Refer to FCOM
DSC-31-OEB Reminder.
The OEB reminder function may not be activated for some OEB s. For example, when an OEB
procedure supersedes an ECAM procedure, under specific conditions only, the OEB reminder
function is not activated, in order to let the flight crew assess the need to apply the OEB procedure
or the ECAM procedure.
The OEB reminder function does not relieve the flight crew of their responsibility to review the
applicable OEBs during the cockpit preparation.
Continued on the following page
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OPERATIONS ENGINEERING BULLETINS
GENERAL DESCRIPTION
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL DESCRIPTION (Cont'd)
OEB REMINDER CODE
The maintenance personnel must enter specific OEB REMINDER code(s) in the FWC OEB
database in order to update the ECAM.
These OEB REMINDER codes are provided in the FCOM OEB chapter only, and are sent to the
Operator’s Flight Operations department along with the associated QRH OEB PROC . This is to
ensure that the OEB database is not updated before the OEB procedure is available in the QRH
and FCOM onboard documentation.
Good coordination between the Airline’s/Operator’s Flight Operations department and the
Airline’s/Operator’s Engineering department must be established, in order to:
‐ Ensure that the QRH OEB section is updated onboard the aircraft before the activation of the
OEB REMINDER function for a specific OEB.
‐ Rapidly send information about the OEB REMINDER codes to the Engineering department for a
rapid update of the ECAM.
‐ Provide the flight crew with confirmation that the OEB REMINDER codes are activated onboard
the aircraft for the ECAM alerts affected by OEBs.
CAUTION
As soon as the maintenance personnel has embodied the corrective action that
cancels the OEB on a specific aircraft, the Operator must ensure that:
1. Maintenance personnel has deactivated the OEB REMINDER function for
the specific OEB , before informing their Flight Operations department of the
installation of the OEB correction action.
2. The QRH OEB section onboard the aircraft is updated to remove the specific
OEB from the applicable aircraft.
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OPERATIONS
ENGINEERING BULLETINS
ERRONEOUS ALTERNATE FUEL
PREDICTIONS UPON MODIFICATION OF
A COMPANY ROUTE IN THE ALTERNATE
FLIGHT PLAN
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Erroneous Alternate Fuel Predictions Upon Modification of a Company Route in the Alternate Flight Plan........... B
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A318/A319/A320/A321
ERRONEOUS ALTERNATE FUEL PREDICTIONS UPON MODIFICATION
OF A COMPANY ROUTE IN THE ALTERNATE FLIGHT PLAN
FLIGHT CREW
OPERATING MANUAL
OEB41 Issue 3
Associated with QRH OEB Proc N°: OEB41/1.0
ERRONEOUS ALTERNATE FUEL PREDICTIONS UPON MODIFICATION
OF A COMPANY ROUTE IN THE ALTERNATE FLIGHT PLAN
Ident.: OEB-41-00013609.0001001 / 15 OCT 15
Applicable to: ALL
Approved by: Head of Airbus Flight Operations & Training Support
- This OEB covers a significant operational issue. Non-compliance with this OEB may have a
significant impact on the operations of the aircraft. The Operators shall distribute its content to all
flight crews without delay. An extract of this OEB is provided for insertion in the QRH.
- It is recommended that all Operators accelerate the incorporation of all corrective Service Bulletins
as soon as they become available.
Reason for issue:
Issue 3:
This OEB is reissued to update the "Cancelled by" section with the
name of the FMS standards cancelling the OEB. There is no technical
change.
Issue 2:
This OEB is reissued to enhance the display of the MCDU FUEL PRED
page (without technical change).
The objective is to address format standardization and enhanced
readability.
Issue 1:
This OEB replaces the A320 OEB 204
This OEB is issued to inform the operators of the following: Erroneous
alternate (ALTN ) fuel predictions are experienced when the flight crew
modifies a company route (CO RTE ) previously inserted in the alternate
Flight Plan (F-PLN).
This OEB provides an explanation and operational recommendations in
case of erroneous ALTN fuel predictions.
Applicable to:
Aircraft with Honeywell FMGC Release 1A "H2" (MOD 38778, Airbus
SB A320 22-1269 and MOD 38779, Airbus SB A320 22-1270)
Cancelled by:
FMS Honeywell standard H2C and subsequent.
The FMS standard H2C is installed by the following FMGC standards:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
OEB-41 P 1/6
24 JAN 17
OPERATIONS ENGINEERING BULLETINS
A318/A319/A320/A321
ERRONEOUS ALTERNATE FUEL PREDICTIONS UPON MODIFICATION
OF A COMPANY ROUTE IN THE ALTERNATE FLIGHT PLAN
FLIGHT CREW
OPERATING MANUAL
‐
‐
‐
‐
FMGC standard H2CC14 (MOD 157166)
FMGC standard H2CPC14 (MOD 161459)
FMGC standard H2CI14 (MOD 156957)
FMGC standard H2CPI13 (MOD 155494)
Note: The interchangeability code, given in the Illustrated Part Catalog (IPC), indicates the conditions for interchangeability
of equipment. After installation of corrective modification(s)/SB(s), if an Operator reinstalls any equipment affected by this
OEB, it is the Operator's responsibility to ensure that the recommendations given in this OEB are applied again for the
applicable aircraft.
Operations Engineering Bulletins are issued by Airbus, as the need arises, to quickly transmit
technical and procedural information. They are distributed to all FCOM holders and to others who
need advice of changes to operational information.
The information in the OEB is recommended by Airbus, but may not be approved by Airworthiness
Authorities. If the procedures contained in this OEB differ from the procedures in the AFM, the AFM
remains the reference.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
OEB-41 P 2/6
24 JAN 17
OPERATIONS ENGINEERING BULLETINS
A318/A319/A320/A321
ERRONEOUS ALTERNATE FUEL PREDICTIONS UPON MODIFICATION
OF A COMPANY ROUTE IN THE ALTERNATE FLIGHT PLAN
FLIGHT CREW
OPERATING MANUAL
M
Localization
OEB-41
Criteria: 22-1269
Applicable to: ALL
OEB-41
Criteria: 22-1269
Applicable to: ALL
T
DU Title
DU identification
00013609.0001001
15 OCT 15
Erroneous Alternate Fuel Predictions
Upon Modification of a Company Route
in the Alternate Flight Plan
00013610.0001001
15 OCT 15
Erroneous Alternate Fuel Predictions
Upon Modification of a Company Route
in the Alternate Flight Plan
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DU date
OEB-41 P 3/6
24 JAN 17
OPERATIONS ENGINEERING BULLETINS
A318/A319/A320/A321
ERRONEOUS ALTERNATE FUEL PREDICTIONS UPON MODIFICATION
OF A COMPANY ROUTE IN THE ALTERNATE FLIGHT PLAN
FLIGHT CREW
OPERATING MANUAL
ERRONEOUS ALTERNATE FUEL PREDICTIONS UPON MODIFICATION
OF A COMPANY ROUTE IN THE ALTERNATE FLIGHT PLAN
Ident.: OEB-41-00013610.0001001 / 15 OCT 15
Applicable to: ALL
EXPLANATION
When the flight crew modifies the CO RTE in the ALTN F-PLN , the FMS no longer computes the
ALTN fuel predictions (refer to the below illustration).
This CO RTE could be extracted from the Navigation database or stored by the flight crew.
The modification of the CO RTE by the flight crew could be for example an entry of a departure
or an arrival procedure.
The consequences of the CO RTE modification are:
‐ The fuel predictions are set to zero for the ALTN (solid circles) on FUEL PRED page (also on
INIT FUEL PRED if done on ground)
This condition is sufficient to apply the operational recommendations provided in the
"PROCEDURE" paragraph.
‐ The Estimated Fuel On Board (EFOB ) and the predicted UTC (solid circles) at ALTN
destination becomes equal to the EFOB and the UTC at the Primary Destination
‐ If the ALTN fuel and the MIN DEST FOB values on FUEL PRED page are both at their default
value (i.e. have not been modified by the crew), the MIN DEST FOB (solid circle) becomes
erroneous (equal to FINAL instead of FINAL+ ALTN ). Therefore, the MCDU scratchpad
message "DEST EFOB BELOW MIN", is no longer triggered on the expected threshold
‐ If the flight crew had entered a value for the ALTN fuel, the entry is correctly used (but no more
modifiable unless a new ALTN is entered)
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
OEB-41 P 4/6
24 JAN 17
OPERATIONS ENGINEERING BULLETINS
A318/A319/A320/A321
ERRONEOUS ALTERNATE FUEL PREDICTIONS UPON MODIFICATION
OF A COMPANY ROUTE IN THE ALTERNATE FLIGHT PLAN
FLIGHT CREW
OPERATING MANUAL
ERRONEOUS ALTERNATE FUEL PREDICTIONS UPON MODIFICATION
OF A COMPANY ROUTE IN THE ALTERNATE FLIGHT PLAN (Cont'd)
‐ If the flight crew had manually entered the MIN DEST FOB value on FUEL PRED page (but
not the ALTN fuel value), then the message "CHECK MIN DEST FOB" is no longer triggered
at the correct threshold
However, the new ALTN F-PLN is correctly displayed on the F-PLN page, the Navigation Display
(ND ) and the INIT page correctly shows the ALTN identifier.
Note:
The EFOB of the primary destination remains correctly computed (dashed circle).
The reason for the anomaly is that when the ALTN CO RTE is modified, the FMS erroneously
assumes there is no alternate F-PLN anymore for the fuel predictions. An additional modification
of the ALTN F-PLN enables to recover correct ALTN fuel predictions.
PROCEDURE
This procedure only applies when a CO RTE is used for ALTN F-PLN . In the case of ALTN fuel
predictions erroneously set to zero further to a modification of this ALTN F-PLN:
ENTER manually a waypoint in the en-route F-PLN (neither in the departure, nor in the arrival), to
start a new computation of ALTN fuel predictions
Maintain or delete the entered waypoint at convenience
Check the ALTN fuel predictions are correct
CORRECTIVE ACTION
Honeywell FMS standard H2C cancels this OEB (Refer to OEB-41 Erroneous Alternate Fuel
Predictions Upon Modification of a Company Route in the Alternate Flight Plan - Approval
"Cancelled by" section).
END OF OEB41
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
OEB-41 P 5/6
24 JAN 17
OPERATIONS ENGINEERING BULLETINS
A318/A319/A320/A321
ERRONEOUS ALTERNATE FUEL PREDICTIONS UPON MODIFICATION
OF A COMPANY ROUTE IN THE ALTERNATE FLIGHT PLAN
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
OEB-41 P 6/6
24 JAN 17
OPERATIONS
ENGINEERING BULLETINS
NO ENGAGEMENT OF GUIDANCE MODE
Intentionally left blank
OPERATIONS ENGINEERING BULLETINS
NO ENGAGEMENT OF GUIDANCE MODE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
No Engagement of Guidance Mode........................................................................................................................A
No Engagement of Guidance Mode........................................................................................................................B
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
OEB-46-PLP-TOC P 1/2
24 JAN 17
OPERATIONS ENGINEERING BULLETINS
NO ENGAGEMENT OF GUIDANCE MODE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
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OEB-46-PLP-TOC P 2/2
24 JAN 17
OPERATIONS ENGINEERING BULLETINS
NO ENGAGEMENT OF GUIDANCE MODE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OEB46 Issue 1
Associated with QRH OEB Proc N°: OEB46/1.0
NO ENGAGEMENT OF GUIDANCE MODE
Ident.: OEB-46-00015286.0001001 / 05 NOV 13
Applicable to: ALL
Approved by: Head of Airbus Flight Operations & Training Support
- This OEB covers a significant operational issue. Non-compliance with this OEB may have a
significant impact on the operations of the aircraft. The Operators shall distribute its content to all
flight crews without delay. An extract of this OEB is provided for insertion in the QRH.
- It is recommended that all Operators accelerate the incorporation of all corrective Service Bulletins
as soon as they become available.
Reason for issue:
The objective of this OEB is to highlight that in the event of an
erroneous Radio Altimeter (RA) height indication, guidance modes may
not engage as expected.
Applicable to:
All A318/A319/A320/A321 aircraft equipped with the ELAC L97 standard
(or subsequent ELAC standards).
Cancelled by:
FG C14 or FG PC14 or FG I15 or FG PI13 standards.
Note: The interchangeability code, given in the Illustrated Part Catalog (IPC), indicates the conditions for interchangeability
of equipment. After installation of corrective modification(s)/SB(s), if an Operator reinstalls any equipment affected by this
OEB, it is the Operator's responsibility to ensure that the recommendations given in this OEB are applied again for the
applicable aircraft.
Operations Engineering Bulletins are issued by Airbus, as the need arises, to quickly transmit
technical and procedural information. They are distributed to all FCOM holders and to others who
need advice of changes to operational information.
The information in the OEB is recommended by Airbus, but may not be approved by Airworthiness
Authorities. If the procedures contained in this OEB differ from the procedures in the AFM, the AFM
remains the reference.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
OEB-46 P 1/4
24 JAN 17
OPERATIONS ENGINEERING BULLETINS
NO ENGAGEMENT OF GUIDANCE MODE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
M
Localization
OEB-46
Criteria: 27-1238
Applicable to: ALL
OEB-46
Criteria: 27-1238
Applicable to: ALL
T
DU Title
No Engagement of Guidance Mode
No Engagement of Guidance Mode
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
DU identification
DU date
00015286.0001001
05 NOV 13
00015287.0001001
05 NOV 13
OEB-46 P 2/4
24 JAN 17
OPERATIONS ENGINEERING BULLETINS
NO ENGAGEMENT OF GUIDANCE MODE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
NO ENGAGEMENT OF GUIDANCE MODE
Ident.: OEB-46-00015287.0001001 / 05 NOV 13
Applicable to: ALL
EXPLANATION
If a RA transmits an erroneous height indication, this may have any of the following effects on
the auto flight system depending on the flight phase. However, these effects may not necessarily
occur in every case of an erroneous RA height indication.
Auto Flight System mode changes (indicated on FMA):
‐ NAV mode engagement is not possible after takeoff,
‐ In case of go-around and if the RA is still frozen at a very low height indication:
• SRS and GA TRK modes engage,
• NAV, HDG or TRK lateral modes cannot be selected,
• LVR CLB will not be displayed on the FMA at THR RED ALT,
• ALT* and ALT will not engage at FCU altitude.
Disconnecting AP and resetting both FDs enable to recover basic mode (HDG and V/S).
PROCEDURE
During go-around
If SRS and GA TRK modes remain engaged and other guidance modes cannot be
selected or engaged as expected:
Note:
‐ At the thrust reduction altitude, LVR CLB will not be displayed on the FMA,
‐ ALT* and ALT will not engage at the FCU altitude.
Disconnect APs.
Set both FD s to OFF then ON. FDs revert to basic modes (HDG - V/S).
Re-engage guidance modes as appropriate.
For the approach that follows the go-around: Do not arm the G/S mode.
Flight crews must report, in the technical logbook, any of the above-listed consequences of
erroneous RA height.
CORRECTIVE ACTION
FG C14 or FG PC14 or FG I15 or FG PI13.
END OF OEB46
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FCOM
B
OEB-46 P 3/4
24 JAN 17
OPERATIONS ENGINEERING BULLETINS
NO ENGAGEMENT OF GUIDANCE MODE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
OEB-46 P 4/4
24 JAN 17
PERFORMANCE
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PERFORMANCE
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TABLE OF CONTENTS
PER-LOD Loading
PER-OPD Operating Data
PER-THR Thrust Ratings
PER-TOF Takeoff
PER-FPL Flight Planning
PER-CLB Climb
PER-CRZ Cruise
PER-HLD Holding
PER-DES Descent
PER-GOA Go Around
PER-LDG Landing
PER-OEI One Engine Inoperative
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PER-PLP-TOC P 1/2
22 MAR 17
PERFORMANCE
PRELIMINARY PAGES
A318/A319/A320/A321
TABLE OF CONTENTS
FLIGHT CREW
OPERATING MANUAL
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PER-PLP-TOC P 2/2
22 MAR 17
PERFORMANCE
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
M
Localization
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
DU Title
DU identification
DU date
No Temporary Documentary Unit
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-PLP-LETDU P 1/2
17 OCT 17
PERFORMANCE
PRELIMINARY PAGES
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS
Intentionally left blank
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PER-PLP-LETDU P 2/2
17 OCT 17
PERFORMANCE
LOADING
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PERFORMANCE
LOADING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-LOD-GEN GENERAL
DEFINITIONS...........................................................................................................................................................A
PER-LOD-CGO CARGO LOADING
GENERAL................................................................................................................................................................ A
PER-LOD-FUL FUEL
USE OF MANUAL MAGNETIC INDICATORS (MMI)............................................................................................. A
PER-LOD-WBA WEIGHT AND BALANCE
PER-LOD-WBA-LTS LOAD AND TRIM SHEET
GENERAL................................................................................................................................................................ A
DATA........................................................................................................................................................................B
DESCRIPTION.........................................................................................................................................................C
LOAD AND TRIM SHEET.......................................................................................................................................D
PER-LOD-WBA-FIT FUEL INDEX TABLES
PER-LOD-WBA-FIT-10 FUEL INDEX TABLE
GENERAL................................................................................................................................................................ A
FUEL INDEX TABLE FOR INNER TANK...............................................................................................................B
FUEL INDEX TABLE FOR OUTER TANK............................................................................................................. C
FUEL INDEX TABLE FOR CENTER TANK........................................................................................................... D
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PER-LOD-PLP-TOC P 1/2
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
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PER-LOD-PLP-TOC P 2/2
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
DEFINITIONS
Ident.: PER-LOD-GEN-00001661.0001001 / 09 DEC 09
Applicable to: ALL
MANUFACTURER’S EMPTY WEIGHT (MEW)
The weight of the structure, power plant, furnishings, systems and other items of equipment that
are considered as integral part of the aircraft. It is essentially a “dry” weight, including only those
fluids contained in closed systems (e.g. hydraulic fluid).
OPERATIONAL EMPTY WEIGHT (OEW)
The manufacturer’s weight empty plus the operator’s items i.e. the flight and cabin crew and their
baggage, unusable fuel, engine oil, emergency equipment, toilet chemicals and fluids, galley
structure, catering equipment, seats, documents etc.
DRY OPERATING WEIGHT (DOW)
The total weight of an aircraft ready for a specific type of operation excluding all usable fuel and
traffic load.
Operational Empty Weight plus items specific to the type of flight i.e. catering, newspapers, pantry
equipment etc.
TAKEOFF FUEL
The weight of the fuel onboard at takeoff.
OPERATING WEIGHT
The weight obtained by addition of the operational empty weight and the takeoff fuel.
TOTAL TRAFFIC LOAD
The weight of the payload including cargo loads, passengers and passengers bags.
ZERO FUEL WEIGHT (ZFW)
The weight obtained by addition of the total traffic load and the dry operating weight.
TAKEOFF WEIGHT (TOW)
The weight at takeoff. It is equal to the addition of the zero fuel weight and takeoff fuel.
TRIP FUEL
The weight of the fuel necessary to cover the normal leg without reserves.
LANDING WEIGHT
The weight at landing. It is equal to takeoff weight minus trip fuel.
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A
PER-LOD-GEN P 1/2
24 JAN 17
PERFORMANCE
LOADING
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
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FCOM
PER-LOD-GEN P 2/2
24 JAN 17
PERFORMANCE
LOADING
A318/A319/A320/A321
CARGO LOADING
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PER-LOD-CGO-00001662.0002001 / 09 DEC 09
Applicable to: ALL
The aircraft has two lower deck cargo compartments :
‐ Forward cargo compartment, compartment 1.
‐ Aft cargo compartment, subdivided into compartments 3, 4 and 5.
The main access doors to forward and aft compartments are hydraulically operated.
A bulk cargo door gives additional access to the aft cargo compartment. It is manually operated.
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PER-LOD-CGO P 1/2
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
CARGO LOADING
FLIGHT CREW
OPERATING MANUAL
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PER-LOD-CGO P 2/2
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
USE OF MANUAL MAGNETIC INDICATORS (MMI)
Applicable to: ALL
Ident.: PER-LOD-FUL-C-00001679.0005001 / 23 JUN 15
GENERAL
Indicators are disposed as follows:
• five in each wing tank, four in inner tank and one in outer tank
• one in the center tank
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PER-LOD-FUL P 1/14
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
TO DETERMINE AIRCRAFT ATTITUDE
Set ADIRS 1, 2, 3 to the NAV position.
On the LH or RH MCDU, press MCDU MENU pushbutton.
Select CFDS line key (LSK 4L).
Select SYSTEM REPORT/TEST line key (LSK 5L).
Select the line key adjacent to the FUEL indication.
On the MCDU control panel, push the NEXT PAGE key to display the FUEL Main Menu second
page.
Select the line key adjacent to the INPUT PARAMETERS VALUES indication.
Use the Table given on the next page to determine the equivalent number and letter from
PITCH and ROLL data.
Select RETURN line key (LSK 6L) until CFDS main menu appears.
Press MCDU MENU pushbutton.
PITCH
Minus 1.5
Minus 1.0
Minus 0.5
0.0
Plus 0.5
Plus 1.0
Plus 1.5
Note:
REF
1
ROLL
Minus 1.5
Minus 1.0
Minus 0.5
0.0
Plus 0.5
Plus 1.0
Plus 1.5
2
3
4
5
6
7
REF
A
B
C
D
E
F
G
1. This procedure can only be used if:
‐ The PITCH and ROLL data is taken from the ADIRS (identified by an “A” after the
PITCH and ROLL title).
‐ The PITCH data displayed for the LEFT, CTR, and RIGHT is no more or less than
0.1 of each other.
‐ The ROLL data displayed for the LEFT, CTR, and RIGHT is no more or less than
0.1 of each other.
2. The FQIS input parameters are not automatically updated. Use the NEXT PAGE
control on the MCDU to cycle the pages to update the screen.
ACCESS PLATFORM...............................................................................................IN POSITION
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PER-LOD-FUL P 2/14
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
Ident.: PER-LOD-FUL-C-00001692.0001001 / 13 JAN 14
TO DETERMINE FUEL QUANTITY IN THE OUTER TANK
MMI number 5......................................................................................... UNLOCK and WITHDRAW
The crewmember must withdraw the MMI slowly until he feels the magnetic attraction between the
rod and float magnets.
Do not use force when withdrawing the MMI as this will disengage the float magnet from the rod
magnet and bring the rod down onto the mechanical stop.
ROD GRADUATION (which aligns with bottom wing surface).................................................READ
MMI............................................................................................................. IN PLACE and LOCKED
Use the table for the applicable aircraft wing side, aircraft attitude (grid square letter and number),
and the MMI stick number 5, to find the volume of fuel in the outer tank (See below).
Multiply the result by the specific gravity to find the fuel weight.
Note:
The manual magnetic indication accuracy is around 5 %.
Ident.: PER-LOD-FUL-C-00001680.0001001 / 13 JAN 14
TO DETERMINE FUEL QUANTITY IN THE INNER TANK
MMI (from number 4 to number 1).......................................................... UNLOCK and WITHDRAW
The crewmember must withdraw the MMI slowly until he feels the magnetic attraction between the
rod and float magnets.
Do not use force when withdrawing the MMI as this will disengage the float magnet from the rod
magnet and bring the rod down onto the mechanical stop.
ROD GRADUATION (which aligns with bottom wing surface).................................................READ
MMI............................................................................................................. IN PLACE and LOCKED
MMIs shall be withdrawn from number 4 to number 1 until one MMI measures fuel.
Use the table for the applicable aircraft wing side, aircraft attitude (grid square letter and number),
and the applicable MMI stick number to find the volume of fuel in the inner tank (Refer to FCOM PER.LOD.FUL FUEL. C.USE OF MANUAL MAGNETIC INDICATORS (MMI) - WING TANKS).
Multiply the result by the specific gravity to find the fuel weight.
Note:
The manual magnetic indication accuracy is around 5 %.
Ident.: PER-LOD-FUL-C-00009658.0001001 / 13 JAN 14
TO DETERMINE FUEL QUANTITY IN THE CENTER TANK
CENTER TANK MMI............................................................................... UNLOCK and WITHDRAW
The crewmember must withdraw the MMI slowly until he feels the magnetic attraction between the
rod and float magnets.
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FUEL
FLIGHT CREW
OPERATING MANUAL
Do not use force when withdrawing the MMI as this will disengage the float magnet from the rod
magnet and bring the rod down onto the mechanical stop.
ROD GRADUATION (which aligns with bottom wing surface).................................................READ
MMI............................................................................................................. IN PLACE and LOCKED
Use the table for the center tank, and for the applicable aircraft attitude (grid square letter and
number) to find the volume of fuel in the center tank (See below).
Multiply the result by the specific gravity to find the fuel weight.
Note:
The manual magnetic indication accuracy is around 5 %.
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PER-LOD-FUL P 4/14
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PERFORMANCE
LOADING
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
Ident.: PER-LOD-FUL-C-00001681.0001001 / 17 MAR 11
WING TANKS (LITERS)
*
**
GRID SQUARE LETTER
GRID SQUARE NUMBER
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22 MAR 17
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FLIGHT CREW
OPERATING MANUAL
*
**
GRID SQUARE LETTER
GRID SQUARE NUMBER
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*
**
GRID SQUARE LETTER
GRID SQUARE NUMBER
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*
GRID SQUARE LETTER
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-LOD-FUL P 11/14
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
**
GRID SQUARE NUMBER
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-LOD-FUL P 12/14
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
Ident.: PER-LOD-FUL-C-00001682.0001001 / 16 NOV 11
CENTER TANK (LITERS)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-LOD-FUL P 13/14
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FUEL
FLIGHT CREW
OPERATING MANUAL
*
**
GRID SQUARE LETTER
GRID SQUARE NUMBER
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-LOD-FUL P 14/14
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEIGHT AND BALANCE - LOAD AND TRIM SHEET
GENERAL
Ident.: PER-LOD-WBA-LTS-00001685.0001001 / 09 DEC 09
Applicable to: ALL
This chart allows the determination of Aircraft CG location (MAC) function of dry operating weight,
pantry adjustment, cargo loads, passengers and fuel on board.
The operational limits shown on the load and trim sheet are more restrictive than the certified limits
because error margins have been taken into account.
The load and trim sheet needs to be updated when :
‐ a modification which changes the aircraft certified limits is included or
‐ a modification (cabin layout, cargo arrangement ...) which influences the operational limits is
made.
It is the airline responsibility to define a load and trim sheet and to keep it up to date. Refer to
PER-LOD-WBA-LTS DESCRIPTION is a description of the Load and Trim Sheet utilization (Refer to
PER-LOD-WBA-LTS LOAD AND TRIM SHEET), for a typical passenger arrangement.
Refer to customized load and trim sheet for preparing a revenue flight.
DATA
Ident.: PER-LOD-WBA-LTS-00001686.0002001 / 23 JUN 15
Applicable to: ALL
Dry Operating Weight = 42 500 kg and CG = 27 % (H-arm = 18.93 m)
Deviation or adjustment = +100 kg in zone F
Cargo = 5 500 kg with the following distribution:
cargo 1 = 2 000 kg; cargo 3 = 1 500 kg; cargo 4 = 1 500 kg; cargo 5 = 500 kg
Passengers = 145 PAX with the following distribution:
cabin OA = 50; cabin OB = 55; cabin OC = 40
Ramp Fuel = 13 200 kg; Taxi Fuel = 200 kg; Fuel Density = 0.785 kg/l
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-LOD-WBA-LTS P 1/4
24 JAN 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEIGHT AND BALANCE - LOAD AND TRIM SHEET
DESCRIPTION
Ident.: PER-LOD-WBA-LTS-00001687.0002001 / 12 FEB 11
Applicable to: ALL
a.
b.
c.
d.
e.
f.
Enter Master data in (1).
Compute Dry Operating Weight Index using the formula indicated in (2) and report in (3).
Dry Operating Index = 53.4.
Enter weight deviation or adjustment in (4) and read corresponding index variation in (5): +1.43.
Calculate corrected index and report in (6): 54.83.
Enter master data in table (7) and determine Zero Fuel Weight: 60 280 kg and Takeoff Weight:
73 280 kg.
g. Enter cargo weight and passenger number per compartment in (8).
h. Enter index scale (9) with corrected index and proceed through cargo and passenger scales (10).
i. From the final point draw a vertical line which intersects (12) the zero fuel weight horizontal line
(11).
j. Check if the intersection point is within the Zero Fuel Weight operational limits, if not rearrange
cargo loading.
k. Read in table (13) the fuel index correction corresponding to Ramp Fuel Weight (13 200 kg) and
Fuel Density (0.785 kg/l).
This example will be continued assuming the FUEL INDEX = –2 was found. Carry in fuel scale
(14).
l. From this point draw a vertical line which intersects (16) the takeoff weight horizontal line (15).
m. Check if the intersection point is within the Takeoff Weight operational limits.
n. Read zero fuel weight and CG position: 32.7 % and fill in table (17).
o. Read takeoff CG position: 30.5 % and fill in table (18).
