Thales Avionics TFS-SDU82155A Topflight SATCOM Satellite data unit User Manual Satellite Data Unit SDU

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TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
Installation and
Maintenance Manual
TopFlight Satcom
SDU – 82155A Series
SCM – 82158A Series
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
Page intentionally left blank
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
RECORD OF REVISIONS
REV.
NO.
REVISION
DATE
October 2007
DATE
INSERTED
BY
REV.
NO.
REVISION
DATE
DATE
INSTERTED
BY
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
CONTENTS
1.
2.
3.
INTRODUCTION....................................................................................6
1.1.
Purpose of Manual............................................................................6
1.2.
Scope.................................................................................................7
1.3.
References ........................................................................................7
1.4.
Compliance to Regulations .............................................................7
1.5.
List of Abbreviations ........................................................................8
DESCRIPTION .....................................................................................10
2.1.
TFS Satellite Communication System Domain ...........................10
2.2.
TFS System Overview ....................................................................10
2.3.
SDU General Description ...............................................................11
2.4.
Interfaces.........................................................................................20
2.5.
Configuration Straps ......................................................................21
2.6.
SDU Interconnections ....................................................................22
2.7.
SCM General Description...............................................................30
INSTALLATION GUIDELINES ..........................................................36
3.1.
Introduction.....................................................................................36
3.2.
Interchangeability ...........................................................................36
3.3.
SDU / SCM Location and Accessibility Guidelines......................36
3.4.
Mounting Tray.................................................................................37
3.5.
Cooling ............................................................................................37
3.6.
Power Requirements ......................................................................37
3.7.
SDU RF Connections......................................................................38
3.8.
Bonding Requirements ..................................................................39
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
3.9.
4.
5.
6.
7.
Issue 2
Ref: TFS062/J-03/003
SDU Fitting Instructions.................................................................39
3.10.
SDU Removal Instructions .........................................................40
3.11.
SCM Fitting Instructions.............................................................40
3.12.
SCM Removal Instructions.........................................................41
INSPECTION AND SYSTEM CHECKOUT ......................................42
4.1.
Inspection/Check procedure .........................................................42
4.2.
System Checkout............................................................................42
MAINTENANCE...................................................................................44
5.1.
Introduction.....................................................................................44
5.2.
Cleaning of Mechanical Parts........................................................44
5.3.
Periodic Checks..............................................................................44
5.4.
Cabling and Connections ..............................................................44
TESTING AND FAULT ISOLATION .................................................45
6.1.
BITE Function .................................................................................45
6.2.
Test Functions ................................................................................46
6.3.
Fault Isolation .................................................................................48
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ......................54
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
1.
INTRODUCTION
1.1.
Purpose of Manual
Issue 2
Ref: TFS062/J-03/003
This manual sets forth installation and maintenance guidelines for the THALES
TopFlight Satcom (TFS) Satellite Data Unit (SDU), and SDU Configuration Module
(SCM). The SDU and SCM installation specific and general guidelines contained
within this manual are supported by mechanical and electrical interconnection
drawings. Drawings should be reviewed by the installation organisation, and any
requirements specific to a particular airframe should be assessed before installation is
commenced.
The Manual covers the following topics:
Title Page
Record of Revisions
Table of Content
Introduction
Description
Installation Guidelines
Inspection and System Checkout
Maintenance
Testing and Fault Isolation
Instructions for Continued Airworthiness
NOTE: This manual does not cover aircraft system commissioning test procedures.
Advisory notes presented within this manual such as: ‘Warnings, Cautions and Notes’
are applicable to the TFS system as follows:
A WARNING is used to alert the reader to possible hazard which may
cause loss of life or physical injury
A CAUTION is used to denote the possibility of damage to materiel but not
danger to personnel
A NOTE is used to convey, or draw attention to, information that is
extraneous to the immediate subject of the text
For any queries related to information contained within this Manual contact the
following THALES TFS Project Manager:
86 Bushey Road
Raynes Park, London
SW20 0JW, UK
Tel. +44 (0)20 8946 8011
Fax. +44 (0)20 8946 7530
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
1.2.
Issue 2
Ref: TFS062/J-03/003
Scope
The Thales SDU and SCM comply with the design requirements set forward in the
ARINC 781 Characteristic. An ARINC 781 compliant system is intended to support
one or more of the Inmarsat aeronautical services known as ‘Classic-Aero’, ‘Swift 64’,
and ‘SwiftBroadband.
This manual provides information specific for the SDU and SCM capable of providing
SwiftBroadband (SBB) services for Single Aisle (SA) aircraft configuration. The SDU
and SCM covered in this manual support the single channel Inmarsat Class 3A and
Class 7 services only.
1.3.
References
1.2.1.
THALES SCM Component Maintenance Manual 44-35-33.