CAUTION
Note:
If there is no customized trim sheet for your airline in this section, do not use the
information enclosed herein for day to day operation as margins and load CG vary
with cabin and cargo layout.
When referring to CG lower than 27 %, an operational margin is taken into account. It is the
reason why performance at forward CG (lower than 25 %) must be used for operational CG
lower than 27 %.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PER-LOD-WBA-LTS P 2/4
24 JAN 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEIGHT AND BALANCE - LOAD AND TRIM SHEET
LOAD AND TRIM SHEET
Ident.: PER-LOD-WBA-LTS-00001688.0002001 / 23 FEB 11
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PER-LOD-WBA-LTS P 3/4
24 JAN 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEIGHT AND BALANCE - LOAD AND TRIM SHEET
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PER-LOD-WBA-LTS P 4/4
24 JAN 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEIGHT AND BALANCE - FUEL INDEX TABLES
FUEL INDEX TABLE
GENERAL
Ident.: PER-LOD-WBA-FIT-10-00012775.0002001 / 21 MAR 17
Applicable to: ALL
The fuel index table has been established assuming a fuel distribution in accordance with refuel
distribution given in sectionRefer to DSC-28-10-70 Refueling - Defueling of this volume.
If after refueling the actual distribution deviates from the chart values, the actual and the trim sheet
CG will show a discrepancy. The following tables allow to determine the fuel index taking into
account the actual fuel quantity in each tank. To determine the actual takeoff CG enter the tables
with the actual fuel quantities in each tank, read the fuel index for each tank and use their sum to
enter the trim sheet. Check that the actual CG is inside the operational limits. If the CG is outside the
limits transfer fuel to achieve a distribution in accordance with the chart or rearrange the load.
Note:
DATA :
These tables are valid only when used with the following formula for the index:
I = W × (H-arm – 18.85)/1 000 + K or I = [(CG – 25) × W × 0.000042] + K
(Weight in kg, H-arm in m)
Fuel in left inner fuel tank = 4 500 kg
Fuel in right inner fuel tank = 4 500 kg
Fuel in left outer fuel tank = 200 kg
Fuel in right outer fuel tank = FULL
Fuel in center tank = 0 kg
Inner tank
Outer tank
Center tank
TOTAL
Left
Right
Left
Right
Weight
4 500
4 500
200
-
691
+
9 891
-
0
Index
3
3
0
2
0
4
Enter the trim sheet with a fuel index of –4
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-LOD-WBA-FIT-10 P 1/4
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEIGHT AND BALANCE - FUEL INDEX TABLES
FUEL INDEX TABLE FOR INNER TANK
Ident.: PER-LOD-WBA-FIT-10-00012776.0001001 / 25 JUL 12
Applicable to: ALL
Note:
These tables are valid only when used with the following formulae for the index:
I=W×(H-arm–18.85)/1 000+K or I=[(CG–25)×W×0.000042]+K (Weight in kg, H-arm in m)
Weight
500
1 000
1 500
2 000
2 500
3 000
3 500
4 000
4 500
5 000
FULL
Index
-1
-1
-2
-2
-2
-3
-3
-3
-3
-3
-2
FUEL INDEX TABLE FOR OUTER TANK
Ident.: PER-LOD-WBA-FIT-10-00012777.0001001 / 25 JUL 12
Applicable to: ALL
Note:
These tables are valid only when used with the following formulae for the index:
I=W×(H-arm–18.85)/1 000+K or I=[(CG–25)×W×0.000042]+K (Weight in kg, H-arm in m)
Weight
250
500
FULL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Index
1
1
2
B to C
PER-LOD-WBA-FIT-10 P 2/4
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEIGHT AND BALANCE - FUEL INDEX TABLES
FUEL INDEX TABLE FOR CENTER TANK
Ident.: PER-LOD-WBA-FIT-10-00012778.0001001 / 25 JUL 12
Applicable to: ALL
Note:
These tables are valid only when used with the following formulae for the index:
I=W×(H-arm–18.85)/1 000+K or I=[(CG–25)×W×0.000042]+K (Weight in kg, H-arm in m)
Weight
500
1 000
1 500
2 000
2 500
3 000
3 500
4 000
4 500
5 000
5 500
6 000
FULL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Index
-1
-1
-2
-3
-3
-4
-5
-6
-7
-7
-8
-9
-10
D
PER-LOD-WBA-FIT-10 P 3/4
22 MAR 17
PERFORMANCE
LOADING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WEIGHT AND BALANCE - FUEL INDEX TABLES
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-LOD-WBA-FIT-10 P 4/4
22 MAR 17
PERFORMANCE
OPERATING DATA
Intentionally left blank
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-OPD-GEN GENERAL
CONVERSIONS - IAS . MACH - TAS . MACH - SAT . TAT..................................................................................A
INTERNATIONAL STANDARD ATMOSPHERE (ISA)............................................................................................B
CONVERSIONS - QNH - QFE - PRESSURE ALTITUDE......................................................................................C
CONVERSIONS QFE HPA - IN. HG - FT..............................................................................................................D
WIND COMPONENTS (FOR TAKEOFF AND LANDING)......................................................................................E
ALTITUDE TEMPERATURE CORRECTION.......................................................................................................... F
PER-OPD-CON GROUND DISTANCE/AIR DISTANCE CONVERSION
PER-OPD-CON-AEO ALL ENGINES OPERATIVE
GENERAL................................................................................................................................................................ A
M.78......................................................................................................................................................................... B
LONG RANGE SPEED UP TO FL270................................................................................................................... C
LONG RANGE SPEED ABOVE FL270.................................................................................................................. D
PER-OPD-CON-OEI ONE ENGINE INOPERATIVE
GENERAL................................................................................................................................................................ A
LONG RANGE SPEED........................................................................................................................................... B
FIXED SPEEDS.......................................................................................................................................................C
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OPD-PLP-TOC P 1/2
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OPD-PLP-TOC P 2/2
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
CONVERSIONS - IAS . MACH - TAS . MACH - SAT . TAT
Ident.: PER-OPD-GEN-00001962.0001001 / 23 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-OPD-GEN P 1/10
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
INTERNATIONAL STANDARD ATMOSPHERE (ISA)
Ident.: PER-OPD-GEN-00001963.0001001 / 09 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PER-OPD-GEN P 2/10
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
CONVERSIONS - QNH - QFE - PRESSURE ALTITUDE
Ident.: PER-OPD-GEN-00001964.0001001 / 09 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PER-OPD-GEN P 3/10
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
CONVERSIONS QFE HPA - IN. HG - FT
Ident.: PER-OPD-GEN-00001965.0001001 / 08 FEB 11
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PER-OPD-GEN P 4/10
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PER-OPD-GEN P 5/10
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
WIND COMPONENTS (FOR TAKEOFF AND LANDING)
Ident.: PER-OPD-GEN-00001966.0001001 / 08 FEB 11
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
PER-OPD-GEN P 6/10
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E
PER-OPD-GEN P 7/10
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
ALTITUDE TEMPERATURE CORRECTION
Ident.: PER-OPD-GEN-00001967.0001001 / 12 FEB 11
Applicable to: ALL
FOR HIGH ALTITUDE USE
FOR LOW ALTITUDE USE
Values to be added by the pilot to minimum promulgated heights/altitude (ft)
Airport Temperature °C
0
200
20
Height above the elevation of the altimeter setting source (feet)
300
400
500
1 000
2 000
3 000
4 000
5 000
20
30
30
60
120
170
230
280
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PER-OPD-GEN P 8/10
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Airport Temperature °C
-10
-20
-30
-40
-50
200
20
30
40
50
60
Continued from the previous page
Height above the elevation of the altimeter setting source (feet)
300
400
500
1 000
2 000
3 000
4 000
5 000
30
40
50
100
200
290
390
490
50
60
70
140
280
420
570
710
60
80
100
190
380
570
760
950
80
100
120
240
480
720
970
1 210
90
120
150
300
590
890
1 190
1 500
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
PER-OPD-GEN P 9/10
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OPD-GEN P 10/10
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GROUND DISTANCE/AIR DISTANCE
CONVERSION - ALL ENGINES OPERATIVE
GENERAL
Ident.: PER-OPD-CON-AEO-00001657.0001001 / 23 FEB 11
Applicable to: ALL
The ground distance/air distance conversion tables show the air distance for a given ground distance
due to the influence of the wind.
The Tables are given for :
‐ M .78
‐ Long range speed.
M.78
Ident.: PER-OPD-CON-AEO-00001658.0001001 / 28 JAN 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-OPD-CON-AEO P 1/4
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GROUND DISTANCE/AIR DISTANCE
CONVERSION - ALL ENGINES OPERATIVE
FLIGHT CREW
OPERATING MANUAL
LONG RANGE SPEED UP TO FL270
Ident.: PER-OPD-CON-AEO-00001659.0001001 / 28 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PER-OPD-CON-AEO P 2/4
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GROUND DISTANCE/AIR DISTANCE
CONVERSION - ALL ENGINES OPERATIVE
FLIGHT CREW
OPERATING MANUAL
LONG RANGE SPEED ABOVE FL270
Ident.: PER-OPD-CON-AEO-00001660.0001001 / 09 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PER-OPD-CON-AEO P 3/4
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GROUND DISTANCE/AIR DISTANCE
CONVERSION - ALL ENGINES OPERATIVE
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OPD-CON-AEO P 4/4
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GROUND DISTANCE/AIR DISTANCE
CONVERSION - ONE ENGINE INOPERATIVE
GENERAL
Ident.: PER-OPD-CON-OEI-00004074.0001001 / 09 DEC 09
Applicable to: ALL
The ground distance/air distance conversion tables are used to calculate the air distance for a given
ground distance due to the influence of the wind.
Tables are given for :
‐ LONG RANGE SPEED
‐ FIXED SPEEDS
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-OPD-CON-OEI P 1/4
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GROUND DISTANCE/AIR DISTANCE
CONVERSION - ONE ENGINE INOPERATIVE
FLIGHT CREW
OPERATING MANUAL
LONG RANGE SPEED
Ident.: PER-OPD-CON-OEI-00001960.0001001 / 09 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PER-OPD-CON-OEI P 2/4
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
GROUND DISTANCE/AIR DISTANCE
CONVERSION - ONE ENGINE INOPERATIVE
FLIGHT CREW
OPERATING MANUAL
FIXED SPEEDS
Ident.: PER-OPD-CON-OEI-00001961.0001001 / 09 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PER-OPD-CON-OEI P 3/4
24 JAN 17
PERFORMANCE
OPERATING DATA
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GROUND DISTANCE/AIR DISTANCE
CONVERSION - ONE ENGINE INOPERATIVE
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OPD-CON-OEI P 4/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
Intentionally left blank
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-THR-GEN GENERAL
GENERAL................................................................................................................................................................ A
PER-THR-MTO MAXIMUM TAKEOFF
DEFINITION............................................................................................................................................................. A
MAXIMUM TAKEOFF.............................................................................................................................................. B
PER-THR-MGA MAXIMUM GO AROUND
DEFINITION............................................................................................................................................................. A
MAXIMUM GO AROUND........................................................................................................................................ B
PER-THR-FLX FLEXIBLE TAKEOFF
DEFINITION............................................................................................................................................................. A
FLEXIBLE TAKEOFF...............................................................................................................................................B
PER-THR-MCT MAXIMUM CONTINUOUS
DEFINITION............................................................................................................................................................. A
MAXIMUM CONTINUOUS...................................................................................................................................... B
PER-THR-MCL MAXIMUM CLIMB
DEFINITION............................................................................................................................................................. A
MAXIMUM CLIMB....................................................................................................................................................B
PER-THR-MCR MAXIMUM CRUISE
DEFINITION............................................................................................................................................................. A
MAXIMUM CRUISE................................................................................................................................................. B
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-THR-PLP-TOC P 1/2
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-THR-PLP-TOC P 2/2
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PER-THR-GEN-00004079.0001001 / 28 FEB 11
Applicable to: ALL
The thrust rating charts have been established for:
‐ Maximum takeoff
‐ Maximum go around
‐ Flexible takeoff
‐ Maximum continuous
‐ Maximum climb
‐ Maximum cruise
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-THR-GEN P 1/2
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-THR-GEN P 2/2
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM TAKEOFF
FLIGHT CREW
OPERATING MANUAL
DEFINITION
Ident.: PER-THR-MTO-00001968.0001001 / 01 MAR 11
Applicable to: ALL
It is the maximum thrust certified for takeoff and is normally limited to five minutes.
This time is extended to ten minutes for engine out contingency, as authorized by the approved AFM.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-THR-MTO P 1/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM TAKEOFF
FLIGHT CREW
OPERATING MANUAL
MAXIMUM TAKEOFF
Ident.: PER-THR-MTO-00001969.0017001 / 28 JAN 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-THR-MTO P 2/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM TAKEOFF
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PER-THR-MTO P 3/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM TAKEOFF
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-THR-MTO P 4/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM GO AROUND
FLIGHT CREW
OPERATING MANUAL
DEFINITION
Ident.: PER-THR-MGA-00001971.0001001 / 23 FEB 11
Applicable to: ALL
It is the maximum permissible thrust during go-around.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-THR-MGA P 1/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM GO AROUND
FLIGHT CREW
OPERATING MANUAL
MAXIMUM GO AROUND
Ident.: PER-THR-MGA-00001972.0024001 / 28 JAN 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-THR-MGA P 2/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM GO AROUND
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PER-THR-MGA P 3/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM GO AROUND
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-THR-MGA P 4/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
DEFINITION
Ident.: PER-THR-FLX-00001973.0001001 / 23 FEB 11
Applicable to: ALL
It is a reduced takeoff thrust as compared to the maximum permissible. The related N1 is calculated
as a function of the flexible temperature entered in the FMGS MCDU. The flexible temperature is a
function of the aircraft weight and environmental conditions.
It guarantees that the regular performance requirements are met.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-THR-FLX P 1/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
FLEXIBLE TAKEOFF
Ident.: PER-THR-FLX-00001974.0035001 / 23 FEB 11
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-THR-FLX P 2/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PER-THR-FLX P 3/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-THR-FLX P 4/4
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM CONTINUOUS
FLIGHT CREW
OPERATING MANUAL
DEFINITION
Ident.: PER-THR-MCT-00001975.0001001 / 28 FEB 11
Applicable to: ALL
It is the maximum thrust certified for continuous use. This rating should be used, at the pilot’s
discretion, only when required to ensure safe flight (engine failure).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-THR-MCT P 1/2
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM CONTINUOUS
FLIGHT CREW
OPERATING MANUAL
MAXIMUM CONTINUOUS
Ident.: PER-THR-MCT-00001976.0011001 / 28 JAN 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PER-THR-MCT P 2/2
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM CLIMB
FLIGHT CREW
OPERATING MANUAL
DEFINITION
Ident.: PER-THR-MCL-00001977.0001001 / 23 FEB 11
Applicable to: ALL
It is the maximum thrust approved for normal climb.
MAXIMUM CLIMB
Ident.: PER-THR-MCL-00001978.0011001 / 28 JAN 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-THR-MCL P 1/2
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM CLIMB
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-THR-MCL P 2/2
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM CRUISE
FLIGHT CREW
OPERATING MANUAL
DEFINITION
Ident.: PER-THR-MCR-00001979.0004001 / 02 FEB 11
Applicable to: ALL
It is the maximum thrust approved for normal cruise.
There is no thrust lever position corresponding to this thrust rating.
It is not displayed to the pilot, and the N1 limit which is displayed in cruise is the maximum climb N1.
The FMGS uses the maximum cruise N1 to compute the aircraft maximum speed.
In manual thrust setting, in cruise, the pilot should limit N1 to the maximum cruise N1 that is equal to
the displayed maximum climb N1 minus 1.9 %.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-THR-MCR P 1/2
24 JAN 17
PERFORMANCE
THRUST RATINGS
A318/A319/A320/A321
MAXIMUM CRUISE
FLIGHT CREW
OPERATING MANUAL
MAXIMUM CRUISE
Ident.: PER-THR-MCR-00001980.0018001 / 28 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PER-THR-MCR P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
Intentionally left blank
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-TOF-THR THRUST OPTIONS
PER-TOF-THR-FLX FLEXIBLE TAKEOFF
PER-TOF-THR-FLX-10 DEFINITION OF FLEXIBLE TAKEOFF
DEFINITION OF FLEXIBLE TAKEOFF...................................................................................................................A
PER-TOF-THR-FLX-20 USE OF FLEXIBLE TAKEOFF
USE OF FLEXIBLE TAKEOFF................................................................................................................................A
PER-TOF-THR-FLX-30 REQUIREMENTS
REQUIREMENTS.................................................................................................................................................... A
PER-TOF-THR-FLX-40 RECOMMENDATION
GENERAL................................................................................................................................................................ A
TAKEOFF PROCEDURE........................................................................................................................................ B
PER-TOF-TOC TAKEOFF CHARTS
PER-TOF-TOC-05 INTRODUCTION
TAKEOFF CHARTS.................................................................................................................................................A
PER-TOF-TOC-10 GENERAL (TEMPERATURE ENTRY)
PER-TOF-TOC-10-10 TAKEOFF PERFORMANCE
TAKEOFF PERFORMANCE................................................................................................................................... A
PER-TOF-TOC-10-20 TAKEOFF CHART DESCRIPTION
GENERAL................................................................................................................................................................ A
Corrections due to Different Takeoff Conditions..................................................................................................... B
DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART........................................................................ C
MINIMUM SPEEDS................................................................................................................................................. D
FLEX TEMPERATURE INDICATOR.......................................................................................................................E
PER-TOF-TOC-10-30 ADDITIONAL INFORMATION
ONE ENGINE OUT CLIMB PROCEDURE............................................................................................................. A
TAKEOFF ON A WET RUNWAY............................................................................................................................B
DESCRIPTION OF TAKEOFF CHART...................................................................................................................C
EXAMPLE OF TAKEOFF CHART.......................................................................................................................... D
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-PLP-TOC P 1/6
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
PER-TOF-TOC-12 MTOW CALCULATION (TEMPERATURE ENTRY)
PER-TOF-TOC-12-10 DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND SPEEDS
DIRECT CHART READING.................................................................................................................................... A
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS.........................................................................B
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS............................................................................... C
CORRECTIONS FOR WET OR CONTAMINATED RUNWAYS............................................................................ D
CORRECTIONS PRODUCED ON THE RTOW CHART........................................................................................ E
COMBINING CORRECTIONS FROM FCOM AND CHART................................................................................... F
PER-TOF-TOC-12-30 EXTRAPOLATION
EXTRAPOLATION................................................................................................................................................... A
PER-TOF-TOC-12-40 MAXIMUM STRUCTURAL TAKEOFF WEIGHT
MAXIMUM STRUCTURAL TAKEOFF WEIGHT..................................................................................................... A
PER-TOF-TOC-12-50 SUMMARY
SUMMARY............................................................................................................................................................... A
PER-TOF-TOC-14 FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
PER-TOF-TOC-14-10 DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE AND
SPEEDS
GENERAL................................................................................................................................................................ A
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS.........................................................................B
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS............................................................................... C
CORRECTIONS FOR WET RUNWAY................................................................................................................... D
CORRECTIONS PRODUCED ON THE RTOW CHART........................................................................................ E
COMBINING CORRECTIONS FROM FCOM AND CHART................................................................................... F
PER-TOF-TOC-14-20 FLEXIBLE TAKEOFF NOT POSSIBLE
FLEXIBLE TAKEOFF NOT POSSIBLE...................................................................................................................A
PER-TOF-TOC-14-25 FLEXIBLE TAKEOFF POSSIBLE BUT NOT USED
FLEXIBLE TAKEOFF POSSIBLE BUT NOT USED............................................................................................... A
PER-TOF-TOC-14-30 SUMMARY
SUMMARY............................................................................................................................................................... A
PER-TOF-TOC-16 GENERAL (WEIGHT ENTRY)
PER-TOF-TOC-16-10 TAKEOFF PERFORMANCE
TAKEOFF PERFORMANCE................................................................................................................................... A
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-PLP-TOC P 2/6
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-TOF-TOC-16-20 TAKEOFF CHART DESCRIPTION
Continued from the previous page
GENERAL................................................................................................................................................................ A
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS.........................................................................B
DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART........................................................................ C
MINIMUM SPEED................................................................................................................................................... D
PER-TOF-TOC-16-30 ADDITIONAL INFORMATION
ONE ENGINE OUT CLIMB PROCEDURE............................................................................................................. A
TAKEOFF ON A WET RUNWAY............................................................................................................................B
RTOW CHARTS - COMPLEMENTARY INFORMATION....................................................................................... C
RTOW EXAMPLE....................................................................................................................................................D
PER-TOF-TOC-18 MTOW CALCULATION (WEIGHT ENTRY)
PER-TOF-TOC-18-10 DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND SPEEDS
GENERAL................................................................................................................................................................ A
MTOW DETERMINATION.......................................................................................................................................B
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS.........................................................................C
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS............................................................................... D
CORRECTIONS FOR WET OR CONTAMINATED RUNWAYS.............................................................................E
CORRECTIONS PRODUCED ON THE RTOW CHART........................................................................................ F
COMBINING CORRECTIONS FROM FCOM AND CHART.................................................................................. G
PER-TOF-TOC-18-20 EXTRAPOLATION
EXTRAPOLATION................................................................................................................................................... A
PER-TOF-TOC-18-30 MAXIMUM STRUCTURAL TAKEOFF WEIGHT
MAXIMUM STRUCTURAL TAKEOFF WEIGHT..................................................................................................... A
PER-TOF-TOC-18-40 SUMMARY
SUMMARY............................................................................................................................................................... A
PER-TOF-TOC-20 FLEXIBLE TAKEOFF (WEIGHT ENTRY)
PER-TOF-TOC-20-10 DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE AND
SPEEDS
GENERAL................................................................................................................................................................ A
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS.........................................................................B
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS............................................................................... C
CORRECTIONS FOR WET RUNWAY................................................................................................................... D
CORRECTIONS PRODUCED ON THE RTOW CHART........................................................................................ E
COMBINING CORRECTIONS FROM FCOM AND CHART................................................................................... F
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-PLP-TOC P 3/6
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-TOF-TOC-20-20 FLEXIBLE TAKEOFF NOT POSSIBLE
Continued from the previous page
FLEXIBLE TAKEOFF NOT POSSIBLE...................................................................................................................A
PER-TOF-TOC-20-30 SUMMARY
SUMMARY............................................................................................................................................................... A
PER-TOF-TOD TAKEOFF DATA
PER-TOF-TOD-24 QNH/BLEEDS CORRECTION
EFFECT OF QNH AND BLEEDS (up to 9200 ft)................................................................................................... A
EXAMPLE................................................................................................................................................................ B
EFFECT OF QNH AND BLEEDS FOR HIGH ALTITUDE OPERATIONS (above 9200 ft).....................................C
EXAMPLES FOR HIGH ALTITUDE OPERATIONS............................................................................................... D
PER-TOF-TOD-25 MINIMUM SPEEDS
PER-TOF-TOD-25-10 SPEEDS LIMITED BY VMCG/VMCA
SPEEDS LIMITED BY VMCG/VMCA......................................................................................................................A
PER-TOF-TOD-25-20 V2 LIMITED BY VMU/VMCA
MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS).................................................................................................. A
PER-TOF-CTA RUNWAY CONTAMINATION
PER-TOF-CTA-10 GENERAL
GENERAL................................................................................................................................................................ A
PER-TOF-CTA-20 DEFINITIONS
DEFINITIONS...........................................................................................................................................................A
EQUIVALENCES..................................................................................................................................................... B
PER-TOF-CTA-30 OPERATIONAL CONDITIONS
OPERATIONAL CONDITIONS................................................................................................................................A
PER-TOF-CTA-40 TAKEOFF PERFORMANCE
PER-TOF-CTA-40-10 TAKEOFF PERFORMANCE
TAKEOFF PERFORMANCE................................................................................................................................... A
PER-TOF-CTA-40-20 TAKEOFF FROM A WET RUNWAY
HOW TO PROCEED............................................................................................................................................... A
NO THRUST REVERSERS OPERATIVE (NO CLEARWAY).................................................................................B
ALL THRUST REVERSERS OPERATIVE (NO CLEARWAY)............................................................................... C
NO THRUST REVERSERS OPERATIVE (WITH CLEARWAY).............................................................................D
ALL THRUST REVERSERS OPERATIVE (WITH CLEARWAY)............................................................................E
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-PLP-TOC P 4/6
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Continued from the previous page
PER-TOF-CTA-40-30 TAKEOFF FROM A CONTAMINATED RUNWAY
TAKEOFF FROM A 6.3 MM (1/4 INCH) WATER COVERED RUNWAY............................................................... A
TAKEOFF FROM A 12.7 MM (1/2 INCH) WATER COVERED RUNWAY............................................................. B
TAKEOFF FROM A 6.3 MM (1/4 INCH) SLUSH COVERED RUNWAY................................................................ C
TAKEOFF FROM A 12.7 MM (1/2 INCH) SLUSH COVERED RUNWAY.............................................................. D
TAKEOFF FROM A COMPACTED SNOW COVERED RUNWAY.........................................................................E
PER-TOF-CTA-40-40 EXAMPLE
TAKEOFF PERFORMANCE ON DRY RUNWAY...................................................................................................A
TAKEOFF PERFORMANCE ON WET RUNWAY.................................................................................................. B
TAKEOFF PERFORMANCE ON RUNWAY COVERED WITH 1/2 INCH SLUSH..................................................C
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-PLP-TOC P 5/6
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
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GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-PLP-TOC P 6/6
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
DEFINITION OF FLEXIBLE TAKEOFF
DEFINITION OF FLEXIBLE TAKEOFF
Ident.: PER-TOF-THR-FLX-10-00001718.0001001 / 28 JAN 11
Applicable to: ALL
In many cases the aircraft takes off with a weight lower than the maximum permissible takeoff
weight. When this happens, it can meet the required performance (runway, second segment,
obstacle,...) with a decreased thrust that is adapted to the weight : this is called FLEXIBLE TAKEOFF
and the thrust is called FLEXIBLE TAKEOFF THRUST.
The use of flexible takeoff thrust saves engine life.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-THR-FLX-10 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-THR-FLX-10 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
USE OF FLEXIBLE TAKEOFF
USE OF FLEXIBLE TAKEOFF
Ident.: PER-TOF-THR-FLX-20-00001719.0001001 / 09 DEC 09
Applicable to: ALL
The pilot can use flexible takeoff when the actual takeoff weight is lower than the maximum
permissible takeoff weight for the actual temperature. The maximum permissible takeoff weight
decreases when temperature increases, so it is possible to assume a temperature at which
the actual takeoff weight would be the limiting one. This temperature is called FLEXIBLE
TEMPERATURE or assumed temperature and is entered in the FADEC via the MCDU PERF TO
page in order to get the adapted thrust.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-THR-FLX-20 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-THR-FLX-20 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
REQUIREMENTS
REQUIREMENTS
Ident.: PER-TOF-THR-FLX-30-00001792.0027001 / 15 MAR 11
Applicable to: ALL
‐ Thrust must not be reduced by more than 40 % of the full rated takeoff thrust.
‐ The flexible takeoff N1 cannot be lower than the Max climb N1 at the same flight conditions.
The FADEC takes the above two constraints into account to determine flexible N1.
The above two constraints also limit the maximum flexible temperature at ISA + 70 (85 °C at sea
level).
‐ The flexible temperature cannot be lower than the flat rating temperature, TREF (ISA +29 up to
2 000 ft) (See Note) , or the actual temperature (OAT).
Note:
TREF being a function of pressure altitude, read it on the takeoff chart.
‐ Flexible takeoff is not permitted on contaminated runways.
‐ The operator should check the maximum thrust (TOGA) at regular intervals in order to detect any
engine deterioration, or maintain an adequate engine performance monitoring program to follow up
the engine parameters.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-THR-FLX-30 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-THR-FLX-30 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
RECOMMENDATION
GENERAL
Ident.: PER-TOF-THR-FLX-40-00001720.0002001 / 15 DEC 15
Applicable to: ALL
• In order to extend engine life and save maintenance costs, it is recommended to use flexible thrust
reduction.
• However, to improve the takeoff performance, the thrust can be increased by selecting a lower
flexible temperature.
Using the same takeoff chart, for a given weight it is possible to :
‐ Select a temperature lower than the maximum determined one and keep the speeds defined at
maximum temperature or,
‐ Move towards the left side (tailwind) of the takeoff chart while remaining within the same
configuration and looking for the same actual takeoff weight at lower temperature.
This produces a lower flexible temperature and, in general, lower takeoff speeds (V1 /VR /V2).