1.2.2.
THALES SDU Component Maintenance Manual 44-35-32.
1.2.3.
EMS AMT-3500 Intermediate Gain Antenna Subsystem Installation Manual
MN-1242-20047.
1.2.4.
ARINC 429: Mark 33 Digital Information Transfer System.
1.2.5.
ARINC 600 Characteristic: Air Transport Avionics Equipment Interfaces.
1.2.6.
ARINC 615 Characteristic: Airborne Computer High speed Data Loader.
1.2.7.
ARINC 615A Characteristic: Ethernet Based Data loading.
1.2.8.
ARINC 781 Characteristic: Mark III Aviation Satellite Communication
(Satcom) System Avionics.
1.2.9.
Transmitter Certification of FCC ID: KV6-TFS-SDU82155A Series TFS SDU
to Federal Communications Commission rule part 87 and Confidentiality:
A111/STE-012/006.
1.2.10. RTCA DO-160E/EUROCAE ED-14E: Environmental Conditions and Test
Procedures for Airborne Equipment.
1.4.
Compliance to Regulations
1.4.1. FCC:
The SDU is designed to be compliant with part 15 and part 87 of the
Federal Communication Commission (FCC) regulations.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
1.4.2. The installation must be compliant to:
EASA/FAR 25.869 Fire protection: systems
EASA 25X0899 Electrical bonding and protection against lightning and
static electricity
EASA/FAR 25.1301 Equipment, general, function and installation
EASA/FAR 25.1309 Equipment, systems and installations
EASA 25X1316 System lightning protection
EASA/FAR 25.1353 Electrical equipment and installations
EASA/FAR 25.1357 Circuit protective devices
EASA 25X1360 Precautions against injury
EASA/FAR 25.1431 Electronic equipment
EASA 25.561 Emergency Landing
1.5.
List of Abbreviations
ac
ACARS
ADL
AES
AGS
AIM
AMO
AOR-E
AOR-W
APM
ARINC
ATE
BGAN
BITE
BSU
CCM
CDU
CMM
CPM
dc
DLNA
EASA
ECM
ECS
EMC
ESD
ESDS
FPL
GES
GNSS
GPS
HPA
IGA
IMEI
IMM
IMSI
Alternating Current
Aircraft Communication Addressing and Reporting System
Airborne Data Loader
Aeronautical Earth Station
Airborne GSM Server
Antenna Interface Mounting
Approved Maintenance Organization
Atlantic Ocean Region-East
Atlantic Ocean Region-West
Avionics Processor Module
Aeronautical Radio Inc.
Automatic Test Equipment
Broadband Global Area Network
Built In Test Equipment
Beam Steering Unit
Channel Card Module
Control Display Unit
Component Maintenance Manual
Communication Processor Module
Direct Current
Diplexer and Low Noise Amplifier
European Aviation Safety Agency
External Configuration Memory
Environmental Control System
Electromagnetic Compatibility
Electro Static Discharge
Electro Static Discharge Sensitive
Front Panel LED
Ground Earth Station
Global Navigation Satellite System
Global Positioning System
High Power Amplifier
Intermediate Gain Antenna
International Mobile Equipment Identity
Installation and Maintenance Manual
International Mobile Subscriber Identity
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
INMARSAT
IOR
IP
IPC
IRS
I/O
ISDN
LED
LES
LRU
mA
MCDU
MCU
MEL
MES
MIB
NVM
OMS
ORT
OCXO
PAST
PC
PLMN
P/N
POR
POST
PPPoE
PSM
PSTN
RF
SA
SATCOM
SBB
SCDU
SCM
SDU
SIM
SIS
SNMP
SRU
STC
SW
TCP/IP
TFS
UMTS
USIM
Wi Fi
WLAN
WOW
Issue 2
Ref: TFS062/J-03/003
International Maritime Satellite Organization
Indian Ocean Region
Internet Protocol
Illustrated Parts List
Inertial Reference System
Input/Output
Integrated Service Digital Network
Light Emitting Diode
Land Earth Station
Line Replaceable Unit
MilliAmpere
Multi-function Control and Display Unit
Modular Concept Unit
Minimum Equipment Level
Mobile Earth Station
Management Information Base
Non Volatile Memory
Onboard Monitoring System
Owner Requirements Table
Oven Controlled Crystal Oscillator
Person Activated Self Test
Personal Computer
Public Land Mobile Network
Part Number
Pacific Ocean Region
Power On Self-Test
Point To Point Protocol over Ethernet
Power Supply Module
Public Switched Telephone Network
Radio Frequency
Single Aisle
Satellite Communication
SwiftBroadband
Satellite Control Display Unit
SDU Configuration Module
Satellite Data Unit
Subscriber Identity Module
Standalone Interface System
Simple Network Management Protocol
Shop Replaceable Unit
Supplemental Type Certificate
Software
Transmission Control Protocol/Internet Protocol
TopFlight Satcom
Universal Mobile Telecommunication System
Universal Subscriber Identity Module
Wireless Fidelity
Wireless Local Area Network
Weight On Wheels
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
2.