Using one of the two above possibilities, check that the selected temperature is greater than the
actual temperature ( OAT ) and greater than the flat rating temperature (TREF ).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-THR-FLX-40 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
THRUST OPTIONS - FLEXIBLE TAKEOFF
FLIGHT CREW
OPERATING MANUAL
TAKEOFF PROCEDURE
Ident.: PER-TOF-THR-FLX-40-00001721.0001001 / 28 JAN 11
Applicable to: ALL
Depending on environmental takeoff conditions, the following procedure is recommended.
CONDITIONS
Dry or wet well paved runway
High altitude takeoff
Badly paved runway
or
Accelerate stop distance limited
runway
Windshear expected along takeoff
path
Contaminated runway
PROCEDURE
‐ Use the flap setting giving the highest
flexible temperature.
‐ When flexible temperature difference
between two flap settings is low, use the
highest flap setting.
REASON
Extend engine life and save
maintenance costs.
Use CONF2/CONF3
Use CONF2/CONF3
or
Move towards left side of the takeoff chart
Improve comfort
Improve comfort
Improve stopping distance
Use maximum thrust
Maintain acceleration capability
Use maximum thrust
(flex forbidden)
Improve stopping distance
Decrease time on runway.
Required by regulations.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PER-TOF-THR-FLX-40 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
TAKEOFF CHARTS - INTRODUCTION
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS
Ident.: PER-TOF-TOC-05-00001704.0001001 / 21 MAR 11
Applicable to: ALL
Takeoff charts are required to provide performance at takeoff. It is possible to present the charts in
two different ways, one of which is selected by the airline. The different presentations are :
‐ temperature entry (temperature provided in the left column)
‐ weight entry (weight provided in the left column).
Both presentations are described here after. Sections PER-TOF-TOC-10, 12 and 14 are relative to
temperature entry while PER-TOF-TOC-16, 18 and 20 are relative to weight entry.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-05 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
TAKEOFF CHARTS - INTRODUCTION
FLIGHT CREW
OPERATING MANUAL
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GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-05 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
TAKEOFF PERFORMANCE
TAKEOFF PERFORMANCE
Ident.: PER-TOF-TOC-10-10-00001705.0001001 / 23 FEB 11
Applicable to: ALL
Takeoff optimization is calculated for a given runway and its obstacles and for given conditions of
flap setting, temperature, wind and QNH. The calculation produces a maximum permissible takeoff
weight (or a maximum takeoff temperature for an actual weight).
The takeoff thrust produced by the engine varies as follows :
The optimization process calculates the speeds which will produce the maximum takeoff weight.
To do so, it takes into account the different takeoff limitations such as TOD , ASD , TOR, second
segment..., as shown on the figure charts below.
On a typical runway, the performance of a twin engine aircraft, is generally limited by the one engine
out operation at takeoff. The optimum V2 /VS and optimum V1 /VR are consequently unique.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-10-10 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-10-10 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHART DESCRIPTION
GENERAL
Ident.: PER-TOF-TOC-10-20-00001706.0003001 / 03 MAR 11
Applicable to: ALL
The takeoff chart (RTOW : Regulatory Takeoff Weight) is calculated for a specific aircraft version
and for a particular runway specified at the top of the chart. The top of the chart also gives some
information about the runway and lists the calculation assumptions.
The chart is given for 2 different configurations and 5 wind values per configuration. This allows the
crew to select the configuration that gives either :
‐ the highest permissible takeoff weight, or, for a given weight,
‐ the highest flexible temperature.
If different configurations give equivalent performance, the crew should select the configuration
associated with the lowest takeoff speeds.
For each temperature value (and for a given configuration and wind), the chart provides the following
information :
The available limitation codes are :
‐ First segment
‐ Second segment
‐ Runway length
‐ Obstacles
‐ Tire speed
‐ Brake energy
‐ Maximum computation weight
‐ Final takeoff
‐ VMU
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
:
:
:
:
:
:
:
:
:
1
2
3
4
5
6
7
8
9
A
PER-TOF-TOC-10-20 P 1/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS
Ident.: PER-TOF-TOC-10-20-00014608.0001001 / 18 JUL 12
Applicable to: ALL
Each takeoff chart is computed for a given set of conditions (air conditioning, QNH, anti ice...)
specified at the top of the chart. If the actual takeoff conditions are different, the crew must apply
corrections. Two types of correction are available :
‐ Conservative corrections on Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS (to be
used when not provided on the chart).
‐ Corrections (less restrictive) listed on the chart, to be applied as explained below.
Note:
‐ If the RTOW chart is based on the CG being at 25 %, the crew can find the takeoff
performance at a more forward CG by decreasing the takeoff weight by 1 000 kg
(2 200 lb) and increasing V1 , VR and V2 by 1 kt.
‐ 25 % CG is the basic certified limit, on which all takeoff computations are based. To
take into account the operational margins, the above penalties must be applied when
operational CG is forward 27 % CG.
DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART
Ident.: PER-TOF-TOC-10-20-00005368.0001001 / 08 JUL 15
Applicable to: ALL
The corrections are presented on 4 lines:
TVMC is a temperature value given per column. This is a fictitious value that indicates the
temperature above which the speeds are close to a VMCG /VMCA limitation or are VMCG /VMCA
limited.
Note:
The lower two lines may be shaded on certain chart formats.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B to C
PER-TOF-TOC-10-20 P 2/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
MINIMUM SPEEDS
Ident.: PER-TOF-TOC-10-20-00005372.0001001 / 08 JUL 15
Applicable to: ALL
Minimum V1/VR/V2 due to VMCG /VMCA are provided on the bottom right side of the takeoff chart.
They are only applicable in case of speed corrections.
These speeds are conservative. They may be slightly higher than V1/VR/V2 displayed on the takeoff
chart.
FLEX TEMPERATURE INDICATOR
Ident.: PER-TOF-TOC-10-20-00005373.0001001 / 18 FEB 11
Applicable to: ALL
On the temperature entry chart, the temperature column may display asterisks or have a gray band
to indicate temperature values above TMAX and which are flex temperature.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D to E
PER-TOF-TOC-10-20 P 3/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-10-20 P 4/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
ADDITIONAL INFORMATION
ONE ENGINE OUT CLIMB PROCEDURE
Ident.: PER-TOF-TOC-10-30-00001708.0001001 / 23 FEB 11
Applicable to: ALL
The performance given in the chart is consistent with the flight path specified for the aircraft with one
engine out and takes into account significant obstacles.
When the procedure to be followed is not the standard instrument departure, the chart describes a
specific procedure (EOSID).
When the specified procedure requires a turn, except if otherwise stated on the RTOW chart, the turn
should be performed with a maximum bank of 15 ° until the aircraft reaches 1 500 ft or until green
dot.
The acceleration height (or altitude) ensures that the net flight path clears the highest obstacle by
at least 35 ft when accelerating in level flight to green dot speed after an engine failure, in the most
adverse conditions.
TAKEOFF ON A WET RUNWAY
Ident.: PER-TOF-TOC-10-30-00001709.0002001 / 23 FEB 11
Applicable to: ALL
Takeoff charts computed for wet runway with a 15 ft screen height and/or use of reverse thrust may
produce, in some conditions, a maximum takeoff weight (or flexible temperature) higher than that
obtained for a dry runway. It is thus mandatory to compare both charts (dry and wet) and retain the
lower of the two weights (or flexible temperature) and the associated speeds determined for a wet
runway.
Note:
The crew need not compare the charts if the top of the wet runway chart specifies “DRY
CHECK”. (The comparison has already been inserted in the WET runway calculation).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-TOF-TOC-10-30 P 1/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
DESCRIPTION OF TAKEOFF CHART
Ident.: PER-TOF-TOC-10-30-00001710.0006001 / 23 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PER-TOF-TOC-10-30 P 2/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PER-TOF-TOC-10-30 P 3/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PER-TOF-TOC-10-30 P 4/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
EXAMPLE OF TAKEOFF CHART
Ident.: PER-TOF-TOC-10-30-00014705.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PER-TOF-TOC-10-30 P 5/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (TEMPERATURE ENTRY)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PER-TOF-TOC-10-30 P 6/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND SPEEDS
DIRECT CHART READING
Ident.: PER-TOF-TOC-12-10-00001712.0002001 / 23 FEB 11
Applicable to: ALL
The takeoff chart is computed for a given runway under a set of conditions, which are:
‐ OAT
‐ Wind
‐ Configuration
‐ QNH, air conditioning, anti ice...
Two configurations are produced on the chart. This enables the crew to select that giving the highest
permissible takeoff weight. In case of equivalent performance, retain the configuration giving the
lower takeoff speeds.
For a given configuration, enter the chart with the OAT and wind value to determine the maximum
permissible weight. For an OAT or wind value not presented on the chart, interpolate between two
consecutive temperature rows and/or two consecutive wind columns. Conservative OAT or wind
values can also be considered. No extrapolation is allowed.
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS
Ident.: PER-TOF-TOC-12-10-00001713.0002001 / 28 JAN 11
Applicable to: ALL
Retain the maximum takeoff weight, associated configuration and speeds from above.
For conditions different from those of the chart, apply relevant corrections.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-TOF-TOC-12-10 P 1/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS
Ident.: PER-TOF-TOC-12-10-00014706.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
Corrections are given for QNH ≠ 1 013 hPa, air conditioning ON, anti ice ON(Refer to
PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS).
1. For the given wind and temperature conditions, read the maximum takeoff weight.
2. Apply the published weight correction(s) to the maximum takeoff weight (for each correction) to
determine the maximum permissible takeoff weight.
3. Read the speeds associated with the maximum permissible takeoff weight by entering the chart in
the wind column.
EXAMPLE 1
DATA:
OAT
= 25 °C
Head Wind = 10 kt
Air conditioning ON
QNH
= 1 013 hPa
Use the chart (Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART):
Enter the 10 kt head wind column and interpolate for 25 °C, CONF 1+F,
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PER-TOF-TOC-12-10 P 2/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
Maximum TO weight (1 000 kg) air conditioning OFF.............................................................82.1
Enter the 10 kt head wind column and interpolate for 25 °C, CONF 2,
Maximum TO weight (1 000 kg) air conditioning OFF.............................................................82.1
Retain CONF 2 as takeoff configuration as the speeds are lower.
Maximum TO weight (1 000 kg) air conditioning OFF.............................................................82.1
Use the QNH/BLEEDS correction page:(Refer to PER-TOF-TOD-24 EFFECT OF QNH AND
BLEEDS).
For example:
Air conditioning correction........................................................................................................... -1.8
Maximum permissible TO weight (1 000 kg) air conditioning ON.............................................. 80.3
Determine takeoff speeds for 80.3 (1 000 kg) in the 10 kt head wind column CONF 2 (interpolate
when necessary).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PER-TOF-TOC-12-10 P 3/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
V1 = 152 kt, VR = 153 kt, V2 = 158 kt.
CORRECTIONS FOR WET OR CONTAMINATED RUNWAYS
Ident.: PER-TOF-TOC-12-10-00001715.0001001 / 28 JAN 11
Applicable to: ALL
(Refer to PER-TOF-CTA-10 GENERAL)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
PER-TOF-TOC-12-10 P 4/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
CORRECTIONS PRODUCED ON THE RTOW CHART
Ident.: PER-TOF-TOC-12-10-00014707.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
For example: Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART
A description of this correction is given on Refer to PER-TOF-TOC-10-20 DESCRIPTION OF THE
CORRECTIONS ON TAKEOFF CHART. The list of corrections is not exhaustive, however the most
commonly used corrections are wet runway, QNH, air conditioning and/or anti ice. A maximum of
three corrections can be produced on one chart.
To apply the corrections, proceed as follows:
1. Enter the chart with given OAT and wind to determine the maximum takeoff weight before
correction.
2. Apply the first correction:
If OAT is less than or equal to TVMC (line 3), apply ΔW correction from line 1 and ΔV1 /ΔVR /ΔV2
corrections from line 2.
Else, (for OAT greater than TVMC ), apply ΔW correction from line 3 and ΔV1 /ΔVR /ΔV2
corrections from line 4.
3. To combine a second (and third, as applicable) correction:
If OAT is less than or equal to TVMC (line 3), apply ΔW correction from line 1 and ΔV1 /VR /ΔV2
corrections from line 2.
Check that the resulting speeds are higher than the minimum speeds displayed on the RTOW
chart and that V2 is higher than the VMU limited speed (Refer to PER-TOF-TOD-25-20 MINIMUM
V2 LIMITED BY VMU/VMCA (KT IAS)).
If OAT is higher than TVMC (line 3) or if the above speed check is not fulfilled, apply ΔW correction
from line 3 and ΔV1 /ΔVR /ΔV2 corrections from line 4. No speed check is required.
Note:
‐ QNH correction is given for ±10 hPa . It is allowed to extrapolate linearly for greater QNH
deviation.
‐ When using a takeoff chart with failure cases, it is not allowed to combine two failure
cases.
‐ Corrections from the chart must be applied from top to bottom, i.e. in the RTOW on Refer
to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART, apply the wet correction first.
‐ If asterisk or dotted lines appear in the correction boxes, refer to more conservative
corrections provided in the FCOM.
‐ No speed check is required for the first correction. However, if the first influence
correction follows a conservative FCOM correction, a speed check is required.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
PER-TOF-TOC-12-10 P 5/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
EXAMPLE 2
DATA :
CONF 2
OAT
= 25 °C
Head Wind = 10 kt
QNH
= 1 028 hPa
WET runway
In this example, we will consider CONF 2 as takeoff configuration. But same computation has to
be done in CONF 1 and you must retain the best configuration.
Use the chart (Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART)
•
• Enter the 10 kt head wind column and interpolate for 25 °C, CONF 2,
max TO weight (1 000 kg).......................................................................................................82.1
• Read associated speeds as V1 = 156 kt, VR = 157 kt, V2 = 162 kt
• Apply WET correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
PER-TOF-TOC-12-10 P 6/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
For OAT < TVMC (54 °C), ΔW =............................................................................................. -1.2
Intermediate weight (1 000 kg).............................................................................................= 80.9
Associated speeds,
V1 = 156 kt - 10 = 146 kt
VR = 157 kt - 1 = 156 kt
V2 = 162 kt - 1 = 161 kt
(No speed check required for first correction)
• Apply QNH correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
PER-TOF-TOC-12-10 P 7/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
For OAT < TVMC (54 °C), ΔW = 0.2 × 15/10 =.....................................................................+ 0.3
Maximum permissible takeoff weight (1 000 kg).................................................................. = 81.2
Associated speeds,
V1 = 146 kt + 1 × 15/10 = 147 kt
VR = 156 kt + 1 × 15/10 = 158 kt
V2 = 161 kt + 1 × 15/10 = 163 kt
• Check that the speeds are higher than minimum speeds from the chart and from VMU table
(Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)).
It is reminded that if the speed checks are not fulfilled, the corrections must be recalculated
using those provided on lines 3 and 4.
TOW (RTOW)
FCOM correction(s)
Intermediate value
WET Correction
Intermediate value
QNH Correction
Final value
TOW
Takeoff Configuration : 2
V1
VR
156
82.1
82.1
- 1.2
80.9
+ 0.3
81.2
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
156
-10
146
+1
147
←E
157
157
-1
156
+2
158
V2
162
162
-1
161
+2
163
PER-TOF-TOC-12-10 P 8/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
COMBINING CORRECTIONS FROM FCOM AND CHART
Ident.: PER-TOF-TOC-12-10-00014713.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
Proceed as follows:
1. Enter the chart with selected configuration, OAT and wind to read the maximum takeoff weight.
2. Apply corrections from FCOM to determine an intermediate weight. Interpolate associated speeds
for intermediate weight in the same column (same wind and configuration).
3. Apply corrections from RTOW chart as explained above.
EXAMPLE 3
DATA :
CONF 2
OAT
= 25 °C
Head wind = 10 kt
Air conditioning ON
QNH
= 1 028 hPa
WET runway
In this example, we will consider CONF 2 as takeoff configuration. But same computation has to
be done in CONF 1 and you must retain the best configuration.
1. Use the chart (Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PER-TOF-TOC-12-10 P 9/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
Enter the 10 kt head wind column and interpolate for 25 °C, CONF 2,
Max TO weight (1 000 kg) air conditioning OFF..................................................................... 82.1
2. First, apply the QNH/Bleeds correction (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND
BLEEDS).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PER-TOF-TOC-12-10 P 10/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
Max TO weight (1 000 kg) air conditioning OFF..................................................................... 82.1
Air conditioning correction....................................................................................................... - 1.8
Intermediate weight.............................................................................................................. = 80.3
Determine the takeoff speeds for 80.3 (1 000 kg) in the 10 kt head wind column CONF 2
(interpolate when necessary)
V1 = 152 kt , VR = 153 kt , V2 = 158 kt
3. Apply WET correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PER-TOF-TOC-12-10 P 11/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
For OAT < TVMC (54 °C), ΔW =............................................................................................. -1.2
Intermediate weight.............................................................................................................. = 79.1
Associated speeds,
V1 = 152 kt - 10 = 142 kt
VR = 153 kt - 1 = 152 kt
V2 = 158 kt - 1 = 157 kt
(No speed check required for first correction).
Apply QNH correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PER-TOF-TOC-12-10 P 12/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
For OAT < TVMC (54 °C), ΔW = 0.2 × 15/10 =......................................................................+0.3
Max permissible takeoff weight............................................................................................ = 79.4
Associated speed,
V1 = 142 kt + 1 × 15/10 = 143 kt
VR = 152 kt + 1 × 15/10 = 154 kt
V2 = 157 kt + 1 × 15/10 = 159 kt
Check that the speeds are higher than minimum speeds from the chart and from VMU table (Refer
to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS))(it is reminded that if
the speed checks are not fulfilled, the corrections must be recalculated using those provided on
lines 3 and 4).
Since the speed check is fulfilled:
Max permissible takeoff weight = 79.4 (1 000 kg)
V1 = 143 kt, VR = 154 kt, V2 = 159 kt.
TOW (RTOW)
FCOM correction(s)
Intermediate value
WET Correction
Intermediate value
QNH Correction
TOW
Takeoff Configuration : 2
V1
VR
82.1
- 1.8
80.3
- 1.2
79.1
+ 0.3
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
152
-10
142
+1
←F→
V2
153
158
-1
-1
152
157
+2
+2
Continued on the following page
PER-TOF-TOC-12-10 P 13/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Final value
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
TOW
Continued from the previous page
Takeoff Configuration : 2
V1
VR
V2
143
154
159
79.4
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F
PER-TOF-TOC-12-10 P 14/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
EXTRAPOLATION
EXTRAPOLATION
Ident.: PER-TOF-TOC-12-30-00001716.0002001 / 01 MAR 11
Applicable to: ALL
For a takeoff weight lower than those displayed on the chart, associated speeds are calculated as
follows :
1. For given configuration and wind, note the speeds associated with the takeoff weight in the row
displaying the highest permissible temperature.
2. Apply speed corrections provided at the bottom of the RTOW chart to V1 , VR and V2 limited to
the minimum speeds.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-12-30 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-12-30 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
MAXIMUM STRUCTURAL TAKEOFF WEIGHT
MAXIMUM STRUCTURAL TAKEOFF WEIGHT
Ident.: PER-TOF-TOC-12-40-00001717.0001001 / 18 MAR 11
Applicable to: ALL
The maximum structural takeoff weight is a weight limitation depending on the aircraft. This limitation
is provided in the Flight Manual and in Refer to LIM-AG-WGHT Weight Limitations. Compare the
maximum structural takeoff weight to the maximum permissible takeoff weight computed for given
conditions and retain the lower of the two values.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-12-40 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-12-40 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
SUMMARY
SUMMARY
Ident.: PER-TOF-TOC-12-50-00006313.0001001 / 11 MAR 11
Applicable to: ALL
The following flow diagram gives the different steps to follow.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-12-50 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (TEMPERATURE ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-12-50 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE AND SPEEDS
GENERAL
Ident.: PER-TOF-TOC-14-10-00001722.0002001 / 17 MAR 11
Applicable to: ALL
Before determining the flexible temperature, calculate the maximum permissible takeoff weight (see
previous section) and ensure that the actual takeoff weight is lower than the determined maximum
takeoff weight.
• Enter the RTOW chart with the wind condition to interpolate for the actual takeoff weight. Read the
flexible temperature in the temperature column corresponding to the actual weight.
• Repeat this process for the other configuration available. Select the configuration giving the
highest flexible temperature.
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS
Ident.: PER-TOF-TOC-14-10-00001723.0001001 / 03 MAR 14
Applicable to: ALL
When the takeoff conditions are different from those provided on the chart, apply the associated
corrections.
Note:
‐ If the RTOW chart is based on the CG being at 25 %, the crew can determine the flexible
temperature at a more forward CG by decreasing the flexible temperature by 2 °C. V1 ,
VR and V2 must be increased by 1 kt.
‐ 25 % CG is the basic certified limit, on which all takeoff computations are based. To
take into account the operational margins, the above penalties must be applied when
operational CG is forward 27 % CG.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-TOF-TOC-14-10 P 1/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS
Ident.: PER-TOF-TOC-14-10-00014714.0001001 / 29 JUL 16
Applicable to: ALL
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS
The following data and graphs are for example only, and are not for operational use. Even if the
data in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
Corrections are given for QNH ≠ 1 013 hPa , air conditioning ON, anti ice ON (Refer to
PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS).
1. For a given takeoff weight, wind condition and selected configuration, determine the flexible
temperature. Retain the takeoff speeds associated with the actual weight.
2. Apply the published temperature correction. To combine two or more corrections, add the
different corrections and apply to temperature value.
(No speed corrections required).
EXAMPLE 2
DATA :
Actual takeoff weight = 75 600 kg
Head wind
= 10 kt
Air conditioning ON
QNH
= 1 013 hPa
Use the chart: (Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART).
Determine the maximum permissible takeoff weight. The actual weight being lower than the
maximum one, flexible takeoff is possible.
Enter the 10 kt head wind column and interpolate for 75 600 kg, CONF 1+F,
Flexible temperature............................................................................................................. 53 °C
Enter the 10 kt head wind column and interpolate for 75 600 kg, CONF 2,
Flexible temperature............................................................................................................. 53 °C
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PER-TOF-TOC-14-10 P 2/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Retain CONF 2 as the speeds are lower.
Takeoff speeds are V1 = 149 kt, VR = 150 kt, V2 = 155 kt
Flexible temperature with air conditioning OFF.................................................................... 53 °C
Use the QNH/Bleeds corrections:(Refer to PER-TOF-TOD-24 EFFECT OF QNH AND
BLEEDS).
For example:
Air conditioning correction ................................................................................................... -3 °C
Flexible temperature...........................................................................................................= 50 °C
Check that OAT/TREF < flex temperature ≤ TMAXFLEX
TMAXFLEX is specified in LIM-70.
CORRECTIONS FOR WET RUNWAY
Ident.: PER-TOF-TOC-14-10-00001725.0001001 / 28 JAN 11
Applicable to: ALL
CORRECTIONS FOR WET RUNWAY
(Refer to PER-TOF-CTA-10 GENERAL)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
PER-TOF-TOC-14-10 P 3/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
CORRECTIONS PRODUCED ON THE RTOW CHART
Ident.: PER-TOF-TOC-14-10-00014717.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
For a description of this correction Refer to PER-TOF-TOC-10-20 DESCRIPTION OF THE
CORRECTIONS ON TAKEOFF CHART. The list of corrections is not exhaustive, however the most
commonly used corrections are wet runway, QNH, air conditioning and/or anti-icing. A maximum of
three corrections can be produced on one chart.
To apply the correction, proceed as follows:
1. Enter the chart with wind and selected configuration. Interpolate for actual takeoff weight. Read
flexible temperature associated with this weight.
2. Apply the first correction:
Apply ΔTflex correction and apply speed corrections (ΔV1 / ΔVR / ΔV2).
Check that the resulting V2 is higher than the VMU Limited speed (Refer to PER-TOF-TOD-25-20
MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)). If the speed checks are not fulfilled, flexible
takeoff is not possible. Set TOGA thrust and retain the speeds associated with maximum
permissible takeoff weight or the speeds read in the chart of the actual weight if they are all lower.
No speed correction is required for QNH and bleeds influence (Not applicable to maximum takeoff
weight determination).
3. To combine a second and/or a third correction, proceed as per point 2, except that also the
resulting speeds must be checked higher than the minimum speed displayed on the RTOW chart.
4. Check that the final flexible temperature is:
‐ higher than OAT and TREF
‐ limited to TMAXFLEX
If the check is fulfilled, retain final flexible temperature as the one to be inserted in the MCDU.
If the check is not fulfilled, (final flexible temperature lower than OAT or TREF), no flexible
takeoff is possible.
Use TOGA thrust and retain speeds that have been calculated for the maximum permissible
takeoff weight. (Refer to PER-TOF-TOC-14-20 FLEXIBLE TAKEOFF NOT POSSIBLE)
Note:
‐ QNH correction is given for ±10 hPa. It is allowed to extrapolate linearly for greater QNH
deviation.
‐ Corrections from the chart must be applied from top to bottom, i.e. in the RTOW on Refer
to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART, apply the wet influence first.
Note:
‐ If asterisk or dotted lines appear in the influence boxes, refer to more conservative
corrections provided in the FCOM.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
PER-TOF-TOC-14-10 P 4/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
EXAMPLE 5
DATA :
CONF 2
Actual takeoff weight = 75 600 kg
Head wind
= 10 kt
WET runway
Air conditioning OFF
QNH
= 1 023 hPa
In this example, we will consider CONF 2 as takeoff configuration. But same computation has to
be done in CONF 1 and you must retain the best configuration.
Use the chart:(Refer to PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART).
Determine the maximum permissible takeoff weight (see example 2). The actual weight being
lower than the maximum one, flexible takeoff is possible.
Enter the 10 kt head wind column and interpolate for 75 600 kg, CONF 2,
Flexible temperature................................................................................................................. 53 °C
Takeoff speeds are V1 = 149 kt, VR = 150 kt, V2 = 155 kt
Apply WET correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
PER-TOF-TOC-14-10 P 5/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
ΔTflex =..................................................................................................................................... -2 °C
Intermediate flex temperature................................................................................................ = 51 °C
Associated speeds,
V1 = 149 kt – 10 = 139 kt
VR = 150 kt – 1 = 149 kt
V2 = 155 kt – 1 = 154 kt
Check that V2 is higher than the VMU. (Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY
VMU/VMCA (KT IAS)).
Apply QNH correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
PER-TOF-TOC-14-10 P 6/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
ΔTflex =...................................................................................................................................... 0 °C
Maximum flexible temperature............................................................................................... = 51 °C
No speed correction is required for QNH and bleed influence.
Takeoff speeds are V1 = 139 kt, VR = 149 kt, V2 = 154 kt
Check that OAT/TREF < flex temperature ≤ TMAXFLEX
TMAXFLEX is specified in LIM-70.
Chart temperature
FCOM correction(s)
Intermediate value
WET Correction
Intermediate value
QNH Correction
Final value
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Tflex
53
Takeoff Configuration: 1 + F
V1
VR
149
150
V2
155
53
149
150
155
51
139
149
154
51
139
149
154
-2
0
←E
-10
0
-1
0
-1
0
PER-TOF-TOC-14-10 P 7/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
COMBINING CORRECTIONS FROM FCOM AND CHART
Ident.: PER-TOF-TOC-14-10-00014718.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
1. Apply corrections from FCOM (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS).
2. Apply corrections from the RTOW chart.
Apply speed corrections except for QNH and bleed influences.
EXAMPLE 6
DATA:
CONF 2
Actual takeoff weight = 75 600 kg
Head wind
= 10 kt
Air conditioning ON
QNH
= 1 028 hPa
WET runway
In this example, we will consider CONF 2 as takeoff configuration. But same computation has to
be done in CONF 1 and you must retain the best configuration.
Use the chart (Refer to PER-TOF-TOC-10-20 DESCRIPTION OF THE CORRECTIONS
ON TAKEOFF CHART). Determine the maximum permissible takeoff weight (Refer to
PER-TOF-TOC-12-10 COMBINING CORRECTIONS FROM FCOM AND CHART: example 3).
The actual weight being lower than the maximum one, flexible takeoff is possible.
Enter the 10 kt head wind column and interpolate for 75 600 kg, CONF 2,
Flexible temperature................................................................................................................. 53 °C
Takeoff speeds are V1 = 149 kt, VR = 150 kt, V2 = 155 kt
First, apply the correction (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS).
Flexible temperature with air conditioning OFF....................................................................... 53 °C
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PER-TOF-TOC-14-10 P 8/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Air conditioning correction......................................................................................................... -3 °C
Intermediate flexible temperature...........................................................................................= 50 °C
No speed correction.
Apply WET correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PER-TOF-TOC-14-10 P 9/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
For flexible temperature < TVMC (54 °C), ΔTflex = ................................................................ -2 °C
Intermediate flex temperature................................................................................................ = 48 °C
Associated speeds,
V1 = 149 kt - 10 = 139 kt
VR = 150 kt - 1 = 149 kt
V2 = 155 kt - 1 = 154 kt
Check that V2 is higher than the VMU (Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY
VMU/VMCA (KT IAS)).
Apply QNH correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PER-TOF-TOC-14-10 P 10/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
For flexible temperature < TVMC (54 °C), ΔTflex =................................................................... 0 °C
Flexible temperature...............................................................................................................= 48 °C
No speed correction is required for QNH and bleed influence.
Takeoff speeds are,
V1 = 139 kt
VR = 149 kt
V2 = 154 kt
Check that OAT/TREF < flex temperature ≤ TMAXFLEX.
TMAXFLEX is specified in LIM-70.
Chart temperature
FCOM correction(s)
Intermediate value
WET Correction
Intermediate value
QNH Correction
Final value
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
Tflex
53
-3
Takeoff Configuration : 2
V1
VR
149
150
0
0
V2
155
0
50
149
150
155
48
139
149
154
48
139
149
154
-2
0
←F
-10
0
-1
0
-1
0
PER-TOF-TOC-14-10 P 11/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-14-10 P 12/12
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
FLEXIBLE TAKEOFF NOT POSSIBLE
FLEXIBLE TAKEOFF NOT POSSIBLE
Ident.: PER-TOF-TOC-14-20-00001726.0001001 / 30 SEP 13
Applicable to: ALL
In some cases when the actual takeoff weight is lower than the maximum permissible takeoff
weight, but the flexible temperature is lower than TREF or OAT , flexible takeoff is not possible. It is
mandatory to use TOGA thrust.
For speed determination:
‐ You can retain the speeds that have been calculated for the maximum permissible takeoff weight;
OR
‐ You can retain the speeds associated with the actual takeoff weight provided they are all lower
than the speeds calculated for the maximum permissible takeoff weight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-14-20 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-14-20 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
FLEXIBLE TAKEOFF POSSIBLE BUT NOT USED
FLEXIBLE TAKEOFF POSSIBLE BUT NOT USED
Ident.: PER-TOF-TOC-14-25-00015228.0001001 / 30 SEP 13
Applicable to: ALL
If the flexible takeoff is possible, but the flight crew elects to perform the takeoff with TOGA thrust, for
speed determination:
‐ You can retain the speeds that have been calculated for the maximum permissible takeoff weight;
OR
‐ You can retain the speeds associated with the actual takeoff weight provided they are all lower
than the speeds calculated for the maximum permissible takeoff weight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-14-25 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-14-25 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
SUMMARY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-14-30 P 1/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
SUMMARY
Ident.: PER-TOF-TOC-14-30-00006034.0001001 / 24 MAR 11
Applicable to: ALL
The flow diagram gives the different steps to follow.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-TOF-TOC-14-30 P 2/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-TOF-TOC-14-30 P 3/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (TEMPERATURE ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-14-30 P 4/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
TAKEOFF PERFORMANCE
TAKEOFF PERFORMANCE
Ident.: PER-TOF-TOC-16-10-00001727.0001001 / 23 JUN 15
Applicable to: ALL
Takeoff optimization is calculated for a given runway and its obstacles and for given conditions of
flap setting, temperature, wind and QNH. The calculation produces a maximum permissible takeoff
weight (or a maximum takeoff temperature for an actual weight).
The takeoff thrust produced by the engine varies as follows :
The optimization process calculates the speeds which will produce the maximum takeoff weight.
To do so, it takes into account the different takeoff limitations such as TOD , ASD , TOR, second
segment..., as shown on the charts below.
On a typical runway, the performance of a twin engine aircraft, is generally limited by the one engine
out operation at takeoff. The optimum V2 /VS and optimum V1 /VR are consequently unique.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-16-10 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-16-10 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHART DESCRIPTION
GENERAL
Ident.: PER-TOF-TOC-16-20-00001728.0003001 / 28 FEB 11
Applicable to: ALL
The takeoff chart (RTOW : Regulatory Takeoff Weight) is calculated for a specific aircraft version
and for a particular runway specified at the top of the chart. The top of the chart also gives some
information about the runway and lists the calculation assumptions.
The chart is given for 2 different configurations and 4 wind values per configuration. This allows the
crew to select the configuration that gives either :
‐ the highest permissible takeoff weight, or, for a given weight,
‐ the highest flexible temperature.
If different configurations give equivalent performance, the crew should select the configuration
associated with the lowest takeoff speeds.
The left column of the chart contains weight entry. For each weight entry (and for a given
configuration and wind), the chart provides the following information :
Note:
The takeoff weight is the sum of the weight entry and the delta weight.
The available limitation codes are :
‐ First segment
‐ Second segment
‐ Runway length
‐ Obstacles
‐ Tire speed
‐ Brake energy
‐ Maximum computation weight
‐ Final takeoff
‐ VMU
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
:
:
:
:
:
:
:
:
:
1
2
3
4
5
6
7
8
9
A
PER-TOF-TOC-16-20 P 1/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS
Ident.: PER-TOF-TOC-16-20-00001729.0105001 / 19 DEC 14
Applicable to: ALL
Each takeoff chart is computed for a given set of conditions (air conditioning, QNH, anti ice...)
specified at the top of the chart. If the actual takeoff conditions are different, the crew must apply
corrections.
Two types of corrections are available :
‐ Conservative corrections (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS) (to be
used when not provided on the chart).
‐ Corrections (less restrictive) listed on the chart, to be applied as explained below.
Note:
1. If the RTOW chart is based on the CG being at 25 %, the crew can find the takeoff
performance at a more forward CG by decreasing the takeoff weight by 1 000 kg
(2 200 lb) and increasing V1 , VR and V2 by 1 kt.
2. 25 % CG is the basic certified limit, on which all takeoff computations are based.
To take into account the operational margins, the above penalties must be applied when
operational CG is forward 27 % CG.
DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART
Ident.: PER-TOF-TOC-16-20-00006633.0001001 / 08 JUL 15
Applicable to: ALL
The corrections are presented on 4 lines :
TVMC is a temperature value given per column. This is a fictitious value that indicates the
temperature above which the speeds are close to a VMCG /VMCA limitation or are VMCG /VMCA
limited.
Note:
The lower two lines may be shaded on certain chart formats.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B to C
PER-TOF-TOC-16-20 P 2/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
MINIMUM SPEED
Ident.: PER-TOF-TOC-16-20-00006634.0001001 / 08 JUL 15
Applicable to: ALL
Minimum V1 /VR /V2 due to VMCG /VMCA are provided on the bottom right side of the takeoff chart.
They are only applicable in case of speed corrections.
These speeds are conservative. They may be slightly higher than V1 /VR /V2 displayed on the
takeoff chart.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PER-TOF-TOC-16-20 P 3/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-16-20 P 4/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
ADDITIONAL INFORMATION
ONE ENGINE OUT CLIMB PROCEDURE
Ident.: PER-TOF-TOC-16-30-00001730.0001001 / 10 DEC 09
Applicable to: ALL
The performance given in the chart is consistent with the flight path specified for the aircraft with one
engine out and takes into account significant obstacles.
When the procedure to be followed is not the standard instrument departure, the chart describes a
specific procedure (EOSID).
When the specified procedure requires a turn, except if otherwise stated on the RTOW chart, the turn
should be performed with a maximum bank of 15 ° until the aircraft reaches 1 500 ft or until green
dot.
The acceleration height (or altitude) ensures that the net flight path clears the highest obstacle by
at least 35 ft when accelerating in level flight to green dot speed after an engine failure, in the most
adverse conditions.
TAKEOFF ON A WET RUNWAY
Ident.: PER-TOF-TOC-16-30-00001731.0002001 / 10 DEC 09
Applicable to: ALL
Takeoff charts computed for wet runway with a 15 ft screen height and/or use of reverse thrust may
produce, in some conditions, a maximum takeoff weight (or flexible temperature) higher than that
obtained for a dry runway. It is thus mandatory to compare both charts (dry and wet) and retain the
lower of the two weights (or flexible temperature) and the associated speeds determined for a wet
runway.
Note:
The crew need not compare the charts if the top of the wet runway chart specifies “DRY
CHECK”. (The comparison has already been inserted in the WET runway calculation).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-TOF-TOC-16-30 P 1/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
RTOW CHARTS - COMPLEMENTARY INFORMATION
Ident.: PER-TOF-TOC-16-30-00001732.0063001 / 10 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PER-TOF-TOC-16-30 P 2/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PER-TOF-TOC-16-30 P 3/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PER-TOF-TOC-16-30 P 4/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
RTOW EXAMPLE
Ident.: PER-TOF-TOC-16-30-00014719.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PER-TOF-TOC-16-30 P 5/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - GENERAL (WEIGHT ENTRY)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PER-TOF-TOC-16-30 P 6/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
DETERMINATION OF MAXIMUM TAKEOFF WEIGHT AND SPEEDS
GENERAL
Ident.: PER-TOF-TOC-18-10-00001734.0002001 / 10 DEC 09
Applicable to: ALL
The takeoff chart is computed for a given runway under a set of conditions, which are :
‐ OAT
‐ Wind
‐ Configuration
‐ QNH, air conditioning, anti ice...
Two configurations are produced on the chart. This enables the crew to select that giving the highest
permissible takeoff weight.
In case of equivalent performance, retain the configuration giving the lower takeoff speeds.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-18-10 P 1/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
MTOW DETERMINATION
Ident.: PER-TOF-TOC-18-10-00013648.0002001 / 01 MAR 11
Applicable to: ALL
Enter the chart with the given configuration and actual wind column reading the temperature value.
This temperature value stands for the OAT . Read the maximum takeoff weight corresponding to
the actual OAT. Note that it is allowed to interpolate between two consecutive lines to obtain the
maximum takeoff weight.
It is reminded that the takeoff weight is the sum of the weight entry and the delta weight. Similarly
determine the takeoff speeds associated with the maximum takeoff weight.
In some cases, it may happen that the first temperature value (displayed for the highest weight entry)
is higher than OAT. In this case, it is allowed to extrapolate the weight value to avoid unnecessary
penalty. Use the Grad 1/Grad 2 gradients provided at the bottom of the corresponding column.
CORRECTION TO WEIGHT
Grad 1/Grad 2 are gradients provided for both sides of the flat rating temperature (TREF).
Grad 1 applies to temperatures below TREF and Grad 2 applies above TREF.
Read the lowest temperature of the column (corresponding to the highest weight entry).
If the lowest temperature and OAT are above TREF.
Obtain weight increment by multiplying Grad 2 by the difference in temperature between OAT
and lowest temperature. Add this weight increment to the maximum takeoff weight calculated
for the lowest temperature.
If the lowest temperature and OAT are below TREF.
Obtain weight increment by multiplying Grad 1 by the difference in temperature between OAT
and lowest temperature. Add this weight increment to the maximum takeoff weight calculated
for the lowest temperature.
If OAT is below TREF and lowest temperature is above TREF.
The weight increment is calculated in two steps. Step one is multiplying Grad 2 by temperature
difference between lowest temperature and TREF. Step two is multiplying Grad 1 by
temperature difference between TREF and OAT. Add results from step one and two to
maximum takeoff weight calculated for lowest temperature.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-TOF-TOC-18-10 P 2/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
Note:
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Use the weight gradients only to extrapolate above the maximum weight shown in the
RTOW chart. They are not valid for interpolation between two boxes, between filled
boxes or between one filled and one blank box.
Repeat the above process for the other available configuration and retain the configuration giving
the highest takeoff weight.
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS
Ident.: PER-TOF-TOC-18-10-00001736.0002001 / 11 FEB 11
Applicable to: ALL
Retain the maximum takeoff weight, associated configuration and speeds from above.
For conditions different from those of the chart, apply relevant corrections.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C
PER-TOF-TOC-18-10 P 3/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS
Ident.: PER-TOF-TOC-18-10-00014720.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
Corrections are given for QNH ≠ 1 013 hPa, air conditioning ON, anti ice ON.
1. For the given wind and temperature conditions, determine the maximum takeoff weight.
2. Apply the published weight correction(s) to the maximum takeoff weight (for each correction) to
determine the maximum permissible takeoff weight.
3. Read the speeds associated with the maximum permissible takeoff weight by entering the chart in
the wind column with the retained weight value.
EXAMPLE A
DATA :
OAT
= 25 °C
Head Wind = 10 kt
Air conditioning ON
QNH
= 1 013 hPa
Use the chart from (Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PER-TOF-TOC-18-10 P 4/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Enter the 10 kt head wind column CONF 1 + F, to read for 25 °C
The lowest temperature of the column is 45 °C, use Grad 1/Grad 2 to extrapolate the maximum
takeoff weight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
PER-TOF-TOC-18-10 P 5/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
TRef value is available on the bottom of this table.
Here, TRef is equal to 44 °C.
MAX TO weight (1 000 kg) air conditioning OFF = 80.6 + 0.46 × 1 + 0.06 × 19 = 82.2
Enter the 10 kt head wind column CONF 2, to read for 25 °C
The lowest temperature of the column is 46 °C, use Grad 1/Grad 2 to extrapolate the maximum
takeoff weight.
MAX TO weight (1 000 kg) air conditioning OFF = 80.3 + 0.47 × 2 + 0.05 × 19 = 82.1
Retain CONF 1 + F as takeoff configuration.
Maximum TO weight (1 000 kg) air conditioning OFF................................................................ 82.2
Use the QNH/BLEEDS correction page (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND
BLEEDS):
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
PER-TOF-TOC-18-10 P 6/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Air conditioning correction............................................................................................................ -1.8
Maximum permissible TO weight (1 000 kg) air conditioning ON............................................ = 80.4
Determine takeoff speeds for 80.4 (1 000 kg) in the 10 kt head wind column CONF 1 + F
(interpolate when necessary).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D→
PER-TOF-TOC-18-10 P 7/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
V1 = 155 kt, VR = 156 kt, V2 = 158 kt
CORRECTIONS FOR WET OR CONTAMINATED RUNWAYS
Ident.: PER-TOF-TOC-18-10-00004071.0001001 / 10 DEC 09
Applicable to: ALL
(Refer to PER-TOF-CTA-10 GENERAL)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← D to E
PER-TOF-TOC-18-10 P 8/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
CORRECTIONS PRODUCED ON THE RTOW CHART
Ident.: PER-TOF-TOC-18-10-00014721.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
(Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE).
A description of this correction is given in PER-TOF-TOC-16-20 (Refer to PER-TOF-TOC-16-20
DESCRIPTION OF THE CORRECTIONS ON TAKEOFF CHART). The list of corrections is not
exhaustive, however the most commonly used corrections are wet runway, QNH, air conditioning
and/or anti ice. A maximum of three corrections can be produced on one chart.
To apply the corrections, proceed as follows:
1. Determine the maximum takeoff weight before correction for the given OAT and wind condition.
2. Apply the first correction:
If OAT is less than or equal to TVMC (line 3), apply ΔW correction from line 1 and ΔV1 /ΔVR /ΔV2
corrections from line 2.
Else, (for OAT greater than TVMC ), apply ΔW correction from line 3 and ΔV1 /ΔVR /ΔV2
corrections from line 4.
3. To combine a second (and third, as applicable) correction:
If OAT is less than or equal to TVMC (line 3), apply ΔW correction from line 1 and ΔV1 /ΔVR /ΔV2
corrections from line 2.
Check that the resulting speeds are higher than the minimum speeds displayed on the RTOW
chart and that V2 is higher than the VMU limited speed (Refer to PER-TOF-TOD-25-20 MINIMUM
V2 LIMITED BY VMU/VMCA (KT IAS)).
If OAT is higher than TVMC (line 3) or if the above speed check is not fulfilled, apply ΔW correction
from line 3 and ΔV1 /ΔVR /ΔV2 corrections from line 4. No speed check is required.
Note:
‐ QNH correction is given for ±10 hPa. It is allowed to extrapolate linearly for greater QNH
deviation.
‐ When using a takeoff chart with failure cases, it is not allowed to combine two failure
cases.
‐ Corrections from the chart must be applied from top to bottom, i.e. in the RTOW (Refer to
PER-TOF-TOC-16-30 RTOW EXAMPLE), apply the wet correction first.
‐ If asterisk or dotted lines appear in the correction boxes, refer to more conservative
corrections provided in the FCOM.
‐ No speed check is required for the first correction. However, if the first influence
correction follows a conservative FCOM correction, a speed check is required.
EXAMPLE B
DATA :
CONF 1+F
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PER-TOF-TOC-18-10 P 9/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
OAT
=
Head wind
=
QNH
=
WET runway
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
45 °C
10 kt
998 hPa
In this example, we will consider CONF 1+F as takeoff configuration. But same computation has to
be done in CONF 2 and you must retain the best configuration.
Use the chart Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE).
• Enter the 10 kt head wind column CONF 1+F, to read for 45 °C
max TO weight (1 000 kg).......................................................................................................80.6
• Read associated speeds as V1 = 155 kt, VR = 156 kt, V2 = 158 kt
• Apply WET correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PER-TOF-TOC-18-10 P 10/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
For OAT < TVMC (69 °C), ΔW =........................................................................................... – 0.7
Intermediate weight (1 000 kg).............................................................................................= 79.9
Associated speeds,
V1 = 155 kt – 8 = 147 kt
VR = 156 kt – 2 = 154 kt
V2 = 158 kt – 2 = 156 kt
(No speed check required for first correction)
• Apply QNH correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PER-TOF-TOC-18-10 P 11/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
For OAT < TVMC (61 °C), ΔW = – 0.7 × 15/10 =.....................................................................– 1
Maximum permissible takeoff weight (1 000 kg).................................................................. = 78.9
Associated speeds,
V1 = 147 kt – 1 × 15/10 = 145 kt
VR = 154 kt – 1 × 15/10 = 153 kt
V2 = 156 kt – 1 × 15/10 = 155 kt
• Check that the speeds are higher than minimum speeds from the chart and from VMU table
(Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)).
It is reminded that if the speed checks are not fulfilled, the corrections must be recalculated
using those provided on lines 3 and 4.
TOW (RTOW)
FCOM correction(s)
Intermediate value
WET Correction
Intermediate value
QNH Correction
Final value
TOW
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
80.6
80.6
- 0.7
79.9
-1
78.9
←F
Takeoff Configuration: 1 + F
V1
VR
155
156
155
-8
147
-2
145
156
-2
154
-1
153
V2
158
158
-2
156
-1
155
PER-TOF-TOC-18-10 P 12/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
COMBINING CORRECTIONS FROM FCOM AND CHART
Ident.: PER-TOF-TOC-18-10-00014722.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
Proceed as follows:
1. Determine the maximum takeoff weight by entering the chart with selected configuration, OAT and
wind.
2. Apply corrections from FCOM to determine an intermediate weight. Interpolate associated speeds
for intermediate weight in the same column (same wind and configuration).
3. Apply corrections from RTOW chart as explained above.
EXAMPLE C
DATA
:
OAT = 25 °C
CONF 1+F
Head wind = 10 kt
Air conditioning ON
QNH = 998 hPa
WET runway
In this example, we will consider CONF 1+F as takeoff configuration. But same computation has to
be done in CONF 2 and you must retain the best configuration.
1. Use the chart (Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
G→
PER-TOF-TOC-18-10 P 13/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Enter the 10 kt head wind column CONF 1 + F, to read for 25 °C
MAX TO weight (1 000 kg) air conditioning OFF = 80.6 + 0.46 × 1 + 0.06 × 19 = 82.2
In this example, Tref is equal to 44 °C, therefore the correction for 25 °C is 19 × GRAD1
correction (60kg) + 1 × GRAD2 correction(460kg).
2. First, apply the QNH/BLEEDS correction (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND
BLEEDS).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
PER-TOF-TOC-18-10 P 14/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Max TO weight (1 000 kg) air conditioning OFF..................................................................... 82.2
Air conditioning correction........................................................................................................ -1.8
Intermediate weight.............................................................................................................. = 80.4
Interpolate takeoff speeds for 80.4 (1 000 kg) in the 10 kt head wind column,
V1 = 155 kt, VR = 156 kt, V2 = 158 kt
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
PER-TOF-TOC-18-10 P 15/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
3. Apply WET correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
PER-TOF-TOC-18-10 P 16/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
For OAT < TVMC (69 °C), ΔW =............................................................................................. -0.7
Intermediate weight.............................................................................................................. = 79.7
Associated speeds,
V1 = 155 kt - 8 = 147 kt
VR = 156 kt - 2 = 154 kt
V2 = 158 kt - 2 = 156 kt
Apply QNH correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←G→
PER-TOF-TOC-18-10 P 17/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
For OAT < TVMC (61 °C), ΔW = -0.7 × 15/10 =........................................................................ -1
Maximum permissible takeoff weight....................................................................................= 78.7
Associated speed,
V1 = 147 kt - 1 × 15/10 = 145 kt
VR = 154 kt - 1 × 15/10 = 153 kt
V2 = 156 kt - 1 × 15/10 = 155 kt
Check that the speeds are higher than minimum speeds from the chart and from VMU table (Refer
to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)).It is reminded that if
the speed checks are not fulfilled, the corrections must be recalculated using those provided on
lines 3 and 4.
Since the speed check is fulfilled:
MAX permissible takeoff weight = 78.7 (1 000 kg)
V1 = 145 kt, VR = 153 kt, V2 = 155 kt.
TOW (RTOW)
FCOM correction(s)
Intermediate value
Takeoff Configuration: 1 + F
V1
VR
TOW
82.2
-1.8
80.4
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
155
←G→
V2
156
158
Continued on the following page
PER-TOF-TOC-18-10 P 18/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
WET Correction
Intermediate value
QNH Correction
Final value
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Continued from the previous page
Takeoff Configuration: 1 + F
V1
VR
V2
-9
-2
-2
TOW
-0.7
79.7
-1
154
156
145
153
155
-2
78.7
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
147
←G
-1
-1
PER-TOF-TOC-18-10 P 19/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-18-10 P 20/20
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
EXTRAPOLATION
EXTRAPOLATION
Ident.: PER-TOF-TOC-18-20-00001740.0002001 / 08 MAR 11
Applicable to: ALL
For OAT lower than the lowest temperature value of a wind column, it is possible to obtain a higher
maximum permissible takeoff weight by using Grad 1/Grad 2 values. Refer to PER-TOF-TOC-18-10
MTOW DETERMINATIONfor more details.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-18-20 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-18-20 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
MAXIMUM STRUCTURAL TAKEOFF WEIGHT
MAXIMUM STRUCTURAL TAKEOFF WEIGHT
Ident.: PER-TOF-TOC-18-30-00001741.0001001 / 01 MAR 11
Applicable to: ALL
The maximum structural takeoff weight is a weight limitation depending on the aircraft. This limitation
is provided in the Flight Manual and in the limitation chapter (Refer to LIM-AG-WGHT Weight
Limitations).
Compare the maximum structural takeoff weight to the maximum permissible takeoff weight
computed for given conditions and retain the lower of the two values.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-18-30 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-18-30 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
SUMMARY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-18-40 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - MTOW CALCULATION (WEIGHT ENTRY)
SUMMARY
Ident.: PER-TOF-TOC-18-40-00006114.0001001 / 17 MAR 11
Applicable to: ALL
The following flow diagram gives the different steps to follow.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-18-40 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
DETERMINATION OF FLEXIBLE TAKEOFF TEMPERATURE AND SPEEDS
GENERAL
Ident.: PER-TOF-TOC-20-10-00013509.0002001 / 23 FEB 11
Applicable to: ALL
Before determining the flexible temperature, calculate the maximum permissible takeoff weight (see
previous section) and ensure that the actual takeoff weight is lower than the determined maximum
takeoff weight.
‐ For a given configuration and wind value, enter the RTOW chart with the actual takeoff weight
to read the flexible temperature and associated speeds. It is reminded that the takeoff weight is
the sum of the weight entry and the delta weight displayed in each box. It is allowed to interpolate
between two consecutive rows and/or columns for weight and for wind values not displayed on the
chart.
‐ Repeat this process for the other configuration available. Select that configuration giving the
highest flexible temperature.
CORRECTIONS DUE TO DIFFERENT TAKEOFF CONDITIONS
Ident.: PER-TOF-TOC-20-10-00013506.0001001 / 12 MAY 16
Applicable to: ALL
When the takeoff conditions are different from those provided on the chart, apply the associated
corrections.
Note:
‐ If the RTOW chart is based on the CG being at 25 %, the crew can determine the flexible
temperature at a more forward CG by decreasing the flexible temperature by 2 °C. V1 ,
VR and V2 must be increased by 1 kt.
‐ 25 % CG is the basic certified limit, on which all takeoff computation are based. To
take into account the operational margins, the above penalties must be applied when
operational CG is forward 27 %CG.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-TOF-TOC-20-10 P 1/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
CONSERVATIVE CORRECTIONS FOR QNH AND BLEEDS
Ident.: PER-TOF-TOC-20-10-00014723.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
Corrections are given for QNH ≠ 1 013 hPa, air conditioning ON, anti ice ON.
1. For a given takeoff weight and wind condition, read the flexible temperature. Retain the takeoff
speeds associated with the actual weight.
2. Apply the published temperature correction. To combine two or more corrections, add the different
corrections and apply to temperature value.
(No speed corrections required).
EXAMPLE D
DATA :
Actual takeoff weight = 68 000 kg
Head wind
= 10 kt
Air conditioning ON
QNH
= 1 013 hPa
Use the chart from Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE. Determine the maximum
permissible takeoff weight. The actual weight being lower than the maximum one, flexible takeoff
is possible.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PER-TOF-TOC-20-10 P 2/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Enter the 10 kt head wind column and interpolate for 68 000 kg, CONF 1 + F,
Flexible temperature................................................................................................................. 67 °C
Enter the 10 kt head wind column and interpolate for 68 000 kg, CONF 2,
Flexible temperature................................................................................................................. 66 °C
Retain CONF 1 + F for takeoff configuration.
Takeoff speeds are V1 = 153 kt, VR = 153 kt, V2 = 154 kt
Flexible temperature with air conditioning OFF....................................................................... 67 °C
Use the QNH/BLEEDS corrections (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS):
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PER-TOF-TOC-20-10 P 3/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Air conditioning correction......................................................................................................... -3 °C
Flexible temperature...............................................................................................................= 64 °C
CORRECTIONS FOR WET RUNWAY
Ident.: PER-TOF-TOC-20-10-00013280.0001001 / 18 FEB 11
Applicable to: ALL
Refer to PER-TOF-CTA-10 GENERAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← C to D
PER-TOF-TOC-20-10 P 4/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
CORRECTIONS PRODUCED ON THE RTOW CHART
Ident.: PER-TOF-TOC-20-10-00014724.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
A description of this correction is given on Refer to PER-TOF-TOC-16-20 CORRECTIONS DUE TO
DIFFERENT TAKEOFF CONDITIONS. The list of corrections is not exhaustive, however the most
commonly used corrections are wet runway, QNH, air conditioning and/or anti-icing. A maximum of
three corrections can be produced on one chart.
To apply the correction, proceed as follows:
1. Enter the chart with selected configuration, wind and actual takeoff weight to read the flexible
temperature associated with this weight.
2. Apply the first correction:
If the flexible temperature is less than or equal to TVMC (line 3), apply ΔTflex correction from line 1
and apply speed corrections (ΔV1 /ΔVR /ΔV2) from line 2.
Else, (flexible temperature greater than TVMC ), apply ΔTflex from line 3 and ΔV1 / ΔVR / ΔV2
corrections from line 4.
Check V2 against VMU limitation (Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY
VMU/VMCA (KT IAS)). If V2 is lower than V2 limited by VMU , flexible takeoff is not possible. Set
TOGA thrust and retain the speeds associated with maximum permissible takeoff weight or the
speeds read in the chart for the actual weight if they are all lower.
No speed correction is required for QNH and bleeds influence (Not applicable to maximum takeoff
weight determination).
3. To combine a second and/or a third correction, proceed as per point 2.
4. Check that the final flexible temperature is:
‐ Higher than OAT and TREF
‐ Limited to TMAX FLEX
If the check is fulfilled, retain final flexible temperature as the one to be inserted in the MCDU
If the check is not fulfilled, (final flexible temperature lower than OAT or TREF), no flexible
takeoff is possible.
Use TOGA thrust and retain speeds that have been calculated for the maximum permissible
takeoff weight. (Refer to PER-TOF-TOC-20-20 FLEXIBLE TAKEOFF NOT POSSIBLE)
Note:
‐ QNH correction is given for ± 10 hPa . It is allowed to extrapolate linearly for greater
QNH deviation.