DESCRIPTION
2.1.
TFS Satellite Communication System Domain
Issue 2
Ref: TFS062/J-03/003
SATCOM (Satellite Communications) systems provide users with long-range voice
and data communication by accessing global satellite and ground communications
networks. The introduction of Pico-Cells on aircrafts, and the new I4 INMARSAT
constellation of geostationary satellites have been the enabling technologies for the
development of significantly smaller, more capable terminals such as the Thales
TopFlight Satcom system.
SwiftBroadband is the aeronautical service, which operates on the INMARSAT BGAN
(Broadband Global Area Network) infrastructure. SwifBroadband supports Circuit
Switched and always-on TCP/IP data (packet switched) services. Thales SBB
TopFlight Satcom system supports the Inmarsat Classes of service 3A and 7.
Figure 2-1 below depicts the TFS communication system.
Inmarsat domain
User Terminals
I4 Satellite
Backbone Networks
IP, PLMN, PSTN
Satellite
Access
Station
TFS System
Aeronautical Segment
Space Segment
Ground Segment
Figure 2-1: Example of TFS communications system overview.
2.2.
TFS System Overview
The TFS system conforms to the ARINC-781 Characteristic, and interfaces with
onboard avionics and communication equipment to provide the aircraft with a range of
communication services by transmitting and receiving L Band signals to and from the
fourth generation of INMARSAT satellites. For this purpose the INMARSAT satellite
constellation is connected to the ground backbone telecommunication network
through Satellite Access Stations (SAS) operated by service providers.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
10
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
The TFS system consists of the following LRUs (Line Replaceable Unit):
One SDU (Satellite Data Unit)
One SCM (SDU Configuration Module)
One DLNA (Diplexer Low Noise Amplifier)
One IGA (Intermediate Gain Antenna)
Figure 2-2 below depicts TFS system interfacing for the Single Aisle configuration.
IGA
Figure 2-2: Example of Single Aisle TFS system interfacing.
2.3.
SDU General Description
2.3.1. Hardware
The SDU hardware meets RTCA/DO-254 level D requirements, and it is composed
(see Fig 2-3) of the following internal sub-assemblies:
High Power Amplifier (HPA)
Channel Card Module (CCM) x 1
Communication Processor Module (CPM)
Power Supply Module (PSM)
Oven Controlled Crystal Oscillator (OCXO)
Avionics Processor Module (APM)
Backplane
Front Panel
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
11
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
The SDU enclosure is constructed of machined lightweight aluminium alloy and it is
packaged in an ARINC 600 6 MCU (Modular Concept Unit) housing suitable for
mounting in the equipment bay of an aircraft.
Two hold-down clamps are used to secure the SDU, permitting it to be firmly held in
position in the mounting rack. A handle fitted on the front panel of the SDU permits
removal, installation and carrying of the SDU.
Figure 2-3: Example of SDU sub-system modules exploded.
2.3.2. Software
The software in the SDU can be considered as being supplied in two elements, one
contained within the CCM the other operating on the SDU processors (CPM & APM).
The SDU’s application software primarily functions as the system controller providing
system level tasks such as CCM control, BITE reporting, Avionics interfacing via
ARINC-429 (including IRS (Inertial Reference System)) and providing external
interfaces (such as Ethernet) as well as routing functions between the external
interfaces and the CCM as necessary.
The SDU’s APM and CPM application software meets RTCA/DO-178B level D
requirements, and the CCM application software meets RTCA/DO-178 level E
requirements.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
12
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
2.3.3. ORT Parameters
The SCM ORT (Owner Requirement Table) is also stored inside the SDU. The ORT
database contains configuration data that is used to customize the operation of the
TFS system. It allows various preferences to be set to enable the efficient use of the
equipment in normal operation. The SDU is delivered to customers with a default
ORT.
2.3.4. General Operation
The SDU controls and processes all essential data in order to manage the reception
and transmission of data through the satellite link. The SDU controls the set-up of the
required channel types, providing modulation/demodulation, error correction, coding,
and data rates associated with the satellite communication channel(s).
The SDU is of modular design and can be configured for use on a wide variety of
aircraft. It meets requirements for cabin only, cockpit only and cabin and cockpit
services. This manual however covers the SA cabin only configuration.
The SDU converts digital/audio inputs to Radio Frequency (RF), and contains a High
Power Amplifier (HPA) function providing the necessary output power to support
communication between the aircraft and the satellite. It also controls the associated
antenna sub-system and uses the SCM for its own configuration data purposes.