‐ Corrections from the chart must be applied from the top to bottom, i.e in the RTOW on
Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE, apply the wet influence first
Note:
‐ When the flexible temperature is higher than TVMC , it is allowed to limit the flexible
temperature to TVMC and apply only corrections from lines 1 and 2.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
E→
PER-TOF-TOC-20-10 P 5/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
‐ If asterisk or dotted lines appear in the correction boxes, refer to more conservative
corrections provided in the FCOM.
EXAMPLE E
DATA :
CONF 1+F
Actual takeoff weight = 68 000 kg
Head wind
= 10 kt
QNH
= 998 hPa
WET runway
Air conditioning OFF
In this example, we will consider CONF 1+F as takeoff configuration. But same computation has to
be done in CONF 2 and you must retain the best configuration.
Use the chart from Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE.
Determine the maximum permissible takeoff weight.
The actual weight being lower than the maximum one, flexible takeoff is possible.
Enter the 10 kt head wind column and interpolate for 68 000 kg, CONF 1+F,
Flexible temperature................................................................................................................. 67 °C
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
PER-TOF-TOC-20-10 P 6/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Takeoff speeds are V1 = 153 kt, VR = 153 kt, V2 = 154 kt
Apply WET correction
For flexible temperature < TVMC (69 °C), ΔTflex =.................................................................. -2 °C
Intermediate flex temperature................................................................................................ = 65 °C
Associated speeds,
V1 = 153 kt – 8 = 145 kt
VR = 153 kt –2 = 151 kt
V2 = 154 kt – 2 = 152 kt
Check V2 against VMU limitation (Refer to PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY
VMU/VMCA (KT IAS) ).It is reminded that if the speed checks are not fulfilled, the corrections must
be recalculated using those provided on lines 3 and 4.
Apply QNH correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←E→
PER-TOF-TOC-20-10 P 7/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
FLIGHT CREW
OPERATING MANUAL
For flex temperature ≥ TVMC (61 °C), ΔTflex = -2 x 15/10 =................................................... -3 °C
Flexible temperature...............................................................................................................= 62 °C
No speed correction is required for QNH and bleed influence.
Takeoff speeds are V1 = 145 kt, VR = 151 kt, V2 = 152 kt
Check that OAT/TREF < flex temperature ≤ TMAXFLEX.
TMAXFLEX is specified in LIM-70.
For this example, if TMAXFLEX is equal to ISA + 45 °C (60 °C at airport elevation), Flex takeoff is
not possible.
Chart temperature
FCOM correction(s)
Intermediate value
WET Correction
Intermediate value
QNH Correction
Final value
Tflex
67
Takeoff Configuration : 1 + F
V1
VR
153
67
-2
65
-3
62
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
153
-8
145
0
145
←E
153
153
-2
151
0
151
V2
154
154
-2
152
0
152
PER-TOF-TOC-20-10 P 8/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
COMBINING CORRECTIONS FROM FCOM AND CHART
Ident.: PER-TOF-TOC-20-10-00014725.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
1. Apply corrections from FCOM (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS).
2. Apply corrections from the RTOW chart.
Apply speed corrections except for QNH and bleed influences.
EXAMPLE F
DATA :
Actual takeoff weight = 68 000 kg
CONF 1+F
Head wind = 10 kt
Air conditioning ON
QNH = 998 hPa
WET runway
In this example, we will consider CONF 1+F as takeoff configuration. But same computation has to
be done in CONF 2 and you must retain the best configuration.
Use the chart (Refer to PER-TOF-TOC-16-30 RTOW EXAMPLE).
Determine the maximum permissible takeoff weight (see example C). The actual weight being
lower than the maximum one, flexible takeoff is possible.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
F→
PER-TOF-TOC-20-10 P 9/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
‐ Enter the 10 kt head wind column and interpolate for 68 000 kg, CONF 1+F,
Flexible temperature............................................................................................................. 67 °C
‐ Takeoff speeds are V1 = 153 kt, VR = 153 kt, V2 = 154 kt
‐ First, apply the correction from FCOM (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND
BLEEDS).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PER-TOF-TOC-20-10 P 10/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Flexible temperature with air conditioning OFF.................................................................... 67 °C
Air conditioning correction..................................................................................................... -3 °C
Intermediate flexible temperature.......................................................................................= 64 °C
No speed correction.
‐ Apply WET correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PER-TOF-TOC-20-10 P 11/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
For flexible temperature < TVMC (69 °C), ΔTflex =.............................................................. -2 °C
Intermediate flex temperature............................................................................................ = 62 °C
Associated speeds,
V1 = 153 kt - 8 = 145 kt
VR = 153 kt - 2 = 151 kt
V2 = 154 kt - 2 = 152 kt
Check V2 against VMU limitation on FCOM Refer to PER-TOF-TOD-25-10 SPEEDS LIMITED
BY VMCG/VMCA.
It is reminded that if the speed checks are not fulfilled, the corrections must be recalculated
using those provided on lines 3 and 4.
‐ Apply QNH correction
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←F→
PER-TOF-TOC-20-10 P 12/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
For flexible temperature ≥ TVMC (61 °C), ΔTflex = -2 x 15/10 = ......................................... -3 °C
Flexible temperature...........................................................................................................= 59 °C
No speed correction is required for QNH and bleed influence.
Takeoff speeds are V1 = 145 kt, VR = 151 kt, V2 = 152 kt
Check that OAT/TREF < flex temperature ≤ TMAXFLEX
TMAXFLEX is specified in LIM-70.
Chart temperature
FCOM correction(s)
Intermediate value
WET Correction
Intermediate value
QNH Correction
Final value
Takeoff Configuration : 1 + F
V1
VR
153
153
Tflex
67
-3
0
0
V2
154
0
64
153
153
154
62
145
151
152
59
145
151
152
-2
-8
-3
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
0
←F
-2
0
-2
0
PER-TOF-TOC-20-10 P 13/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-20-10 P 14/14
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
FLEXIBLE TAKEOFF NOT POSSIBLE
FLEXIBLE TAKEOFF NOT POSSIBLE
Ident.: PER-TOF-TOC-20-20-00013281.0001001 / 18 FEB 11
Applicable to: ALL
In some cases when the actual takeoff weight is lower than the maximum permissible one but no
flexible takeoff possible (that is flexible temperature lower than TREF or OAT):
‐ It is mandatory to use TOGA thrust
‐ You can retain the speeds that have been calculated for the maximum permissible takeoff weight;
OR
‐ You can retain the speeds associated with the actual takeoff weight provided they are all lower
than the speeds calculated for the maximum permissible takeoff weight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOC-20-20 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-20-20 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
SUMMARY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-20-30 P 1/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
SUMMARY
Ident.: PER-TOF-TOC-20-30-00013282.0001001 / 24 MAR 11
Applicable to: ALL
The flow diagram gives the different steps to follow
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-TOF-TOC-20-30 P 2/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-TOF-TOC-20-30 P 3/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF CHARTS - FLEXIBLE TAKEOFF (WEIGHT ENTRY)
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOC-20-30 P 4/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
EFFECT OF QNH AND BLEEDS (UP TO 9200 FT)
Ident.: PER-TOF-TOD-24-00012927.0090001 / 31 MAR 11
Applicable to: ALL
Note:
‐ * Corrections valid only for OAT < 10 °C
‐ For high altitude operation, REFER TO PER-TOF-TOD-24 EFFECT OF QNH FOR HIGH
ALTITUDE OPERATIONS (if applicable).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-TOD-24 P 1/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
EXAMPLE
Ident.: PER-TOF-TOD-24-00014726.0001001 / 29 JUL 16
Applicable to: ALL
TAKEOFF CHART DATA
The following data and graphs are for example only, and are not for operational use. Even if the
data in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
Airport geometric elevation = 450 ft
QNH = 1 013 hPa
Anti ice OFF
Air conditioning OFF
EXAMPLE 1 - FULL THRUST TAKEOFF
Actual data :
OAT = 5 °C
QNH = 998 hPa
Engine anti ice ON
Air conditioning OFF
Weight read in the takeoff chart: 73 000 kg.
Use the QNH/BLEEDS corrections (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS)
or (Refer to PER-TOF-TOD-24 EFFECT OF QNH AND BLEEDS FOR HIGH ALTITUDE
OPERATIONS ) for high altitude operations.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-TOF-TOD-24 P 2/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
Read in the above table the corrections for high QNH and engine anti ice ON.
QNH correction: 120 kg x (1013 - 998) = 1 800 kg
Engine anti ice correction: No correction.
The maximum permissible takeoff weight is 73 000 - 1800 - 0 = 71 200 kg
EXAMPLE 2 - FLEXIBLE THRUST TAKEOFF
Actual data :
OAT = 5 °C
QNH = 1 004 hPa
Anti ice OFF
Air conditioning ON
TOW = 65 000 kg
Flexible temperature read on the takeoff chart: TFLEX = 55 °C.
Read TREF on the takeoff chart or on the quick reference table.
Read in the above table the correction for QNH and air conditioning ON:
QNH correction = 1 °C / 3 hPa × (1 004 - 1 013) = -3 °C
Air conditioning ON correction: -3 °C
New flexible temperature = 55 - 3 - 3 = 49 °C
Check that the flexible temperature is above TREF and actual OAT.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B→
PER-TOF-TOD-24 P 3/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
Check that the flexible temperature is less than the maximum flexible temperature.
EFFECT OF QNH AND BLEEDS FOR HIGH ALTITUDE OPERATIONS (ABOVE 9200 FT)
Ident.: PER-TOF-TOD-24-00012926.0207001 / 24 MAR 11
Applicable to: ALL
Note:
* Corrections valid only for OAT < 10 °C
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← B to C
PER-TOF-TOD-24 P 4/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
EXAMPLES FOR HIGH ALTITUDE OPERATIONS
Ident.: PER-TOF-TOD-24-00012925.0070001 / 18 MAR 11
Applicable to: ALL
TAKEOFF CHART DATA
Airport geometric elevation = 11 500 ft
QNH = 1 013 hPa
Anti ice OFF
Air conditioning OFF
OAT = 0 °C
MTOW = 73 000 kg
EXAMPLE 1 - FULL THRUST TAKEOFF
Actual data :
QNH = 1 040 hPa
Engine anti ice ON
Air conditioning OFF
Determine the actual airport pressure altitude (1 hPa is equivalent to 28 ft according to the ISA
model).
Pressure altitude = 11 500 - (1 040 - 1 013) × 28 = 10 744 ft
Read in the above table the corrections for high QNH and engine anti ice ON.
QNH correction = 60 kg × (11 500 - 10 744)/28 hPa = +1 620 kg
Engine anti ice correction: 1 800 kg
The maximum permissible takeoff weight is 73 000 + 1 620 - 1 800 = 72 820 kg
EXAMPLE 2 - FLEXIBLE THRUST TAKEOFF
Actual data :
QNH = 1 040 hPa
Anti ice OFF
Air conditioning ON
TOW = 65 000 kg
TFLEX = 55 °C
Read TREF on the takeoff chart or on the quick reference table.
Determine the actual airport pressure altitude (1 hPa is equivalent to 28 ft according to the ISA
model).
Pressure altitude = 11 500 - (1 040 - 1 013) × 28 = 10 744 ft
Read in the above table the correction for QNH and air conditioning ON:
QNH correction = 1 °C/11 hPa × (11 500 - 10 744)/28 hPa = +3 °C
Air conditioning ON correction = -5 °C
New flexible temperature = 55 + 3 - 5 = 53 °C
Check that the flexible temperature is above TREF and actual OAT.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PER-TOF-TOD-24 P 5/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF DATA - QNH/BLEEDS CORRECTION
Check that the flexible temperature is less than the maximum flexible temperature and retain the
lower of the two.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PER-TOF-TOD-24 P 6/6
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
TAKEOFF DATA - MINIMUM SPEEDS
FLIGHT CREW
OPERATING MANUAL
SPEEDS LIMITED BY VMCG/VMCA
SPEEDS LIMITED BY VMCG/VMCA
Ident.: PER-TOF-TOD-25-10-00001754.0268001 / 08 JUL 15
Applicable to: ALL
All takeoff speeds have a minimum value limited by control. These minimum speeds are usually
provided on each RTOW chart. If these speeds are not available, use the following conservative
values. These speeds may be slightly higher than the minimum control speeds displayed on the
RTOW chart.
CONF
1+F
2
3
CONF
1+F
2
3
CONF
1+F
2
3
-2 000
0
1 000
113
112
117
115
114
112
115
-2 000
1 000
117
116
119
118
116
-2 000
118
115
0
1 000
121
120
124
121
123
121
123
111
0
121
119
114
120
120
MINIMUM V1 (KT IAS)
PRESSURE ALTITUDE (FT)
2 000 3 000 4 000 5000 6 000
113
112
112
111
110
110
110
110
109
108
111
111
110
109
108
MINIMUM VR (KT IAS)
PRESSURE ALTITUDE (FT)
2 000 3 000 4 000 5000 6 000
116
116
116
115
114
114
114
114
113
112
115
114
114
113
112
MINIMUM V2 (KT IAS)
PRESSURE ALTITUDE (FT)
2 000 3 000 4 000 5000 6 000
119
119
119
118
117
119
119
118
117
116
119
119
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
119
A
117
116
7 000
8 000
9 200
14 100
107
106
104
100
109
107
108
105
106
104
100
100
7 000
8 000
9 200
10 200
111
109
108
100
113
110
111
109
110
107
102
100
7 000
8 000
9 200
10 200
115
114
112
103
115
115
114
114
112
112
104
103
PER-TOF-TOD-25-10 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
TAKEOFF DATA - MINIMUM SPEEDS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOD-25-10 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
TAKEOFF DATA - MINIMUM SPEEDS
FLIGHT CREW
OPERATING MANUAL
V2 LIMITED BY VMU/VMCA
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-TOD-25-20 P 1/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
TAKEOFF DATA - MINIMUM SPEEDS
MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)
Ident.: PER-TOF-TOD-25-20-00001756.0095001 / 25 MAR 11
Applicable to: ALL
The following tables, one per configuration, provide the V2 limited by minimum unstick speed and
minimum control speed in the air.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-TOF-TOD-25-20 P 2/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
TAKEOFF DATA - MINIMUM SPEEDS
←A→
PER-TOF-TOD-25-20 P 3/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
TAKEOFF DATA - MINIMUM SPEEDS
←A
PER-TOF-TOD-25-20 P 4/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - GENERAL
GENERAL
Ident.: PER-TOF-CTA-10-00001781.0001001 / 21 JUL 14
Applicable to: ALL
This section presents the recommendations of Airbus for operations from wet runways or from
runways which are covered with contaminants such as standing water, slush or snow.
CAUTION
Takeoff is not recommended:
‐ From an icy runway
‐ From a runway for which the depth of contaminant is greater than the
performance levels or the equivalences published in the documentation or
performance software.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-CTA-10 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-CTA-10 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - DEFINITIONS
FLIGHT CREW
OPERATING MANUAL
DEFINITIONS
Ident.: PER-TOF-CTA-20-00001782.0001001 / 22 MAY 13
Applicable to: ALL
DAMP
:
WET
:
STANDING WATER
:
SLUSH
:
WET SNOW
:
DRY SNOW
:
COMPACTED SNOW :
ICY
:
A runway is damp when the surface is not dry, but when the water on it
does not give it a shiny appearance.
A runway is considered as wet when the surface has a shiny
appearance due to a thin layer of water. When this layer does not
exceed 3 mm depth, there is no substantial risk of hydroplaning.
is caused by heavy rainfall and /or insufficient runway drainage with a
depth of more than 3 mm.
is water saturated with snow which spatters when stepping firmly on
it. It is encountered at temperatures around 5 °C and its density is
approximately 0.85 kg/l (7.1 lb/US Gal).
is a condition where, if compacted by hand, snow will stick together
and tend to form a snowball. Its density is approximately 0.4 kg/l
(3.35 lb/US Gal).
is a condition where snow can be blown if loose, or if compacted by
hand, will fall apart again upon release. Its density is approximately
0.2 kg/l (1.7 lb/US Gal).
is a condition where snow has been compressed.
is a condition where the friction coefficient is 0.05 or below.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-CTA-20 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - DEFINITIONS
FLIGHT CREW
OPERATING MANUAL
EQUIVALENCES
Ident.: PER-TOF-CTA-20-00014919.0001001 / 21 JUL 14
Applicable to: ALL
For the below-listed reported contaminants, the following equivalent runway conditions can be
retained for the takeoff performance determination.
Reported contaminant
Type of contaminant
Depth of contaminant
Slush
Water
Wet snow
Dry snow
≤ 3 mm (1/8 in)
≤ 3 mm (1/8 in)
≤ 3 mm (1/8 in)
≤ 12.7 mm (1/2 in)
≤ 25.4 mm (1 in)
≤ 3 mm (1/8 in)
≤ 50.8 mm (2 in)
≤ 100 mm (4 in)
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
Equivalent Runway Condition
Wet
6.3 mm (1/4 in) Slush
12.7 mm (1/2 in) Slush
Wet
6.3 mm (1/4 in) Slush
12.7 mm (1/2 in) Slush
PER-TOF-CTA-20 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - OPERATIONAL CONDITIONS
OPERATIONAL CONDITIONS
Ident.: PER-TOF-CTA-30-00001783.0001001 / 14 DEC 09
Applicable to: ALL
Performance penalties for takeoff as published in this section are computed with the
following assumptions :
‐ The contaminant is in a layer of uniform depth and density over the entire length of the runway.
‐ Antiskid and spoilers are operative.
‐ The friction coefficient is based on studies and checked by actual tests.
‐ The screen height at the end of takeoff segment is 15 ft, not 35 ft.
In addition, for contaminated runways only :
‐ There is drag due to rolling resistance of the wheels.
‐ There is drag due to spray on the airframe and gears.
‐ Reverse thrust is used for the deceleration phase.
‐ Maximum thrust is used for takeoff.
Note:
The net flight path clears obstacles by 15 ft instead of 35 ft.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-CTA-30 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - OPERATIONAL CONDITIONS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-CTA-30 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
TAKEOFF PERFORMANCE
TAKEOFF PERFORMANCE
Ident.: PER-TOF-CTA-40-10-00013660.0003001 / 23 JUN 15
Applicable to: ALL
CAUTION
The method is based on the use of the RTOW charts established at optimum V2 /VS
and optimum V1 /VR . In addition, when applying corrections for a wet runway, the
RTOW charts should also have been established with V1 min (minimum V1 of the
V1 range). The method should not be used with takeoff charts computed for other
conditions. All tables have been established for TOGA (and Flexible Takeoff for wet
runways). Do not use them for Derated thrust.
Correct the determined maximum takeoff weight on dry runway to take into account QNH and bleed
effects, then apply the corrections given on the following pages.
Note:
1. The results obtained with this method may be different from the influence given at the
bottom of the RTOW chart.
2. On contaminated runway, in some cases, no MTOW can be determined with this method
(box dashed below a given weight). A specific RTOW chart must then be computed.
3. The published corrections are valid for charts calculated with forward CG and basic CG.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-CTA-40-10 P 1/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-CTA-40-10 P 2/2
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
TAKEOFF FROM A WET RUNWAY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-CTA-40-20 P 1/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
HOW TO PROCEED
Ident.: PER-TOF-CTA-40-20-00012966.0004001 / 24 MAR 11
Applicable to: ALL
1. Determine the maximum takeoff weight or flexible temperature and associated speeds on dry
runway.
2. Two sets of tables are given depending on the use of thrust reversers and the presence of
clearway. Select the table to use as applicable to your case.
The runway length in the table corresponds to the available takeoff run (TORA).
3. Apply the corrections shown in the table to the maximum takeoff weight or flexible temperature
and associated speeds determined on dry runway.
4. Check that takeoff speeds are greater than the minimum values shown on the RTOW chart.
If one or more speeds are lower than these minimum values, apply the following procedure :
‐ Actual TOW = maximum TOW
• If V1 is lower than the minimum V1 (V1 limited by VMCG ), take this last value as V1 and
further decrease weight by 3 000 kg (6 600 lb ) per knot difference between them. Check that
VR and V2 are higher than or equal to the minimum values.
• If VR or/and V2 falls below the minimum values, takeoff is not possible.
‐ Actual TOW lower than maximum TOW
• If V1 corresponding to actual TOW is lower than the minimum V1 (V1 limited by VMCG) :
▪ If maximum TOW has a V1 equal to or above minimum V1 , retain minimum V1 as V1 and
decrease the flexible temperature by 4 °C per knot difference between them.
▪ In the rare case when the V1 corresponding to maximum TOW falls below the minimum V1
, decrease maximum TOW by 3 000 kg (6 600 lb ) per knot difference between them. Limit
the actual TOW to the value found after this decrement. Take V1 equal to minimum V1 and
decrease the flexible temperature by 4 °C per knot difference between this last value and
the V1 corresponding to the actual TOW . Check that VR and V2 are higher than or equal
to the minimum values.
• If VR or V2 corresponding to actual TOW falls below the minimum values, and if VR and V2
corresponding to maximum TOW are above the minimum values, retain the minimum speed
value for VR and V2.
5. Check that V2 is above the minimum V2 value due to VMU (Refer to PER-TOF-TOD-25-10
SPEEDS LIMITED BY VMCG/VMCA).
6. Check that the corrected flexible temperature is higher than OAT and Tref.
Note:
‐ Do not extrapolate below the shortest runway length provided in the table.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-TOF-CTA-40-20 P 2/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
‐ If no minimum speed value is available, use the conservative values provided on Refer to
PER-TOF-TOD-25-10 SPEEDS LIMITED BY VMCG/VMCA.
NO THRUST REVERSERS OPERATIVE (NO CLEARWAY)
Ident.: PER-TOF-CTA-40-20-00012743.0048001 / 04 MAR 11
Applicable to: ALL
TAKEOFF
CONFIGURATION
RUNWAY LENGTH
(m)
(ft)
1+F
FLEX TO
Temperature
decrement (°C)
MAX TO Weight
decrement (1 000 kg)
(1 000 lb)
V1 decrement (kt)
VR and V2
decrement (kt)
2
3
2 500
8 000
3 000
10 000
3 500
11 500
and above
2 000
6 500
2 500
8 000
3 000
1 750
10 000
5 750
and above
2 000
6 500
2 500
8 000
and above
8
5
3
8
6
2
6
6
2
2.6
5.8
2.0
4.5
1.3
2.9
2.5
5.6
2.2
4.9
0.7
1.6
2.1
4.7
2.1
4.7
0.7
1.6
15
14
14
16
14
14
14
15
13
2
1
1
2
1
2
1
2
0
ALL THRUST REVERSERS OPERATIVE (NO CLEARWAY)
Ident.: PER-TOF-CTA-40-20-00012744.0084001 / 04 MAR 11
Applicable to: ALL
TAKEOFF
CONFIGURATION
RUNWAY LENGTH
(m)
(ft)
FLEX TO Temperature
decrement (°C)
MAX TO Weight
decrement (1000 kg)
(1000 lb)
V1 decrement (kt)
VR and V2
decrement (kt)
1+F
2
3
2500
8000
3000
10000
3500
11500
and above
2000
6500
2500
8000
3000
10000
and above
1750
5750
2000
6500
2500
8000
and above
3
2
0
3
1
0
2
1
1
1.0
2.3
9
0.6
1.4
9
0.0
0.0
9
0.8
1.8
10
0.3
0.7
8
0.0
0.0
9
0.6
1.4
10
0.2
0.5
9
0.1
0.3
8
0
0
0
0
0
0
0
0
0
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to C
PER-TOF-CTA-40-20 P 3/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
NO THRUST REVERSERS OPERATIVE (WITH CLEARWAY)
Ident.: PER-TOF-CTA-40-20-00012745.0044001 / 08 FEB 11
Applicable to: ALL
TAKEOFF
CONFIGURATION
RUNWAY LENGTH
(m)
(ft)
FLEX TO
Temperature
decrement (°C)
MAX TO Weight
decrement
(1 000 kg)
(1 000 lb)
V1 decrement (kt)
VR and V2
decrement (kt)
1+F
2
2 500
8 000
3 000
10 000
15
9
9
5.4
12.0
4.1
9.1
4
3
14
3 500
2 000
11 500
6 500
and above
15
3
2 500
8 000
3 000
10 000
and above
1 750
5 750
2 000
6 500
2 500
8 000
and above
14
11
4
15
12
5
3.8
8.4
4.6
10.2
4.2
9.3
1.6
3.6
4.5
10.0
4.5
10.0
2.2
4.9
6
4
4
6
3
4
5
15
14
14
15
13
13
14
ALL THRUST REVERSERS OPERATIVE (WITH CLEARWAY)
Ident.: PER-TOF-CTA-40-20-00012941.0044001 / 28 JAN 11
Applicable to: ALL
TAKEOFF
CONFIGURATION
RUNWAY LENGTH
(m)
(ft)
FLEX TO Temperature
decrement (°C)
MAX TO Weight
decrement (1 000 kg)
(1 000 lb)
V1 decrement (kt)
VR and V2
decrement (kt)
1+F
2 500 3 000
8 000 10 000
2
3 500
2 000
11 500
6 500
and above
2 500
8 000
3
3 000
1 750
10 000
5 750
and above
2 000
6 500
2 500
8 000
and above
11
5
2
10
8
3
11
9
3
3.9
8.6
9
2.3
5.1
10
0.9
2.0
12
3.3
7.3
9
3.1
6.9
9
1.0
2.3
10
3.3
7.3
8
3.3
7.3
9
1.3
2.5
9
3
2
3
3
3
4
2
2
4
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D to E
PER-TOF-CTA-40-20 P 4/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
TAKEOFF FROM A CONTAMINATED RUNWAY
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-TOF-CTA-40-30 P 1/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
TAKEOFF FROM A 6.3 MM (1/4 INCH) WATER COVERED RUNWAY
Ident.: PER-TOF-CTA-40-30-00001786.0373001 / 22 FEB 17
Applicable to: ALL
‐ Determine maximum takeoff weight on dry runway.
‐ Apply the following weight decrement versus takeoff configuration, runway length and clearway
availability to determine a corrected weight.
TAKEOFF
CONFIGURATION
CONF 1 + F
CONF 2
CONF 3
RUNWAY LENGTH
(m)
(ft)
2 500
8 000
3 000
10 000
3 500
11 500
2 000
6 500
2 500
8 000
3 000
10 000
and
above
1 750
5750
2 000
6 500
Δ Weight (1 000 kg)
With clearway
Without clearway
4 000
13 00
and
above
2 500
8 000
and
above
12.8
10.5
11.7
10.1
9.8
9.0
9.8
9.0
13.9
11.1
13.2
11.1
11.4
10.4
14.9
11.4
14.5
11.8
13.1
11.8
‐ Enter the following tables with the corrected weight to determine MTOW then determine takeoff
speeds associated with actual TOW.
CONF 1 + F
CORRECTED
WEIGHT
(1 000 kg)
56
58
58 to 78
46.7
50
58
EQUAL TO CORRECTED WEIGHT
ACTUAL WEIGHT
<46.7 46.7
(1 000 kg)
48
50
MTOW
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
<55.2 55.2
-
52
54
56
58
60
62
64
66
68
70
72
74
76
78
124
124 126 129 131 134 136 138 141 143 145 148 150 152 155 157 159 161
121
121 123 126 128 131 133 135 138 140 142 145 147 149 152 154 156 158
117
117 117 117 117 117 117 117 120 122 124 127 129 131 134 136 138 140
CONF 2
CORRECTED
WEIGHT
(1 000 kg)
MTOW
(1 000 kg)
<56.8 56.8
-
48.7
58
59
59 to 78
55
59
EQUAL TO CORRECTED WEIGHT
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-TOF-CTA-40-30 P 2/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
ACTUAL WEIGHT
<48.7 48.7
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
50
52
54
56
58
59
60
62
64
66 68 70 72 74
76
78
125
125
127 129 132 134 137 138 139 141 143 146 148 150 153 155 157 159
119
119
121 123 126 128 131 132 133 135 137 140 142 144 147 149 151 153
115
115
115 115 115 115 115 115 116 118 120 123 125 127 130 132 134 136
CONF 3
CORRECTED
WEIGHT
(1 000 kg)
58
60
60 to 78
48
49
60
EQUAL TO CORRECTED WEIGHT
ACTUAL WEIGHT
<48
(1 000 kg)
48
50
52
123
126
126 128 131 133 135 138 140 142 145 147 149 151 153 155 157
118
118
121 123 126 128 130 133 135 137 140 142 144 146 148 150 152
114
114
114 114 114 114 114 114 116 118 121 123 125 129 129 131 133
MTOW
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
<57.8 57.8
-
54
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
56
58
←A
60
62
64
66
68
70
72
74
76
78
PER-TOF-CTA-40-30 P 3/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
TAKEOFF FROM A 12.7 MM (1/2 INCH) WATER COVERED RUNWAY
Ident.: PER-TOF-CTA-40-30-00001794.0117001 / 01 APR 11
Applicable to: ALL
‐ Determine maximum takeoff weight on dry runway.
‐ Apply the following weight decrement versus takeoff configuration, runway length and clearway
availability to determine a corrected weight.
TAKEOFF
CONFIGURATION
CONF 1 + F
CONF 2
CONF 3
RUNWAY LENGTH
(m)
(ft)
2 500
8 000
3 000
10 000
3 500
11 500
2 000
6 500
2 500
8 000
3 000
10 000
and
above
1 750
5 750
2 000
6 500
Δ Weight (1 000 kg)
With clearway
Without clearway
4 000
13 000
and
above
2 500
8 000
and
above
16.7
14.4
15.7
14.1
12.9
12.0
10.4
9.6
17.3
13.3
16.6
14.5
15.5
14.5
17.5
14.0
17.5
14.8
16.3
15.0
‐ Enter the following tables with the corrected weight to determine MTOW then determine takeoff
speeds associated with actual TOW.
CONF 1 + F
CORRECTED
WEIGHT
<51.4 51.4 52 52.7
(1 000 kg)
MTOW
(1 000 kg)
ACTUAL
WEIGHT
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
-
52.7 to 78
46.7 49 52.7
<46.7 46.7 48
50
EQUAL TO CORRECTED WEIGHT
52 52.7 54
56
58
60
62
64
66
68
70
72
74
76
78
124 124 126 129 131 132 134 136 138 141 143 145 148 150 152 155 157 159 161
122 122 124 127 129 130 132 134 136 139 141 143 146 148 150 153 155 157 159
117 117 117 117 117 117 119 121 123 126 128 130 133 135 137 140 142 144 146
CONF 2
CORRECTED
WEIGHT
<52.9 52.9 54
(1 000 kg)
MTOW
(1 000 kg)
-
48 54
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
54 to 78
EQUAL TO CORRECTED WEIGHT
B→
PER-TOF-CTA-40-30 P 4/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
ACTUAL
WEIGHT
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
<48
48
50
52
54
56
58
60
62
64
66
68
70
72
74
76
78
124 124 127 129 132 134 137 139 141 143 146 148 150 153 155 157 159
119 119 122 124 127 129 132 134 136 138 141 143 145 148 150 152 154
115 115 115 115 115 117 120 122 124 126 129 131 133 136 138 140 142
CONF 3
CORRECTED
WEIGHT
(1 000 kg)
<54 54 56
MTOW
(1 000 kg)
-
ACTUAL
WEIGHT
(1 000 kg)
<48
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
56 to 78
48 56
48
50
EQUAL TO CORRECTED WEIGHT
52
54
56
58
60
62
64
66
68
70
72
74
76
78
123 123 126 128 131 133 135 138 140 142 145 147 149 151 153 155 157
118 118 121 123 126 128 130 133 135 137 140 142 144 146 148 150 152
114 114 114 114 114 114 116 119 121 123 126 128 130 132 134 136 138
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PER-TOF-CTA-40-30 P 5/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
TAKEOFF FROM A 6.3 MM (1/4 INCH) SLUSH COVERED RUNWAY
Ident.: PER-TOF-CTA-40-30-00001787.0374001 / 25 MAR 11
Applicable to: ALL
‐ Determine maximum takeoff weight on dry runway.
‐ Apply the following weight decrement versus takeoff configuration, runway length and clearway
availability to determine a corrected weight.
TAKEOFF
CONFIGURATION
CONF 1 + F
CONF 2
CONF 3
RUNWAY LENGTH
(m)
(ft)
2 500
8 000
3 000
10 000
3 500
11 500
2 000
6 500
2 500
8 000
3 000
10 000
and
above
1 750
5 750
2 000
6 500
Δ Weight (1 000 kg)
With clearway
Without clearway
4 000
13 000
and
above
2 500
8 000
and
above
13.2
10.9
11.8
10.2
9.8
9.0
9.8
9.0
14.5
11.7
13.8
11.7
11.6
10.6
15.2
11.5
15.2
12.5
13.9
12.6
‐ Enter the following tables with the corrected weight to determine MTOW then determine takeoff
speeds associated with actual TOW.
CONF 1 + F
CORRECTED
WEIGHT
<53.2 53.2 54
(1 000 kg)
MTOW
(1 000 kg)
ACTUAL
WEIGHT
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
55
55 to 78
46.7 51
55
EQUAL TO CORRECTED WEIGHT
<46.7 46.7 48
50
-
52 54
55
56
58
60
62
64
66
68
70 72 74
76
78
124
124 126 129 131 134 135 136 138 141 143 145 148 150 152 155 157 159 161
122
122 124 127 129 132 133 134 136 139 141 143 146 148 150 153 155 157 159
117
117 117 117 117 117 117 118 120 123 125 127 130 132 134 137 139 141 143
CONF 2
CORRECTED
WEIGHT
<54.8 54.8 56 56.7
(1 000 kg)
56.7 to 76
-
EQUAL TO CORRECTED WEIGHT
MTOW
(1 000 kg)
48
53 56.7
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PER-TOF-CTA-40-30 P 6/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
ACTUAL
WEIGHT
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
<48
48
50
52
54
56 56.7 58
60
62
64
66
68
70
72
74
76
78
124
124 127 129 132 134 135 137 139 141 143 146 148 150 153 155 157 159
119
119 122 124 127 129 130 132 134 136 138 141 143 145 148 150 152 154
115
115 115 115 115 115 115 117 119 121 123 126 128 130 133 135 137 139
CONF 3
CORRECTED
WEIGHT
<56.3 56.3 58 58.7
(1 000 kg)
58.7 to 78
MTOW
(1 000 kg)
-
48
55 58.7
EQUAL TO CORRECTED WEIGHT
ACTUAL
WEIGHT
(1 000 kg)
<48
48
50
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
52
54
56
58 58.7 60
62
64
66
68
70
72
74
76
78
123 123 126 128 131 133 135 136 138 140 142 145 147 149 151 153 155 157
118 118 121 123 126 128 130 131 133 135 137 140 142 144 146 148 150 152
114 114 114 114 114 114 114 114 116 118 120 123 125 127 129 131 133 135
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PER-TOF-CTA-40-30 P 7/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
TAKEOFF FROM A 12.7 MM (1/2 INCH) SLUSH COVERED RUNWAY
Ident.: PER-TOF-CTA-40-30-00001788.0369001 / 23 JUN 15
Applicable to: ALL
‐ Determine maximum takeoff weight on dry runway.
‐ Apply the following weight decrement versus takeoff configuration, runway length and clearway
availability to determine a corrected weight.
TAKEOFF CONFIGURATION
RUNWAY LENGTH
(m)
(ft)
Δ Weight (1 000 kg)
With clearway
Without clearway
CONF 1 + F
CONF 2
4 000
3 000
3 500
2 500 3 000
13 000 2 000 2 500 10 000
11
8 000 10 000
and 6 500 8 000
and
500
above
above
18.9
17.3
18.9
17.3
16.3
15.4
15.4
14.6
18.7
14.7
18.7
16.6
17.9
16.9
CONF 3
1 750 2 000
5 750 6 500
18.9
15.4
18.4
15.7
2 500
8 000
and
above
18.3
17.0
‐ Enter the following tables with the corrected weight to determine MTOW then determine takeoff
speeds associated with actual TOW.
CONF 1 + F
CORRECTED
WEIGHT
<47.8 47.8 48
(1 000 kg)
MTOW
(1 000 kg)
-
46.7 48
ACTUAL WEIGHT
<46.7 46.7 48
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
48 to 78
EQUAL TO CORRECTED WEIGHT
50
52
54
56
58
60
62 64 66 68 70 72 74 76 78
124
124 126 129 131 134 136 138 141 143 145 148 150 152 155 157 159 161
123
123 125 128 130 133 135 137 140 142 144 147 149 151 154 156 158 160
117
117 117 120 122 125 127 129 132 134 136 139 141 143 146 148 150 152
CONF 2
CORRECTED
WEIGHT
<49.5 49.5 50
(1 000 kg)
MTOW
(1 000 kg)
-
47
50
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
50 to 78
EQUAL TO CORRECTED WEIGHT
D→
PER-TOF-CTA-40-30 P 8/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
ACTUAL WEIGHT
<47 47
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
48
50
52
54
56
58
60
62
64
66
68
70
72
74
76
78
123 123 124 127 129 132 134 137 139 141 143 146 148 150 153 155 157 159
119 119 120 123 125 128 130 133 135 137 139 142 144 146 149 151 153 155
115 115 115 115 117 120 122 125 127 129 131 134 136 138 141 143 145 147
CONF 3
CORRECTED
WEIGHT
(1 000 kg)
MTOW
(1 000 kg)
<51
51
52
52 to 78
-
48
52
EQUAL TO CORRECTED WEIGHT
ACTUAL WEIGHT
<48
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
48
50
52
54
56
58
60
62
64
66
68
70
72
74
76
78
123 123 126 128 131 133 135 138 140 142 145 147 149 151 153 155 157
119 119 122 124 127 129 131 134 136 138 141 143 145 147 149 151 153
114 114 114 114 117 119 121 124 126 128 131 133 135 137 139 141 143
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PER-TOF-CTA-40-30 P 9/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
TAKEOFF FROM A COMPACTED SNOW COVERED RUNWAY
Ident.: PER-TOF-CTA-40-30-00001789.0347001 / 23 JUN 15
Applicable to: ALL
‐ Determine maximum takeoff weight on dry runway.
‐ Apply the following weight decrement versus takeoff configuration and runway length to determine
a corrected weight.
TAKEOFF CONFIGURATION
RUNWAY LENGTH
(m)
(ft)
Δ Weight decrement
(1 000 kg)
With clearway
Without clearway
CONF 1 + F
CONF 2
4 000
3 000
3 500
2 500 3 000
13 000 2 000 2 500 10 000
11
8 000 10 000
and 6 500 8 000
and
500
above
above
8.6
6.3
8.5
6.3
8.5
7.4
9.8
9.0
10.5
7.7
7.4
5.3
CONF 3
1 750 2 000
5 750 6 500
5.6
4.6
13.1
9.6
2 500
8 000
and
above
10.3
7.6
8.2
6.9
‐ Enter the following tables with the corrected weight to determine MTOW then determine takeoff
speeds associated with actual TOW.
CONF 1 + F,
CORRECTED
WEIGHT <52.7 52.7 54
(1 000 kg)
MTOW
(1 000 kg)
ACTUAL
WEIGHT
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
-
54 to 78
46.7 54
<46.7 46.7 48
EQUAL TO CORRECTED WEIGHT
50
52
54 56 58
60
62
64
66
68
70
72
74
76
78
124 124 126 129 131 134 136 138 141 143 145 148 150 152 155 157 159 161
123 123 125 128 130 133 135 137 140 142 144 147 149 151 154 156 158 160
117 117 117 117 117 117 119 121 124 126 128 131 133 135 138 140 142 144
CONF 2
CORRECTED
WEIGHT <54.8 54.8
(1 000 kg)
48
MTOW
56
56.7
53
56.7
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
56.7 to 78
EQUAL TO CORRECTED WEIGHT
Continued on the following page
E→
PER-TOF-CTA-40-30 P 10/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
FLIGHT CREW
OPERATING MANUAL
CORRECTED
WEIGHT <54.8 54.8
(1 000 kg)
Continued from the previous page
56
56.7
50
52
56.7 to 78
(1 000 kg)
ACTUAL
WEIGHT
(1 000 kg)
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
<48
48
54
56 56.7
58
60
62
64
66
68
70
72
74
76
78
124 124 127 129 132 134 135 137 139 141 143 146 148 150 153 155 157 159
119 119 122 124 127 129 130 132 134 136 138 141 143 145 148 150 152 154
115 115 115 115 115 115 115 117 119 121 123 126 128 130 133 135 137 139
CONF 3
CORRECTED
WEIGHT <56.3 56.3
(1 000 kg)
58 58.7
58.7 to 78
EQUAL TO CORRECTED WEIGHT
MTOW
(1 000 kg)
-
48
55 58.7
ACTUAL
WEIGHT
(1 000 kg)
<48
48
50
V2
(kt IAS)
VR
(kt IAS)
V1
(kt IAS)
52
54
56
58 58.7
60
62
64
66
68
70
72
74
76
78
123 123 126 128 131 133 135 136 138 140 142 145 147 149 151 153 155 157
119 119 122 124 127 129 131 132 134 136 138 141 143 145 147 149 151 153
114 114 114 114 114 114 114 114 116 118 120 123 125 127 129 131 133 135
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←E
PER-TOF-CTA-40-30 P 11/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
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FCOM
PER-TOF-CTA-40-30 P 12/12
22 MAR 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
EXAMPLE
TAKEOFF PERFORMANCE ON DRY RUNWAY
Ident.: PER-TOF-CTA-40-40-00014730.0001001 / 29 JUL 16
Applicable to: ALL
DATA
The following data and graph are for example only, and are not for operational use. Even if the
data in the following example is in "kg" and "m", the same method can be applied for "lb" and "ft".
Runway length : 3 000 m, OAT = 36 °C, no wind, CONF 1+F
Determine maximum takeoff weight on dry runway from RTOW chart (Refer to
PER-TOF-TOC-10-30 EXAMPLE OF TAKEOFF CHART).
Maximum TOW = 80 100 kg, V1 = 153 kt, VR = 156 kt, V2 = 158 kt.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-TOF-CTA-40-40 P 1/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
TAKEOFF PERFORMANCE ON WET RUNWAY
Ident.: PER-TOF-CTA-40-40-00014731.0001001 / 29 JUL 16
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
With no thrust reversers operating and assuming that no clearway was used to compute the dry
RTOW chart, use the table Refer to PER-TOF-CTA-40-20 NO THRUST REVERSERS OPERATIVE
(NO CLEARWAY).
• Maximum takeoff weight correction :
MTOW = 80 100 - 900 = 79 200 kg, V1 = 153 - 16 = 137 kt, VR = 156 - 3 = 153 kt, V2 = 158 - 3 =
155 kt.
• Flex temperature correction :
Assuming an actual takeoff weight of 75 000 kg and an initial flex temperature of 53 °C
TOW = 75 000 kg ⇒ Flex temperature = 53 - 3 = 50 °C
V1 = 152 - 16 = 136 kt, VR = 153 - 3 = 150 kt, V2 = 154 - 3 = 151 kt.
Check the resulting speeds against the minimum speeds as per procedure Refer to
PER-TOF-CTA-40-20 HOW TO PROCEED.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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B
PER-TOF-CTA-40-40 P 2/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
TAKEOFF PERFORMANCE ON RUNWAY COVERED WITH 1/2 INCH SLUSH
Ident.: PER-TOF-CTA-40-40-00014732.0001001 / 29 JUL 16
Applicable to: ALL
DATA
The following data and graphs are for example only, and are not for operational use. Even if the
data in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
Runway length 3 000 m (no clearway), OAT = 5 °C, 5 kt tailwind, CONF 1 + F
Determine maximum takeoff weight on dry runway (Refer to PER-TOF-TOC-10-30 EXAMPLE OF
TAKEOFF CHART)
Maximum takeoff weight on dry runway = 80 300 kg
Determine a corrected weight (Refer to PER-TOF-CTA-40-30 TAKEOFF FROM A 12.7 MM (1/2
INCH) SLUSH COVERED RUNWAY). As no clearway, use the correction diplayed on the second
line (without clearway).
Corrected weight = 80 300 – 14 700 = 65 600 kg
Determine maximum takeoff weight and associated speeds :
MTOW = 65 600 kg
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PER-TOF-CTA-40-40 P 3/4
24 JAN 17
PERFORMANCE
TAKEOFF
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - TAKEOFF PERFORMANCE
V1 = 141 kt, VR = 147 kt, V2 = 148 kt
GLG A318/A319/A320/A321 For A/C: HC-CRU
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←C
PER-TOF-CTA-40-40 P 4/4
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
Intentionally left blank
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-FPL-GEN GENERAL
PER-FPL-GEN-MFR MINIMUM RECOMMENDED FUEL REQUIREMENTS
MINIMUM RECOMMENDED FUEL REQUIREMENTS.......................................................................................... A
PER-FPL-GEN-FPL FLIGHT PLAN
FLIGHT PLAN..........................................................................................................................................................A
PER-FPL-FLP FLIGHT PREPARATION
PER-FPL-FLP-QFP QUICK DETERMINATION OF FLIGHT PLANNING
PER-FPL-FLP-QFP-10 INTRODUCTION
INTRODUCTION......................................................................................................................................................A
PER-FPL-FLP-QFP-20 CORRECTION FOR DEVIATION FROM REFERENCE LANDING
WEIGHT
CORRECTION FOR DEVIATION FROM REFERENCE LANDING WEIGHT........................................................ A
PER-FPL-FLP-QFP-30 EXAMPLE
EXAMPLE................................................................................................................................................................ A
PER-FPL-FLP-QFP-40 FLIGHT PLANNING AT A GIVEN MACH NUMBER
FLIGHT PLANNING M.78....................................................................................................................................... A
PER-FPL-FLP-QFP-50 FLIGHT PLANNING AT LONG RANGE SPEED
FLIGHT PLANNING LRC........................................................................................................................................ A
PER-FPL-FLP-ALN ALTERNATE
PER-FPL-FLP-ALN-20 ALL ENGINES OPERATIVE
GENERAL................................................................................................................................................................ A
CORRECTION FOR DEVIATION FROM REFERENCE WEIGHT......................................................................... B
ALTERNATE PLANNING ISA................................................................................................................................. C
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PER-FPL-PLP-TOC P 1/2
05 SEP 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
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PER-FPL-PLP-TOC P 2/2
05 SEP 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL - MINIMUM RECOMMENDED FUEL REQUIREMENTS
MINIMUM RECOMMENDED FUEL REQUIREMENTS
Ident.: PER-FPL-GEN-MFR-00001837.0001001 / 08 FEB 11
Applicable to: ALL
The total fuel quantity required to fly a given sector is the sum of the following quantities:
TAXI FUEL
Quantity required for startup and taxi. Fuel calculation is based on a consumption of 11.5 kg/min or
25 lb/min
Average quantity (12 min) → 140 kg or 300 lb
TRIP FUEL
Fuel required from departure to destination includes the following quantities:
‐ Takeoff and climb at selected speed.
‐ Cruise at selected speed.
‐ Descent from cruising level to 1 500 ft above destination airport.
‐ Approach and landing. Fuel calculation is based on a consumption of 20 kg/min or 45 lb/min
Average quantity (6 min IFR) →120 kg or 270 lb
RESERVE FUEL
This quantity includes :
“EN ROUTE” RESERVE FUEL (CONTINGENCY FUEL)
• According to national regulations and company policy (generally based on a percentage of
trip fuel).
ALTERNATE FUEL
• Fuel required to fly from destination to alternate airport.
It includes go-around 100 kg or 220 lb, climb to cruising level, cruise at long range speed,
descent and approach procedure.
80 kg or 180 lb for 4 min VFR
HOLDING FUEL
Calculation of holding fuel should take into account the altitude of the alternate and the landing
weight at the alternate. To use holding charts Refer to PER-HLD-GEN GENERAL.
A conservative quantity corresponding to a 30 min holding at 1 500 ft above alternate airport
elevation at “green dot” speed in the clean configuration is 1 200 kg or 2 700 lb
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A→
PER-FPL-GEN-MFR P 1/2
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GENERAL - MINIMUM RECOMMENDED FUEL REQUIREMENTS
APU FUEL
During ground operations, APU fuel consumption is about 130 kg/h or 290 lb/h (Packs ON,
90 KVA load on APU GEN).
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FCOM
←A
PER-FPL-GEN-MFR P 2/2
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
GENERAL - FLIGHT PLAN
FLIGHT CREW
OPERATING MANUAL
FLIGHT PLAN
Ident.: PER-FPL-GEN-FPL-00001835.0001001 / 22 MAR 11
Applicable to: ALL
When no precalculated flight plan is available, flight planning can be determined by using the tables
given in this chapter.
Fuel policy will be the same as for precalculated flight plan.
The graph on the following page defines the different terms used in this chapter.
GLG A318/A319/A320/A321 For A/C: HC-CRU
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A
PER-FPL-GEN-FPL P 1/2
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
GENERAL - FLIGHT PLAN
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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FCOM
PER-FPL-GEN-FPL P 2/2
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
INTRODUCTION
INTRODUCTION
Ident.: PER-FPL-FLP-QFP-10-00001827.0003001 / 02 MAY 12
Applicable to: ALL
The following flight planning tables allow the planner to determine trip fuel consumption and trip time
required to cover a given air distance.
These tables are established for:
‐ Takeoff
‐ Climb profile 250 kt/300 kt/M 0.78
‐ Cruise Mach number M 0.78/LR
‐ Descent profile M 0.78/300 kt/250 kt
‐ Approach and landing 120 kg - 6 min IFR
‐ ISA
‐ CG = 33 %
‐ Normal air conditioning
‐ Anti ice OFF
They are based upon a reference landing weight of 55 000 kg and have been calculated using
databases for CFM 56–5–B/P. If the engines fitted on the aircraft are neither /P, nor /3, the fuel
consumption has to be increased by 3 %.
Note:
1. In the tables, the asterisk (*) means that a step climb of 4 000 ft must be flown to reach
the corresponding FL.
2. To obtain a flight plan at optimum cruise level, the highest flight level desired within the
flight has to be selected in the table.
3. For each degree Celcius above ISA temperature apply fuel correction 0.015 (kg/°C/NM)
× ΔISA (°C) × Air Distance (NM).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-FPL-FLP-QFP-10 P 1/2
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
Intentionally left blank
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PER-FPL-FLP-QFP-10 P 2/2
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
CORRECTION FOR DEVIATION FROM REFERENCE LANDING WEIGHT
CORRECTION FOR DEVIATION FROM REFERENCE LANDING WEIGHT
Ident.: PER-FPL-FLP-QFP-20-00001828.0001001 / 03 MAR 11
Applicable to: ALL
The fuel consumption must be corrected when the actual landing weight is different from the
reference landing weight.
If it is lower (or greater) than the reference landing weight, subtract (or add) the value given in the
correction part of the table per 1 000 kg below (or above) the reference landing weight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-FPL-FLP-QFP-20 P 1/2
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
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PER-FPL-FLP-QFP-20 P 2/2
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PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
EXAMPLE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-FPL-FLP-QFP-30 P 1/6
05 SEP 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
EXAMPLE
Ident.: PER-FPL-FLP-QFP-30-00014738.0001001 / 04 JUL 17
Applicable to: ALL
INTRODUCTION
This section provides an example explaining step by step how to perform a quick planning.
This example is based on an A320-232 aircraft, which most likely does not reflect your actual
aircraft. Nevertheless, the principle is valid for any aircraft, provided the appropriate performance
tables are used.
For actual calculations, access the appropriate tables corresponding to your current aircraft and
desired flight profile by following the "refer to" indications specified at each step, and do not use
the tables provided in the example.
EXAMPLE
The example is based on the following parameters:
‐
‐
‐
‐
‐
‐
‐
‐
‐
‐
‐
Aircraft used for the example
Zero Fuel Weight
Temperature
Air conditioning
Anti-ice
Cruise
Departure - destination ground distance
Average wind on the leg to destination
Reserve fuel
Destination - alternate ground distance
Average wind on the leg to alternate
A320-232
60 000 kg
ISA conditions
Normal
Off
M 0.78 at FL 370
1 800 NM
-40 kt (headwind)
5%
200 NM at FL 200
0 kt
To calculate the flight plan, it is necessary to start from the minimum landing fuel at the alternate
airport.
1. Determine the 30 minutes holding fuel required at alternate airport (at 1 500 ft AGL).
(Refer to PER-FPL-GEN-MFR MINIMUM RECOMMENDED FUEL REQUIREMENTS for actual
30 min fuel value).
For the example, the conservative value of 1 200 kg is chosen.
The resulting landing weight at alternate is 60 000 + 1 200 = 61 200 kg.
2. Determine time, trip fuel, and fuel correction for the leg from destination to alternate airport:
GLG A318/A319/A320/A321 For A/C: HC-CRU
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PER-FPL-FLP-QFP-30 P 2/6
05 SEP 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
a. Convert the ground distance to air distance.
(Refer to PER-OPD-CON-AEO GENERAL for conversion).
On this leg, the average wind is zero. Therefore, the air distance equals the ground distance.
b. Enter the table with the air distance and desired flight level to obtain time, trip fuel, and fuel
correction.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-FPL-FLP-QFP-30 P 3/6
05 SEP 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
(Refer to PER-FPL-FLP-ALN-20 GENERAL for actual table).
For 200 NM air distance at FL 200, the table provides 0 h 38 min, 1 573 kg and
9 kg/1 000 kg.
c. Calculate the fuel burn correction regarding the estimated landing weight at the alternate
airport.
Table reference weight
: 55 000 kg
Estimated landing weight : 61 200 kg
Fuel correction 9 kg per 1 000 kg difference
The extra fuel burn is (61.2 - 55.0) x 9 = 56 kg.
d. Calculate the total trip fuel from destination to alternate.
Trip fuel : 1 573 + 56 = 1 629 kg
The estimated landing weight at destination is 61 200 + 1 629 = 62 829 kg.
3. Determine time, trip fuel, and fuel correction for the leg from departure to destination airport at
M 0.78:
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-FPL-FLP-QFP-30 P 4/6
05 SEP 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
a. Convert the ground distance to air distance.
(Refer to PER-OPD-CON-AEO GENERAL for conversion).
For 1 800 NM ground distance and 40 kt headwind at M 0.78, the interpolation from the table
provides 1 979 NM air distance.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-FPL-FLP-QFP-30 P 5/6
05 SEP 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
b. Enter the table with the air distance and desired flight level to obtain time, trip fuel, and fuel
correction.
(Refer to PER-FPL-FLP-QFP-40 FLIGHT PLANNING M.78 for actual M 0.78 table).
For 1 979 NM air distance at FL 370, the interpolation from the M 0.78 table provides 4 h
38 min, 10 226 kg and 146 kg/10 000 kg.
c. Calculate the fuel burn correction regarding the estimated landing weight at the destination
airport.
Table reference weight
: 55 000 kg
Estimated landing weight : 62 829 kg
Fuel correction 146 kg per 1 000 kg difference
The extra fuel burn is (62.829 - 55) x 146 = 1 143 kg.
d. Calculate the total trip fuel from departure to destination.
Trip fuel : 10 226 + 1 143 = 11 369 kg
4. Determine the contingency (reserve) fuel.
(Refer to company policy for fuel reserve value).
The five percent of the departure - destination trip fuel is:
11 369 x 0.05 = 568 kg.
5. Determine the taxi fuel at departure.
(Refer to PER-FPL-GEN-MFR MINIMUM RECOMMENDED FUEL REQUIREMENTS for actual
taxi fuel).
For the example, the conservative value of 140 kg (12 min taxi time) is chosen.
6. Calculate the final block fuel.
‐
‐
‐
‐
‐
30 min holding at alternate (1 500 ft AGL)
Trip fuel to alternate
Trip fuel to destination
Contingency (reserve) fuel
Taxi fuel
1 200 kg
1 629 kg
11 369 kg
568 kg
140 kg
Total block fuel
Block weight
14 906 kg
74 906 kg
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-FPL-FLP-QFP-30 P 6/6
05 SEP 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
FLIGHT PLANNING AT A GIVEN MACH NUMBER
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-FPL-FLP-QFP-40 P 1/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
FLIGHT PLANNING M.78
Ident.: PER-FPL-FLP-QFP-40-00001830.0024001 / 25 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-FPL-FLP-QFP-40 P 2/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-FPL-FLP-QFP-40 P 3/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-FPL-FLP-QFP-40 P 4/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-FPL-FLP-QFP-40 P 5/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-FPL-FLP-QFP-40 P 6/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
FLIGHT PLANNING AT LONG RANGE SPEED
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-FPL-FLP-QFP-50 P 1/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
FLIGHT PLANNING LRC
Ident.: PER-FPL-FLP-QFP-50-00001831.0071001 / 17 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-FPL-FLP-QFP-50 P 2/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-FPL-FLP-QFP-50 P 3/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-FPL-FLP-QFP-50 P 4/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-FPL-FLP-QFP-50 P 5/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
FLIGHT PREPARATION - QUICK DETERMINATION OF FLIGHT PLANNING
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-FPL-FLP-QFP-50 P 6/6
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT PREPARATION - ALTERNATE
FLIGHT CREW
OPERATING MANUAL
ALL ENGINES OPERATIVE
GENERAL
Ident.: PER-FPL-FLP-ALN-20-00001832.0009001 / 25 FEB 14
Applicable to: ALL
The alternate planning tables enable the flight crew to determine the fuel consumption and time
required to cover a given air distance from go-around at destination airport to landing at alternate
airport.
These tables are established for:
‐ Go-around: 100 kg or 220 lb
‐ Climb profile: 250 kt/300 kt/M .78
‐ Long range speed
‐ Descent profile: M .78/300 kt/250 kt
‐ Approach and landing at alternate airport: 80 kg or 180 lb (4 min)
‐ ISA
‐ CG = 33 %
‐ Normal air conditioning
‐ Anti ice OFF
Following tables have been calculated using databases for CFM 56–5–B /P. If the engines fitted on
the aircraft are not /P or /3, the fuel consumption has to be increased by 3 %.
Note:
1. In the tables, the asterisk (*) means that a step climb of 4 000 ft must be flown to reach
the corresponding flight level.
2. The flight level shown on the top of each column is the final flight level.
3. For each degree Celsius above ISA temperature apply a fuel correction of
0.015 (kg/°C/NM) × ΔISA (°C) × Air distance (NM)
or 0.033 (lb/°C/NM) × ΔISA (°C) × Air distance (NM)
CORRECTION FOR DEVIATION FROM REFERENCE WEIGHT
Ident.: PER-FPL-FLP-ALN-20-00001834.0001001 / 28 FEB 11
Applicable to: ALL
The alternate planning tables are based on a reference landing weight at alternate.
The fuel consumption must be corrected when the landing weight is different from the reference
landing weight.
If it is lower (or greater) than the reference weight, subtract (or add) the value given in the correction
part of the table per 1 000 kg or 1 000 lb below (or above) the reference weight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-FPL-FLP-ALN-20 P 1/4
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT PREPARATION - ALTERNATE
FLIGHT CREW
OPERATING MANUAL
ALTERNATE PLANNING ISA
Ident.: PER-FPL-FLP-ALN-20-00001833.0025001 / 02 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PER-FPL-FLP-ALN-20 P 2/4
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
FLIGHT PREPARATION - ALTERNATE
←C
PER-FPL-FLP-ALN-20 P 3/4
24 JAN 17
PERFORMANCE
FLIGHT PLANNING
A318/A319/A320/A321
FLIGHT PREPARATION - ALTERNATE
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-FPL-FLP-ALN-20 P 4/4
24 JAN 17
PERFORMANCE
CLIMB
Intentionally left blank
PERFORMANCE
CLIMB
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-CLB-GEN GENERAL
GENERAL................................................................................................................................................................ A
PER-CLB-CLT CLIMB TABLES
CLIMB - ISA +10..................................................................................................................................................... A
CLIMB - ISA +20..................................................................................................................................................... B
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-CLB-PLP-TOC P 1/2
24 JAN 17
PERFORMANCE
CLIMB
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-CLB-PLP-TOC P 2/2
24 JAN 17
PERFORMANCE
CLIMB
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PER-CLB-GEN-00001982.0001001 / 15 FEB 11
Applicable to: ALL
Climb tables are established at MAX CLIMB THRUST with air conditioning in normal mode and anti
ice OFF.
The climb speed profile is :
‐ 250 kt from 1 500 ft up to FL 100
‐ acceleration from 250 kt to 300 kt
‐ climb at 300 kt then M .78 up to selected altitude.
All charts are established with a center of gravity corresponding to 33 %.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-CLB-GEN P 1/2
24 JAN 17
PERFORMANCE
CLIMB
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-CLB-GEN P 2/2
24 JAN 17
PERFORMANCE
CLIMB
A318/A319/A320/A321
CLIMB TABLES
FLIGHT CREW
OPERATING MANUAL
CLIMB - ISA +10
Ident.: PER-CLB-CLT-00001987.0065001 / 15 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-CLB-CLT P 1/4
24 JAN 17
PERFORMANCE
CLIMB
A318/A319/A320/A321
CLIMB TABLES
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-CLB-CLT P 2/4
24 JAN 17
PERFORMANCE
CLIMB
A318/A319/A320/A321
CLIMB TABLES
FLIGHT CREW
OPERATING MANUAL
CLIMB - ISA +20
Ident.: PER-CLB-CLT-00001989.0021001 / 15 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-CLB-CLT P 3/4
24 JAN 17
PERFORMANCE
CLIMB
A318/A319/A320/A321
CLIMB TABLES
FLIGHT CREW
OPERATING MANUAL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PER-CLB-CLT P 4/4
24 JAN 17
PERFORMANCE
CRUISE
Intentionally left blank
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-CRZ-ALT ALTITUDE
PER-CRZ-ALT-10 OPTIMUM AND MAXIMUM ALTITUDES
DEFINITIONS...........................................................................................................................................................A
PER-CRZ-ALT-20 WIND ALTITUDE TRADE FOR CONSTANT SPECIFIC RANGE
WIND ALTITUDE TRADE FOR CONSTANT SPECIFIC RANGE.......................................................................... A
PER-CRZ-CRT CRUISE TABLES
PER-CRZ-CRT-10 GENERAL
GENERAL................................................................................................................................................................ A
PER-CRZ-CRT-20 CRUISE AT M.78
CRUISE - M.78 - ISA.............................................................................................................................................. A
CRUISE - M.78 - ISA+20........................................................................................................................................ B
PER-CRZ-CRT-30 CRUISE AT LONG RANGE
LONG RANGE CRUISE - ISA................................................................................................................................ A
LONG RANGE CRUISE - ISA+20.......................................................................................................................... B
PER-CRZ-ICQ IN CRUISE QUICK CHECK
PER-CRZ-ICQ-10 GENERAL
GENERAL................................................................................................................................................................ A
CORRECTION FOR DEVIATION FROM REFERENCE WEIGHT......................................................................... B
PER-CRZ-ICQ-20 EXAMPLE
EXAMPLE FOR THE QRH USE.............................................................................................................................A
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-CRZ-PLP-TOC P 1/2
22 MAR 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-CRZ-PLP-TOC P 2/2
22 MAR 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ALTITUDE - OPTIMUM AND MAXIMUM ALTITUDES
DEFINITIONS
Ident.: PER-CRZ-ALT-10-00001995.0001001 / 22 MAR 17
Applicable to: ALL
• Optimum altitude : the altitude at which the airplane covers the maximum distance per kilogram
(pound) of fuel (best specific range). It depends on the actual weight and the deviation from ISA.
• Maximum altitude is defined as the lower of:
‐ maximum altitude at maximum cruise thrust in level flight and
‐ maximum altitude at maximum climb thrust with 300 ft/min vertical speed.
Refer to QRH/PER-M Optimum & Maximum Altitudes (Paper Only) or use the performance
application of FlySmart with Airbus.
The QRH charts are established for a center of gravity at 33 % MAC.
Maximum and optimum altitudes are given for different temperatures at long range speed and
M 0.78.
Note:
1. The n = 1.3 g (n = 1.4 g) curve indicates the buffet margin.
2. Definition of the maximum altitude in the FMGC is different (Refer to DSC-22_20-50-10
MCDU).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-CRZ-ALT-10 P 1/2
22 MAR 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ALTITUDE - OPTIMUM AND MAXIMUM ALTITUDES
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-CRZ-ALT-10 P 2/2
22 MAR 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ALTITUDE - WIND ALTITUDE TRADE FOR CONSTANT SPECIFIC RANGE
WIND ALTITUDE TRADE FOR CONSTANT SPECIFIC RANGE
Ident.: PER-CRZ-ALT-20-00001998.0007001 / 10 DEC 09
Applicable to: ALL
GIVEN
:
FIND
:
RESULTS :
Weight : 65 000 kg (143 300 lb)
Wind at FL 350 : 10 kt head
Minimum wind difference to descend to FL 310 : (40 - 4) = 36 kt
Descent to FL 310 may be considered provided the tail wind at this altitude is more
than (36 - 10) = 26 kt.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-CRZ-ALT-20 P 1/2
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
ALTITUDE - WIND ALTITUDE TRADE FOR CONSTANT SPECIFIC RANGE
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-CRZ-ALT-20 P 2/2
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
CRUISE TABLES - GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PER-CRZ-CRT-10-00004112.0002001 / 01 DEC 14
Applicable to: ALL
Cruise tables are established:
‐ for ISA and ISA + 20
‐ with normal air conditioning and anti ice OFF
‐ from FL 290 to FL 390 at M 0.78
‐ from FL 100 to FL 390 at long range speed
‐ with a 33 % center of gravity.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-CRZ-CRT-10 P 1/2
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
CRUISE TABLES - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-CRZ-CRT-10 P 2/2
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
CRUISE TABLES - CRUISE AT M.78
FLIGHT CREW
OPERATING MANUAL
CRUISE - M.78 - ISA
Ident.: PER-CRZ-CRT-20-00002005.0010001 / 09 DEC 09
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-CRZ-CRT-20 P 1/4
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - CRUISE AT M.78
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-CRZ-CRT-20 P 2/4
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
CRUISE TABLES - CRUISE AT M.78
FLIGHT CREW
OPERATING MANUAL
CRUISE - M.78 - ISA+20
Ident.: PER-CRZ-CRT-20-00002015.0009001 / 09 DEC 09
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-CRZ-CRT-20 P 3/4
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - CRUISE AT M.78
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PER-CRZ-CRT-20 P 4/4
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
CRUISE TABLES - CRUISE AT LONG RANGE
FLIGHT CREW
OPERATING MANUAL
LONG RANGE CRUISE - ISA
Ident.: PER-CRZ-CRT-30-00002018.0009001 / 10 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-CRZ-CRT-30 P 1/4
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - CRUISE AT LONG RANGE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-CRZ-CRT-30 P 2/4
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
CRUISE TABLES - CRUISE AT LONG RANGE
FLIGHT CREW
OPERATING MANUAL
LONG RANGE CRUISE - ISA+20
Ident.: PER-CRZ-CRT-30-00002033.0009001 / 10 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-CRZ-CRT-30 P 3/4
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - CRUISE AT LONG RANGE
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PER-CRZ-CRT-30 P 4/4
24 JAN 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IN CRUISE QUICK CHECK - GENERAL
GENERAL
Ident.: PER-CRZ-ICQ-10-00002036.0001001 / 22 MAR 17
Applicable to: ALL
In cruise, a quick check table (Refer to QRH/PER-M In Cruise Quick Check at a Given Mach Number
(Paper Only) or use the performance application of FlySmart with Airbus) allows the flight crew to
determine the fuel consumption and the time required to cover a given air distance from any moment
in cruise to land.
The QRH table is established for:
‐ Cruise Mach number: M 0.78
‐ Descent profile: M 0.78/300 kt/250 kt
‐ Approach and landing: 120 kg or 270 lb -6 min IMC
‐ ISA
‐ CG = 33 %
‐ Normal air conditioning
‐ Anti ice OFF
Note:
1. In the table, the asterisk “*” means that a step climb of 4 000 ft has been made to reach
the corresponding flight level.
2. The flight level shown on the top of each column is the final flight level.
3. For each degree celsius above ISA apply a fuel correction of
0.005 (kg/°C/NM) × ΔISA (°C) × Air Distance (NM)
or 0.011 (lb/°C/NM) × ΔISA (°C) × Air Distance (NM)
CORRECTION FOR DEVIATION FROM REFERENCE WEIGHT
Ident.: PER-CRZ-ICQ-10-00002039.0001001 / 22 MAR 16
Applicable to: ALL
The in cruise quick check table is based on a reference initial weight.
The fuel consumption must be corrected when the actual weight is different from the reference initial
weight.
If it is lower (or greater) than the reference weight, subtract (or add) the value given in the correction
part of the table per 1 000 kg or 1 000 lb below (or above) the reference weight.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-CRZ-ICQ-10 P 1/2
22 MAR 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
IN CRUISE QUICK CHECK - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-CRZ-ICQ-10 P 2/2
22 MAR 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
IN CRUISE QUICK CHECK - EXAMPLE
FLIGHT CREW
OPERATING MANUAL
EXAMPLE FOR THE QRH USE
Ident.: PER-CRZ-ICQ-20-00014741.0001001 / 22 MAR 17
Applicable to: ALL
The following data and graphs are for example only, and are not for operational use. Even if the data
in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
In-cruise quick check with cruise at M.78
FL 370
Actual cruise weight
: 55 000 kg
Remaining ground distance
: 800 NM
ISA +10
Average wind during flight
: -40 kt (head wind)
‐ Evaluation of air distance to be covered
• Use the “Ground Distance/Air Distance” conversion table (Refer to PER-OPD-CON-AEO M.78)
GROUND TAILWIND
DIST. (NM)
+150
7
10
15
20
22
30
30
40
37
50
75
100
150
200
225
300
300
400
375
500
750
1000
1125
1500
1500
2000
1875
2500
2250
3000
2624
3500
2999
4000
3374
4500
3749
5000
AIR DISTANCE (NM) - M.78
+100
8
16
25
33
41
82
164
245
327
409
818
1227
1636
2045
2454
2863
3272
3681
4090
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
WIND COMPONENTS (KT)
+50
9
18
27
36
45
90
180
270
360
450
900
1350
1800
2250
2700
3150
3600
4050
4500
A→
0
10
20
30
40
50
100
200
300
400
500
1000
1500
2000
2500
3000
3500
4000
4500
5000
-50
11
23
34
45
56
113
225
338
450
563
1125
1688
2250
2813
3375
3938
4500
5063
5626
-100
13
26
39
51
64
129
257
386
514
643
1286
1929
2572
3215
3858
4501
5144
5787
6430
HEADWIND
-150
15
30
45
60
75
150
300
450
600
750
1501
2251
3001
3752
4502
5252
6003
6753
7503
PER-CRZ-ICQ-20 P 1/4
22 MAR 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IN CRUISE QUICK CHECK - EXAMPLE
The corresponding air distance is : 880 NM
‐ Determination of the fuel consumption and time for the reference initial weight in cruise.
• Enter table (Refer to QRH/PER-M In Cruise Quick Check at a Given Mach Number (Paper
Only)) with an air distance of 880 NM and FL 370 for ISA.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A→
PER-CRZ-ICQ-20 P 2/4
22 MAR 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IN CRUISE QUICK CHECK - EXAMPLE
Fuel consumption : 4 053 kg
Time needed : 2 h 07 min
‐ Correction due to real in cruise weight of 55 000 kg
Δ fuel consumption
: -51 kg per 1 000 kg below reference
Δ fuel
: -51 × (60 - 55) = -255 kg
‐ Temperature correction :
Δ fuel consumption
: +0.005 kg per 1 °above ISA and per 1 NM Air distance
Δ fuel
: +0.005 × 10 × 880 = 44 kg
RESULT
Fuel :
Time :
4 053 - 255 + 44 = 3 842 kg
2 h 07 min
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-CRZ-ICQ-20 P 3/4
22 MAR 17
PERFORMANCE
CRUISE
A318/A319/A320/A321
IN CRUISE QUICK CHECK - EXAMPLE
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-CRZ-ICQ-20 P 4/4
22 MAR 17
PERFORMANCE
HOLDING
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PERFORMANCE
HOLDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-HLD-GEN GENERAL
GENERAL................................................................................................................................................................ A
PER-HLD-HLD HOLDING TABLES
CONF 0 - GREEN DOT SPEED.............................................................................................................................A
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FCOM
PER-HLD-PLP-TOC P 1/2
24 JAN 17
PERFORMANCE
HOLDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
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PER-HLD-PLP-TOC P 2/2
24 JAN 17
PERFORMANCE
HOLDING
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PER-HLD-GEN-00002129.0001001 / 01 DEC 14
Applicable to: ALL
Holding table contains information about the total fuel flow that allows the flight crew to plan holding
and reserve fuel requirements.
It is established for flight in a race track holding pattern in clean configuration at green dot speed.
This chart is established with air conditioning in normal mode and the center of gravity at 33 %.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-HLD-GEN P 1/2
24 JAN 17
PERFORMANCE
HOLDING
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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FCOM
PER-HLD-GEN P 2/2
24 JAN 17
PERFORMANCE
HOLDING
A318/A319/A320/A321
HOLDING TABLES
FLIGHT CREW
OPERATING MANUAL
CONF 0 - GREEN DOT SPEED
Ident.: PER-HLD-HLD-00002146.0023001 / 16 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-HLD-HLD P 1/2
24 JAN 17
PERFORMANCE
HOLDING
A318/A319/A320/A321
HOLDING TABLES
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
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FCOM
PER-HLD-HLD P 2/2
24 JAN 17
PERFORMANCE
DESCENT
Intentionally left blank
PERFORMANCE
DESCENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-DES-GEN GENERAL
GENERAL................................................................................................................................................................ A
PER-DES-STD STANDARD
DESCENT- M.78/300KT/250KT...............................................................................................................................A
PER-DES-EMG EMERGENCY
EMER Descent........................................................................................................................................................ A
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FCOM
PER-DES-PLP-TOC P 1/2
22 MAR 17
PERFORMANCE
DESCENT
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
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FCOM
PER-DES-PLP-TOC P 2/2
22 MAR 17
PERFORMANCE
DESCENT
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PER-DES-GEN-00002131.0001001 / 09 DEC 09
Applicable to: ALL
Descent tables are established for normal descent speed M .78 / 300 kt /250 kt and emergency
descent at MMO/VMO with airbrakes extended, down to 1 500 ft with :
• Normal air conditioning
• CG = 33 %
• Anti ice OFF
For normal descent, cabin vertical speed is limited to 350 ft/min
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-DES-GEN P 1/2
24 JAN 17
PERFORMANCE
DESCENT
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-DES-GEN P 2/2
24 JAN 17
PERFORMANCE
DESCENT
A318/A319/A320/A321
STANDARD
FLIGHT CREW
OPERATING MANUAL
DESCENT- M.78/300KT/250KT
Ident.: PER-DES-STD-00002133.0037001 / 09 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-DES-STD P 1/2
24 JAN 17
PERFORMANCE
DESCENT
A318/A319/A320/A321
STANDARD
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-DES-STD P 2/2
24 JAN 17
PERFORMANCE
DESCENT
A318/A319/A320/A321
EMERGENCY
FLIGHT CREW
OPERATING MANUAL
EMER DESCENT
Ident.: PER-DES-EMG-00002134.0201001 / 21 MAR 17
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-DES-EMG P 1/2
22 MAR 17
PERFORMANCE
DESCENT
A318/A319/A320/A321
EMERGENCY
FLIGHT CREW
OPERATING MANUAL
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FCOM
PER-DES-EMG P 2/2
22 MAR 17
PERFORMANCE
GO AROUND
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PERFORMANCE
GO AROUND
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-GOA-GEN GENERAL
GENERAL................................................................................................................................................................ A
PROCEDURE.......................................................................................................................................................... B
PER-GOA-ACG APPROACH CLIMB LIMITING WEIGHT
PER-GOA-ACG-NOR NORMAL
CONF 2....................................................................................................................................................................A
CONF 3....................................................................................................................................................................B
PER-GOA-ACG-CAT CAT II
CAT II - CONF 2..................................................................................................................................................... A
CAT II - CONF 3..................................................................................................................................................... B
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-GOA-PLP-TOC P 1/2
22 MAR 17
PERFORMANCE
GO AROUND
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-GOA-PLP-TOC P 2/2
22 MAR 17
PERFORMANCE
GO AROUND
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PER-GOA-GEN-00002140.0001001 / 28 JAN 11
Applicable to: ALL
In the go around configuration corresponding to the all engine procedure, the minimum steady
gradient one engine inoperative required by the regulations is 2.1 % at a speed not exceeding 1.4
Vs. This requirement is also called approach climb performance by regulations.
The following tables allow to determine the go around limiting weight which satisfies the required
gradient with the certified go around configurations 3 and 2.
The required gradient of 2.1 % is considered at the airport reference altitude. The power setting
is “GO AROUND” thrust with the air conditioning ON. The speed is 1.23 Vs of the specified
configuration. For the occasional cases where approach climb performance is found restrictive, a
correction is given for an increased speed, up to 1.4 Vs.
Note:
Landing climb performance (2 engines running) is never limiting.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-GOA-GEN P 1/2
22 MAR 17
PERFORMANCE
GO AROUND
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
PROCEDURE
Ident.: PER-GOA-GEN-00002141.0001001 / 21 MAR 17
Applicable to: ALL
According to airport pressure altitude and temperature determine if the slats/flaps setting must be
restricted as a function of the landing weight, in order to meet the go around gradient requirement of
2.1 %.
Establish the final approach configuration with one more step of flaps. If the approach is interrupted,
retract the flaps by one step during the go-around.
In case of category 2 and 3 approaches, JAR -OPS requires a regulatory approach climb gradient of
2.5 % to be maintained.
Use the tables for CAT II & III approaches to determine the maximum approach climb limiting weight
according to airport pressure altitude and temperature.
Note:
1. If circumstances dictate, landing may be made at a weight corresponding to the
maximum structural takeoff weight. (Refer to PRO-ABN-MISC [QRH] OVERWEIGHT
LANDING).
2. When icing conditions are predicted during the flight and TAT is 10 °C or below and there
is an evidence of significant ice accretion, to take into account ice formation on the non
heated structure:
‐ Decrease the approach climb limiting weight by 4.5 %
‐ In CONF FULL, the approach speed must not be lower than VREF +5 kt, or
in CONF 3, the approach speed must not be lower than VLS +10 kt.
For Landing Performance assessment, refer to QRH PER-A.
3. In the following tables corrections for anti ice are only valid for OAT lower than 10 °C.
4. Use the CAT II tables in case of CAT III approach calculation.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PER-GOA-GEN P 2/2
22 MAR 17
PERFORMANCE
GO AROUND
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
APPROACH CLIMB LIMITING WEIGHT - NORMAL
CONF 2
Ident.: PER-GOA-ACG-NOR-00002142.0322001 / 24 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-GOA-ACG-NOR P 1/2
24 JAN 17
PERFORMANCE
GO AROUND
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
APPROACH CLIMB LIMITING WEIGHT - NORMAL
CONF 3
Ident.: PER-GOA-ACG-NOR-00002143.0387001 / 24 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PER-GOA-ACG-NOR P 2/2
24 JAN 17
PERFORMANCE
GO AROUND
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
APPROACH CLIMB LIMITING WEIGHT - CAT II
CAT II - CONF 2
Ident.: PER-GOA-ACG-CAT-00002144.0062001 / 24 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-GOA-ACG-CAT P 1/2
24 JAN 17
PERFORMANCE
GO AROUND
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
APPROACH CLIMB LIMITING WEIGHT - CAT II
CAT II - CONF 3
Ident.: PER-GOA-ACG-CAT-00002145.0062001 / 24 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PER-GOA-ACG-CAT P 2/2
24 JAN 17
PERFORMANCE
LANDING
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PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-LDG-GEN GENERAL
GENERAL................................................................................................................................................................ A
DISPATCH............................................................................................................................................................... B
Use of the Autobrake System................................................................................................................................. C
PER-LDG-CTA RUNWAY CONTAMINATION
PER-LDG-CTA-10 GENERAL
GENERAL................................................................................................................................................................ A
PER-LDG-CTA-20 DEFINITIONS
DEFINITIONS...........................................................................................................................................................A
EQUIVALENCES..................................................................................................................................................... B
PER-LDG-DIS DISPATCH
PER-LDG-DIS-MAT Runway Condition Assessment Matrix for Landing
Runway Condition Assessment Matrix for Landing.................................................................................................A
PER-LDG-DIS-RLD REQUIRED LANDING DISTANCES / MANUAL LANDING
RLD CONF FULL.................................................................................................................................................... A
RLD CONF 3........................................................................................................................................................... B
Example................................................................................................................................................................... C
PER-LDG-DIS-RLA REQUIRED LANDING DISTANCES
AUTOMATIC LANDING ON DRY RUNWAY.......................................................................................................... A
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FCOM
PER-LDG-PLP-TOC P 1/2
05 SEP 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-LDG-PLP-TOC P 2/2
05 SEP 17
PERFORMANCE
LANDING
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
GENERAL
Ident.: PER-LDG-GEN-00013287.0001001 / 19 APR 17
Applicable to: ALL
REQUIRED LANDING DISTANCE (RLD) AT DISPATCH
The RLD is the regulatory reference to be used for dispatch landing performance computation.
The RLD is the factored certified landing distance based on:
‐ Maximum manual braking initiated immediately after main gear touchdown
‐ Prompt selection of max reverse thrust, maintained to 70kt, and idle thrust to full stop (when
credit is used)
‐ Antiskid and all spoilers operative
‐ The regulatory dispatch factor.
MANUAL LANDING
CONTAMINATED RUNWAY
If the surface is contaminated, EU-OPS operators must use the longer of the RLD for wet
runway and the RLD for the applicable contaminant for dispatch.
AUTOMATIC LANDING
The RLD for automatic landing is defined as the RLD in manual landing corrected with the
increment given in AFM. These increments assume maximum manual braking from main gear
touchdown.
IN-FLIGHT LANDING DISTANCE
The flight crew should use the Landing Distances published in the QRH as the reference
for In-Flight landing performance computation. The In-Flight Landing Distances reflect the
performance achievable in a typical operational landing without margin, assuming realistic airborne
phase from threshold to touchdown and deceleration on ground to full stop.
The In-Flight Landing Distances consider:
‐ Airborne phase of 7 seconds from threshold to touchdown
‐ Maximum manual braking initiated immediately after main gear touchdown
‐ Normal system delays in braking activation in case of autobrake
‐ Prompt selection of max reverse thrust, maintained to 70kt, and idle thrust to full stop (when
credit is used)
‐ Antiskid and all spoilers operative.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-LDG-GEN P 1/4
19 JUN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
FACTORED IN-FLIGHT LANDING DISTANCE
The flight crew should apply an appropriate margin to the In-Flight Landing Distances published
in the QRH to account for operational variability (e.g. in wind and runway condition reporting) and
flying technique (e.g. speed and height above threshold, flare).
This factor should account for:
‐ The Applicable Regulations
‐ The Airline Policy
‐ The discretion of the Pilot.
The Factored In-Flight Landing Distance may in some cases, and in particular on contaminated
runway, exceed the RLD considered at dispatch.
The requirements for dispatch remain unchanged and are based on the RLD. However, when
arrival conditions are expected to be marginal it is recommended to make a preliminary calculation
of In-Flight Landing Distance or Factored In-Flight Landing Distance at dispatch in order to
nominate suitable destination alternates.
DISPATCH
Ident.: PER-LDG-GEN-00013288.0001001 / 18 MAR 11
Applicable to: ALL
The pilot must check before departure that the available runway length at destination is at least equal
to the required landing distance for the forecasted landing weight.
In case of aircraft system failure affecting landing distance known before the dispatch, the available
runway length must be at least equal to the required landing distance with failure, i.e. the required
landing distance without failure multiplied by the coefficient given in the Flight Manual or the MMEL.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
← A to B
PER-LDG-GEN P 2/4
19 JUN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
USE OF THE AUTOBRAKE SYSTEM
Ident.: PER-LDG-GEN-00012045.0001001 / 22 MAY 12
Applicable to: ALL
The autobrake system is designed to help the pilot in case of :
‐ aborted takeoff or
‐ landing on short runways or
‐ operation with low visibility weather conditions
Furthermore, it ensures a straight roll-out and optimizes the landing distance on contaminated
runways provided the contamination is evenly distributed.
At landing, select the braking mode according to :
‐ runway length
‐ configuration
‐ runway condition
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PER-LDG-GEN P 3/4
19 JUN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-LDG-GEN P 4/4
19 JUN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
RUNWAY CONTAMINATION - GENERAL
GENERAL
Ident.: PER-LDG-CTA-10-00013002.0001001 / 21 JUL 14
Applicable to: ALL
This section presents the recommendations of Airbus for operations from wet runways or from
runways which are covered with contaminants such as standing water, slush or snow.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-LDG-CTA-10 P 1/2
24 JAN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
RUNWAY CONTAMINATION - GENERAL
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-LDG-CTA-10 P 2/2
24 JAN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
RUNWAY CONTAMINATION - DEFINITIONS
FLIGHT CREW
OPERATING MANUAL
DEFINITIONS
Ident.: PER-LDG-CTA-20-00013004.0001001 / 31 AUG 17
Applicable to: ALL
DAMP
:
WET
:
FROST
:
COMPACTED SNOW :
SLIPPERY WHEN WET:
DRY SNOW
:
WET SNOW
:
STANDING WATER
:
SLUSH
:
ICE (Cold and Dry)
WET ICE
:
:
A runway is considered as damp, when the surface of the runway is not
dry, but the water on the surface does not cause a shiny appearance.
A runway is considered as wet, when the surface of the runway has a
shiny appearance due to a thin film of water. When this film does not
exceed 3 mm, there is no significant danger of hydroplaning.
The deposit of ice crystals on the runway is referred to as frost. The
direct sublimation of humidity contained in the air on a runway, when the
surface temperature is below freezing, causes frost.
The maintenance personnel use a snow groomer to compress snow on
a runway in order to obtain a hard surface.
Notice to Airmen (NOTAM) report a runway as "slippery when wet",
when the runway partially or entirely fails to satisfy the minimum
(regulatory) friction requirement of the responsible authority.
Dry snow is snow that, if compacted by hand, does not stay compressed
when released. The wind can blow dry snow. The density of dry snow is
approximately 0.2 kg/l (1.7 lb/US Gal).
Wet snow is snow that, if compacted by hand, stays compressed when
released, and with which snowballs can be created. The density of wet
snow is approximately 0.4 kg/l (3.35 lb/US Gal).
Standing water occurs due to heavy rain and/or insufficient runway
drainage with a depth of more than 3 mm.
Slush is snow soaked with water, which spatters when stepped on
firmly. Slush occurs at temperatures around 5 °C and has a density of
approximately 0.85 kg/l (7.1 lb/US Gal).
Situation in which ice occurs on the runway in cold and dry conditions.
When the ice on a runway melts, or there are loose/fluid contaminants
on top of the ice, the ice is referred to as "wet ice". When there is wet ice
on a runway, braking and directional control are difficult or not possible,
because the runway surface is very slippery.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-LDG-CTA-20 P 1/2
05 SEP 17
PERFORMANCE
LANDING
A318/A319/A320/A321
RUNWAY CONTAMINATION - DEFINITIONS
FLIGHT CREW
OPERATING MANUAL
EQUIVALENCES
Ident.: PER-LDG-CTA-20-00014917.0001001 / 21 JUL 14
Applicable to: ALL
For the below-listed reported contaminants, the following equivalent runway conditions can be
retained for the landing performance determination.
Reported contaminant
Type of contaminant
Depth of contaminant
Slush
Water
Wet snow
Dry snow
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
≤ 3 mm (1/8 in)
≤ 3 mm (1/8 in)
≤ 3 mm (1/8 in)
≤ 30 mm (6/5 in)
≤ 3 mm (1/8 in)
≤ 100 mm (4 in)
B
Equivalent Runway Condition
Wet
Slush
Wet
Slush
PER-LDG-CTA-20 P 2/2
05 SEP 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DISPATCH - RUNWAY CONDITION ASSESSMENT MATRIX FOR LANDING
RUNWAY CONDITION ASSESSMENT MATRIX FOR LANDING
Ident.: PER-LDG-DIS-MAT-00014450.0001001 / 17 MAR 17
Applicable to: ALL
Runway State or / and
Runway Contaminant
Dry
Damp
Wet
Up to 3 mm (1/8'') of water
Slush
Up to 3 mm (1/8'')
Dry snow
Up to 3 mm (1/8'')
Wet snow
Up to 3 mm (1/8'')
Frost
Compacted snow
OAT at or below -15 °C
Dry snow
More than 3 mm (1/8''), up to 100 mm
(4'')
Wet snow
More than 3 mm (1/8''), up to 30 mm
(6/5'')
Compacted snow
OAT above -15 °C
Dry snow over compacted snow
Wet snow over compacted snow
Slippery when wet
Water
More than 3 mm (1/8''), up to 12.7 mm
(1/2'')
Slush
More than 3 mm (1/8''), up to 12.7 mm
(1/2'')
Ice (cold & dry)
Related Landing
Performance
Observations on
Deceleration and
Directional Control
Code
Level
-
6
DRY
Maximum
Crosswind
for Landing
(Gust included)
38 kt
Good
Braking deceleration
is normal for the
wheel braking effort
applied. Directional
control is normal.
5
GOOD
38 kt
Good to
Medium
Braking deceleration
and controllability
is between Good
and Medium.
4
GOOD TO
MEDIUM
29 kt
Medium
Braking deceleration
is noticeably reduced
for the wheel braking
effort applied.
Directional control
may be reduced.
3
MEDIUM
25 kt
Medium
to Poor
Braking deceleration
and controllability is
between Medium and
Poor. Potential for
hydroplaning exists.
2
MEDIUM
TO POOR
20 kt
Poor
Braking deceleration
is significantly
reduced for the
wheel braking effort
applied. Directional
1
POOR
15 kt
Runway Surface Conditions
ESF(1) or
PIREP(2)
-
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
Continued on the following page
PER-LDG-DIS-MAT P 1/2
22 MAR 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DISPATCH - RUNWAY CONDITION ASSESSMENT MATRIX FOR LANDING
Runway Surface Conditions
Runway State or / and
Runway Contaminant
ESF or
PIREP(2)
(1)
Wet ice
Water on top of Compacted Snow
Dry Snow or Wet Snow over ice
Nil
(1)
ESF: Estimated Surface Friction
(2)
PIREP: Pilot Report of Braking Action
Note:
Observations on
Deceleration and
Directional Control
control may be
significantly reduced.
Braking deceleration
is minimal to
non-existant for
the wheel braking
effort applied.
Directional control
may be uncertain.
Continued from the previous page
Related Landing
Maximum
Performance
Crosswind
for Landing
Code
Level
(Gust included)
-
-
-
Refer for FCOM LIM-AFS chapter for Automatic Approach, Landing and Rollout limitations.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-LDG-DIS-MAT P 2/2
22 MAR 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DISPATCH - REQUIRED LANDING DISTANCES / MANUAL LANDING
RLD CONF FULL
Ident.: PER-LDG-DIS-RLD-00013995.0036001 / 22 MAY 12
Applicable to: ALL
The RLD in the first table considers: Sea Level (SL), ISA, no wind, no slope, no engine reverse
thrust, manual landing, and VAPP=VLS.
Runway State
Weight (1000 kg)
46
50
54
58
62
66
Runway State
Altitude
Speed
Wind
Reverse
CG
Per 1 000 ft
ABOVE SL
Per 5 kt
Per 5 kt TW
Per Thrust
Reverser Operative
Extended
Forward CG
Required landing distances (ft)
Compacted
Dry
Wet
snow
3 820
4 390
4 490
3 990
4 590
4 760
4 160
4 790
5 030
4 350
5 000
5 300
4 550
5 230
5 570
4 930
5 660
5 840
Corrections on landing distances (ft)
Compacted
Dry
Wet
snow
Slush
4 450
4 750
5 040
5 340
5 650
5 960
Standing
Water
4 600
4 900
5 210
5 550
5 960
6 390
Slush
Standing
Water
+ 180
+ 210
+ 260
+ 420
+ 410
+ 310
+ 480
+ 370
+ 550
+ 300
+ 510
+ 380
+ 780
+ 570
+ 1 070
-
-
- 240
- 240
- 250
+ 80
+ 110
+ 150
+ 140
+ 170
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-LDG-DIS-RLD P 1/6
24 JAN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DISPATCH - REQUIRED LANDING DISTANCES / MANUAL LANDING
RLD CONF 3
Ident.: PER-LDG-DIS-RLD-00013996.0036001 / 22 MAY 12
Applicable to: ALL
The RLD in the first table considers: Sea Level (SL), ISA, no wind, no slope, no engine reverse
thrust, manual landing, and VAPP=VLS.
Runway State
Weight (1000 kg)
46
50
54
58
62
66
Runway State
Altitude
Speed
Wind
Reverse
CG
Per 1 000 ft
ABOVE SL
Per 5 kt
Per 5 kt TW
Per Thrust
Reverser Operative
Extended
Forward CG
Required landing distances (ft)
Compacted
Dry
Wet
snow
4 070
4 680
4 900
4 270
4 900
5 200
4 460
5 120
5 490
4 670
5 370
5 780
4 980
5 730
6 080
5 470
6 290
6 380
Corrections on landing distances (ft)
Compacted
Dry
Wet
snow
Slush
4 890
5 220
5 540
5 880
6 220
6 630
Standing
Water
5 050
5 390
5 770
6 250
6 740
7 250
Slush
Standing
Water
+ 200
+ 230
+ 290
+ 490
+ 500
+ 340
+ 490
+ 390
+ 560
+ 320
+ 530
+ 500
+ 880
+ 660
+ 1 220
-
-
- 290
- 300
- 300
+ 90
+ 100
+ 170
+ 210
+ 200
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PER-LDG-DIS-RLD P 2/6
24 JAN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DISPATCH - REQUIRED LANDING DISTANCES / MANUAL LANDING
EXAMPLE
Ident.: PER-LDG-DIS-RLD-00014743.0001001 / 29 JUL 16
Applicable to: ALL
EXAMPLE 1
The following data and graphs are for example only, and are not for operational use. Even if the
data in the following example is in “kg” and “m”, the same method can be applied for “lb” and “ft”.
Required Landing Distance (RLD) determination with multiple corrections
Data: Landing CONF = CONF FULL
LW = 58 T
DRY runway
Airport altitude = 2 000 ft
Approach speed = VLS
5 kt TW
ISA conditions
No slope
Read the reference distance for 58 T from RLD table:
Required Landing Distances (m)
Compacted
Dry
Wet
Slush
snow
1 150
1 320
1 310
1 300
Do not use for operational purpose
1 260
1 450
1 480
1 480
1 320
1 510
1 560
1 570
1 380
1 580
1 640
1 670
1 480
1 710
1 730
1 760
Runway State
Weight (1000 kg)
46
50
54
58
62
66
Standing
Water
1 350
1 530
1 630
1 750
1 880
RLD (DRY, 0 ft, VLS, no wind) = 1 320 m
Read the different corrections:
Runway State
Altitude
Speed
Wind
Reverse
CG
Per 1 000 ft
ABOVE SL
Per 5 kt
Per 5 kt TW
Per Thrust
Reverser Operative
Extended
Forward CG
Corrections on Landing Distances (m)
Compacted
Dry
Wet
snow
Slush
Standing
Water
+ 60
+ 70
+ 90
+ 130
+ 140
+ 100
+ 140
+ 100
+ 170
+ 80
+ 150
+ 110
+ 220
+ 160
+ 300
-
-
- 90
- 90
- 110
+ 30
+ 30
+ 40
+ 40
+ 50
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PER-LDG-DIS-RLD P 3/6
24 JAN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DISPATCH - REQUIRED LANDING DISTANCES / MANUAL LANDING
Altitude correction: 60 x 2 = +120 m
Wind correction: 140 x 1 = +140 m
RLD (DRY, 2 000 ft, VLS, 5 kt TW) = 1 320 + 120 + 140 = 1 580 m
EXAMPLE 2
Required Landing Distance (RLD) calculation with WET CHECK (Mandatory for EASA
operators)
Data: Landing CONF = CONF FULL
LW = 58 T
Runway covered with STANDING WATER
Airport altitude = 2 000 ft
Approach speed = VLS
Credit for all thrust reversers
ISA conditions
No slope
Runway State
Weight (1000 kg)
46
50
54
58
62
66
Runway State
Altitude
Speed
Wind
Reverse
CG
Per 1 000 ft
ABOVE SL
Per 5 kt
Per 5 kt TW
Per Thrust
Reverser Operative
Extended
Forward CG
Required Landing Distances (m)
Compacted
Dry
Wet
snow
1 150
1 320
1 310
1 210
1 390
1 400
1 260
1 450
1 480
1 320
1 510
1 560
1 380
1 580
1 640
1 480
1 710
1 730
Corrections on Landing Distances (m)
Compacted
Dry
Wet
snow
Slush
1 300
1 390
1 480
1 570
1 670
1 760
Standing
Water
1 350
1 440
1 530
1 630
1 750
1 880
Slush
Standing
Water
+ 60
+ 70
+ 90
+ 130
+ 140
+ 100
+ 140
+ 100
+ 170
+ 80
+ 150
+ 110
+ 220
+ 160
+ 300
-
-
- 90
- 90
- 110
+ 30
+ 30
+ 40
+ 40
+ 50
RLD (WATER, 2 000 ft, VLS, no wind, all reversers) = 1 630 + 140 x 2 - 110 x 2 = 1 690 m
Compare this distance to the landing distance in the same conditions on WET runway:
RLD (WET, 2 000 ft, VLS, no wind) = 1 510 + 70 x 2 = 1 650 m
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C→
PER-LDG-DIS-RLD P 4/6
24 JAN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DISPATCH - REQUIRED LANDING DISTANCES / MANUAL LANDING
RLD (WET) < RLD (WATER), therefore RLD = 1 690 m
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PER-LDG-DIS-RLD P 5/6
24 JAN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DISPATCH - REQUIRED LANDING DISTANCES / MANUAL LANDING
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-LDG-DIS-RLD P 6/6
24 JAN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DISPATCH - REQUIRED LANDING DISTANCES
AUTOMATIC LANDING ON DRY RUNWAY
Ident.: PER-LDG-DIS-RLA-00013359.0204001 / 18 MAR 11
Applicable to: ALL
Determine the corrected required landing distance for manual landing from the data above.
The required landing distance for automatic landing is equal to the corrected required landing
distance for manual landing except in the following case:
‐ In case of landing in CONF 3 with landing weight equal to or less than 55 000 kg and with no wind
or headwind, it is equal to the corrected required landing distance for manual required landing
increased by 310 ft.
‐ In case of landing in CONF FULL with landing weight equal to or less than 70 000 kg it is equal to
the corrected required landing distance for manual required landing increased by 290 ft.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-LDG-DIS-RLA P 1/2
24 JAN 17
PERFORMANCE
LANDING
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DISPATCH - REQUIRED LANDING DISTANCES
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-LDG-DIS-RLA P 2/2
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
Intentionally left blank
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-OEI-GEN GENERAL
INTRODUCTION......................................................................................................................................................A
FLIGHT PREPARATION......................................................................................................................................... B
STRATEGY..............................................................................................................................................................C
PER-OEI-ALT ALTITUDE
PER-OEI-ALT-10 CEILINGS
Ceilings.....................................................................................................................................................................A
PER-OEI-CRT CRUISE TABLES
PER-OEI-CRT-10 STANDARD AND OBSTACLE STRATEGIES
LONG RANGE CRUISE - 1 ENGINE OUT - ISA................................................................................................... A
LONG RANGE CRUISE - 1 ENGINE OUT - ISA +20............................................................................................B
PER-OEI-CRT-20 FIXED SPEED STRATEGIES
CRUISE - MCT/VMO - 1 ENGINE OUT - ISA........................................................................................................A
CRUISE - MCT/VMO - 1 ENGINE OUT - ISA +20.................................................................................................B
CRUISE - MCT/320KT - 1 ENGINE OUT - ISA..................................................................................................... C
CRUISE - MCT/320KT - 1 ENGINE OUT - ISA +20.............................................................................................. D
PER-OEI-ICQ IN CRUISE QUICK CHECK
PER-OEI-ICQ-10 STANDARD STRATEGIES
IN CRUISE QUICK CHECK AT LONG RANGE SPEED........................................................................................A
CORRECTION FOR DEVIATION FROM REFERENCE WEIGHT......................................................................... B
PER-OEI-ICQ-20 FIXED SPEED STRATEGIES
GENERAL................................................................................................................................................................ A
CORRECTION FOR DEVIATION FROM REFERENCE WEIGHT......................................................................... B
IN CRUISE QUICK CHECK VMO.......................................................................................................................... C
IN CRUISE QUICK CHECK 320KT........................................................................................................................ D
PER-OEI-HLD HOLDING
HOLDING................................................................................................................................................................. A
PER-OEI-DES DESCENT
PER-OEI-DES-10 STANDARD STRATEGY
DESCENT - M.78/300KT.........................................................................................................................................A
PER-OEI-DES-15 OBSTACLE STRATEGY
GROSS FLIGHT PATH DESCENT AT GREEN DOT SPEED - ISA...................................................................... A
GROSS FLIGHT PATH DESCENT AT GREEN DOT SPEED - ISA +20...............................................................B
Continued on the following page
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OEI-PLP-TOC P 1/2
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
PRELIMINARY PAGES - TABLE OF CONTENTS
PER-OEI-DES-20 FIXED SPEED STRATEGIES
Continued from the previous page
DESCENT - M.80/350KT.........................................................................................................................................A
DESCENT - M.78/320KT ....................................................................................................................................... B
PER-OEI-DES-30 DESCENT TO LANDING
DESCENT TO LANDING........................................................................................................................................ A
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OEI-PLP-TOC P 2/2
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
INTRODUCTION
Ident.: PER-OEI-GEN-00002064.0001001 / 10 DEC 09
Applicable to: ALL
This chapter provides the single engine performance data to be used for the conduct and monitoring
of the flight following an engine failure.
The diversion strategy (descent and cruise speed schedules) shall be selected, and specified in the
operator’s routes specifications, as a function of the prevailing operational factors (e.g. obstacles
clearance requirements and/or ETOPS operation).
FLIGHT PREPARATION
Ident.: PER-OEI-GEN-00002065.0001001 / 01 DEC 14
Applicable to: ALL
In readiness for a possible engine failure occurring during the flight, any flight shall be planned so as
to comply with any of the following requirements, as applicable :
• obstacle clearance,
• oxygen,
• maximum diversion distance (ETOPS operation).
The following FCOM sections provide flight preparation and fuel planning information :
• Refer to PER-FPL-GEN-MFR MINIMUM RECOMMENDED FUEL REQUIREMENTS, for Standard
Fuel Planning,
• Refer to PRO-SPO-40-10 General, for Extended Range Operation (ETOPS) and associated fuel
requirements.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-OEI-GEN P 1/2
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
GENERAL
FLIGHT CREW
OPERATING MANUAL
STRATEGY
Ident.: PER-OEI-GEN-00002067.0001001 / 23 NOV 11
Applicable to: ALL
Depending on the prevailing operational constraints, the most appropriate diversion strategy shall be
selected, out of the following options:
STANDARD
STRATEGY
DESCENT
TO CEILING
CRUISE
• M .78/300 kt
• MCT
LR ceiling
LR speed
OBSTACLE
STRATEGY
320 kt
• Green Dot Speed
• MCT
• M .78/320 kt
• MCT
‐ Obstacle not
cleared:
Maintain Green Dot
Speed at MCT
‐ Obstacle cleared :
Revert to standard
strategy
DESCENT
TO LANDING
Approx
increase in fuel
consumption
compared with
both engines
operative
FIXED SPEED STRATEGIES
VMO
• M .80/350 kt
• MCT
FL per Refer to
FL per Refer to
PRO-SPO-40-60
PRO-SPO-40-60
ETOPS Fuel
ETOPS Fuel
Requirement from
Requirement from
Critical Point to
Critical Point to
Landing - One Engine Landing - One Engine
Out - Cruise at 320kt Out - Cruise at 350kt
MCT/320 kt
MCT/350 kt
IDLE/M .78/300 kt/250 kt
+33 %
For ETOPS operations, any of the above diversion strategies can be used provided that the selected
strategy and speed schedule is used in:
‐ establishing the area of operation (maximum diversion distance), Refer to PRO-SPO-40-60
General,
‐ calculating the diversion fuel requirements for the single engine ETOPS critical scenario, Refer to
PRO-SPO-40-30 ETOPS Fuel Scenarios,
‐ demonstrating the applicable obstacle clearance requirements (net flight path and net ceiling).
During the diversion, the flight crew is expected to use the planned speed schedule.
However, based on the evaluation of the actual situation, the pilot in command has the authority to
deviate from this planned one engine inoperative speed.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PER-OEI-GEN P 2/2
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
ALTITUDE - CEILINGS
FLIGHT CREW
OPERATING MANUAL
CEILINGS
Ident.: PER-OEI-ALT-10-00016065.0001001 / 22 MAR 17
Applicable to: ALL
Refer to QRH/PER-L Ceilings (Paper Only) or use the performance application of FlySmart with
Airbus.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-OEI-ALT-10 P 1/2
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
ALTITUDE - CEILINGS
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OEI-ALT-10 P 2/2
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - STANDARD AND OBSTACLE STRATEGIES
LONG RANGE CRUISE - 1 ENGINE OUT - ISA
Ident.: PER-OEI-CRT-10-00002108.0020001 / 10 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-OEI-CRT-10 P 1/4
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - STANDARD AND OBSTACLE STRATEGIES
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-OEI-CRT-10 P 2/4
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - STANDARD AND OBSTACLE STRATEGIES
LONG RANGE CRUISE - 1 ENGINE OUT - ISA +20
Ident.: PER-OEI-CRT-10-00002111.0063001 / 04 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-OEI-CRT-10 P 3/4
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - STANDARD AND OBSTACLE STRATEGIES
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PER-OEI-CRT-10 P 4/4
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
CRUISE TABLES - FIXED SPEED STRATEGIES
FLIGHT CREW
OPERATING MANUAL
CRUISE - MCT/VMO - 1 ENGINE OUT - ISA
Ident.: PER-OEI-CRT-20-00002112.0023001 / 09 DEC 09
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A→
PER-OEI-CRT-20 P 1/8
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - FIXED SPEED STRATEGIES
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←A
PER-OEI-CRT-20 P 2/8
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - FIXED SPEED STRATEGIES
CRUISE - MCT/VMO - 1 ENGINE OUT - ISA +20
Ident.: PER-OEI-CRT-20-00002115.0043001 / 09 DEC 09
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-OEI-CRT-20 P 3/8
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - FIXED SPEED STRATEGIES
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PER-OEI-CRT-20 P 4/8
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
CRUISE TABLES - FIXED SPEED STRATEGIES
FLIGHT CREW
OPERATING MANUAL
CRUISE - MCT/320KT - 1 ENGINE OUT - ISA
Ident.: PER-OEI-CRT-20-00002116.0023001 / 09 DEC 09
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C→
PER-OEI-CRT-20 P 5/8
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - FIXED SPEED STRATEGIES
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←C
PER-OEI-CRT-20 P 6/8
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - FIXED SPEED STRATEGIES
CRUISE - MCT/320KT - 1 ENGINE OUT - ISA +20
Ident.: PER-OEI-CRT-20-00002119.0023001 / 09 DEC 09
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D→
PER-OEI-CRT-20 P 7/8
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
CRUISE TABLES - FIXED SPEED STRATEGIES
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←D
PER-OEI-CRT-20 P 8/8
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IN CRUISE QUICK CHECK - STANDARD STRATEGIES
IN CRUISE QUICK CHECK AT LONG RANGE SPEED
Ident.: PER-OEI-ICQ-10-00002122.0001001 / 22 MAR 17
Applicable to: ALL
In cruise quick check tables (Refer to QRH/PER-L In Cruise Quick Check Long Range (Paper Only)
or use the performance application of FlySmart with Airbus) allow the flight crew to determine the
fuel consumption and the time required to cover a given air distance from any moment in cruise to
landing, with one engine inoperative.
The QRH tables are established for:
‐ Cruise Mach number : long range
‐ Descent profile : M .78/300 kt/250 kt
‐ Approach and landing : 120 kg or 270 lb - 6 min IMC
‐ ISA
‐ CG = 33 %
‐ Pack flow HI
‐ Anti ice OFF
Note:
1. In the tables, the asterisk (*) means that a step climb of 4 000 ft must be flown to reach
the corresponding flight level.
2. The flight level shown on the top of each column is the final flight level.
3. For each degree Celsius above ISA temperature apply a fuel correction of 0.015
(kg/°C/NM) × Δ ISA (°C) × air distance (NM) or 0.033 (lb/°C/NM) × ΔISA (°C) × air
distance (NM).
CORRECTION FOR DEVIATION FROM REFERENCE WEIGHT
Ident.: PER-OEI-ICQ-10-00002123.0001001 / 21 MAR 17
Applicable to: ALL
The in cruise quick check tables are based on a reference initial weight.
A correction on the fuel consumption has to be made, when the actual initial weight is different from
the reference initial weight.
If it is lower (or greater) than the reference weight, subtract (or add) the value given in the correction
part of the table per 1 000 kg or 1 000 lb below (or above) the reference initial weight (Refer to
PER-OEI-DES-20 DESCENT - M.80/350KT).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-OEI-ICQ-10 P 1/2
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IN CRUISE QUICK CHECK - STANDARD STRATEGIES
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OEI-ICQ-10 P 2/2
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IN CRUISE QUICK CHECK - FIXED SPEED STRATEGIES
GENERAL
Ident.: PER-OEI-ICQ-20-00002125.0001001 / 14 NOV 11
Applicable to: ALL
The following in cruise quick check tables allow the flight crew to determine the fuel consumption and
the time required to cover a given air distance from any moment in cruise to landing with one engine
inoperative.
These tables are established for:
‐ Cruise speed: MCT /VMO , MCT/320 kt.
‐ Descent profile: M .78/300 kt/250 kt
‐ Approach and landing: 120 kg or 270 lb - 6 min IMC
‐ ISA
‐ CG = 33 %
‐ Pack flow HI
‐ Anti ice OFF
Note:
1. In the tables, the asterisk "*" means that a step climb of 4 000 ft has been made to reach
the corresponding flight level.
2. The flight level shown on the top of each column is the final flight level.
3. For each degree Celsius above ISA apply a fuel correction of
0.015 (kg/°C/NM) × ΔISA (°C) × Air Distance (NM)
or 0.033 (lb/°C/NM) × ΔISA (°C) × Air Distance (NM)
CORRECTION FOR DEVIATION FROM REFERENCE WEIGHT
Ident.: PER-OEI-ICQ-20-00002126.0001001 / 21 MAR 17
Applicable to: ALL
The in cruise quick check tables are based on a reference initial weight. The fuel consumption must
be corrected when the actual weight is different from the reference initial weight.
If it is lower (or greater) than the reference weight, subtract (or add) the value given in the
correction part of the table per 1 000 kg or 1 000 lb below (or above) the reference weight (Refer to
PER-OEI-DES-20 DESCENT - M.80/350KT).
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A to B
PER-OEI-ICQ-20 P 1/4
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IN CRUISE QUICK CHECK - FIXED SPEED STRATEGIES
IN CRUISE QUICK CHECK VMO
Ident.: PER-OEI-ICQ-20-00002127.0022001 / 10 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
C
PER-OEI-ICQ-20 P 2/4
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IN CRUISE QUICK CHECK - FIXED SPEED STRATEGIES
IN CRUISE QUICK CHECK 320KT
Ident.: PER-OEI-ICQ-20-00002128.0022001 / 10 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
D
PER-OEI-ICQ-20 P 3/4
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
IN CRUISE QUICK CHECK - FIXED SPEED STRATEGIES
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OEI-ICQ-20 P 4/4
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
HOLDING
FLIGHT CREW
OPERATING MANUAL
HOLDING
Ident.: PER-OEI-HLD-00002130.0024001 / 28 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-OEI-HLD P 1/2
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
HOLDING
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OEI-HLD P 2/2
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
DESCENT - STANDARD STRATEGY
FLIGHT CREW
OPERATING MANUAL
DESCENT - M.78/300KT
Ident.: PER-OEI-DES-10-00002135.0020001 / 09 MAR 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-OEI-DES-10 P 1/2
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
DESCENT - STANDARD STRATEGY
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OEI-DES-10 P 2/2
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCENT - OBSTACLE STRATEGY
GROSS FLIGHT PATH DESCENT AT GREEN DOT SPEED - ISA
Ident.: PER-OEI-DES-15-00002080.0022001 / 09 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-OEI-DES-15 P 1/4
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCENT - OBSTACLE STRATEGY
GROSS FLIGHT PATH DESCENT AT GREEN DOT SPEED - ISA +20
Ident.: PER-OEI-DES-15-00002088.0022001 / 22 MAR 17
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B→
PER-OEI-DES-15 P 2/4
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
FLIGHT CREW
OPERATING MANUAL
DESCENT - OBSTACLE STRATEGY
‐ For LONG RANGE CRUISE table Refer to PER-OEI-CRT-10 LONG RANGE CRUISE - 1 ENGINE
OUT - ISA
‐ For IN CRUISE QUICK CHECK Refer to QRH/PER-L In Cruise Quick Check Long Range (Paper
Only) or use the performance application of FlySmart with Airbus.
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
←B
PER-OEI-DES-15 P 3/4
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
DESCENT - OBSTACLE STRATEGY
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OEI-DES-15 P 4/4
22 MAR 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
DESCENT - FIXED SPEED STRATEGIES
FLIGHT CREW
OPERATING MANUAL
DESCENT - M.80/350KT
Ident.: PER-OEI-DES-20-00002136.0023001 / 22 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-OEI-DES-20 P 1/2
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
DESCENT - FIXED SPEED STRATEGIES
FLIGHT CREW
OPERATING MANUAL
DESCENT - M.78/320KT
Ident.: PER-OEI-DES-20-00002137.0023001 / 02 FEB 11
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
B
PER-OEI-DES-20 P 2/2
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
DESCENT - DESCENT TO LANDING
FLIGHT CREW
OPERATING MANUAL
DESCENT TO LANDING
Ident.: PER-OEI-DES-30-00002138.0022001 / 09 DEC 09
Applicable to: ALL
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
A
PER-OEI-DES-30 P 1/2
24 JAN 17
PERFORMANCE
ONE ENGINE INOPERATIVE
A318/A319/A320/A321
DESCENT - DESCENT TO LANDING
FLIGHT CREW
OPERATING MANUAL
Intentionally left blank
GLG A318/A319/A320/A321 For A/C: HC-CRU
FCOM
PER-OEI-DES-30 P 2/2
24 JAN 17
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