The SDU operates within set frequency bandwidths:
RX range is between 1525 to 1559 MHz
TX is tuned over the range 1626.5 to 1660.5 MHz
TX operational range is between 1631.5 to 1660.5 MHz
2.3.5. Sub-modules Basic Detailed Operation
The Front Panel assembly gives visual indications for system status,
external maintenance interface connections and the SDU Person Activated
Self Test (PAST) push button
The Backplane assembly makes interconnections between external
interfaces and the SDU internal sub-assemblies
The APM provides interfacing to external avionics. It receives aircraft
position, speed and heading information from external avionics via ARINC
429 (Aeronautical Radio Incorporated), and updates the CCM with position
information every second. The APM manages satellite selection based on
aircraft position, and maintains antenna pointing to the wanted satellite
beam steering via ARINC 429. The APM manages RF (Radio Frequency)
resources and set CCM transmit power levels, taking into consideration
antenna gain and cable losses stored within the ORT
The CPM handles and controls all communications interfaces (Ethernet,
RS232 and RS422)
The CCM converts user’s input/output data to signals suitable for
transmitting and receiving L-Band signals using the satellite link
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
13
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
The High Power Amplifier (HPA) module amplifies the low level RF
signals from the CCM to produce high power output prior to connection to
the antenna
The PSM operates from 115 Vac and supplies low level dc power supplies
to SRUs within the SDU and 12 Vdc to the SCM
The OCXO provides 10 MHz clock reference signal for the CCM circuit
2.3.6. Operating Environment
Operating temperature: between -15o C (5o F) and +55o C (131o F)
Cooling: Forced air type in accordance with ARINC 600, requiring airflow
rate of 50 kg/hr, blowing from top to bottom. Maximum inlet temperature
+40o C
Heat dissipation: 220 W (assuming 100% duty cycles with HPA operating
at 30 W output
2.3.7. Environmental Conditions
The SDU complies with the RTCA/DO-160-E (ED-14E). The environmental
qualifications categories complied with, are as per listed in Figure 2-4.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
14
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
RTCA DO-160E (ED-14E) Environmental Categories
Temperature/Altitude
A2
Loss of Cooling
Temp Var.
Humidity
Shock/Crash
Vibration
Vibration Curve
BC
Explosion
Waterproof
Fluids
10
Sand/Dust
11
Fungus
12
Salt Fog
13
Magnetic Effect
Power Input
A(WF)
Harmonics
15
Voltage Spike
16
Conducted Audio
17
Induced
ZW
18
RF Susceptibility
TR
19
RF Emissions
20
Lightning Induced
21
Lightning Direct
22
Icing
23
ESD
24
Fire
14
R(WF)
A3G33
Figure 2-4: Environmental test categories for SDU & SCM.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
15
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
2.3.8. Identification Label
Figure 2-5 represent the SDU Front Panel Identification Label for detailed description
of the numbered field refer to the legend in Figure 2-6.
12
HW PNR
Minor Rev.
SW PNR
HW PNR 82155X30
SATELLITE DATA UNIT (SDU)
MFR
MFR K0385
SER
SER NO
DMF
DMF
Supply 115VAC
SW PNR
CSD
cm
Wt. 9.5kg (max)
SDU
FAA TC
TEST
FCC id
SCM
HW DO-254 Level C
SW DO-178B Level D
Antenna
AMDT
DO-160E Env. Cat
G H
[(A2)Z]BAE[SC]EXXXFXA[
17
DLNA
INSPECT
A(WF)]A[R(WF)][ZW][RR
TEST PORT
]M[A3G33]XXAC
Ext. HPA
11
Ext. BSU
Ext. Data Bus
CAUTION
ORT/Config.
Sat. Link #1
15
THIS EQUIPMENT
REQUIRES FIELD
LOADABLE SOFTWARE
ENSURE CORRECT
SOFTWARE IS LOADED
REFER TO AMM
10
Sat. Link #2
LED INDICATIONS MAY RELATE TO
OTHER EQUIPMENT OR AIRCRAFT WIRING
CAUTION
CAUTION
HOT
16
SURFACE
14
13
11
Figure 2-5: Example of SDU Front Panel.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
16
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
SDU Front Panel legend
Manufacturer’s Name
Hardware Part Number
Hardware Minor Revision
Software Part Number
Manufacturer’s Code
Equipment Serial Number
Date of Final Factory Inspection (month and year)
Amendment Label
Inspection Stamp
10
Standalone Identification System
11
Field Loadable Software Warning
12
Voltage Supply, Compass Safe Distance, Weight of Equipment, FCC
(Federal Communication Commission) ID, Hardware and Software
Compliance references
13
Carrying Handle
14
Hold Down Lugs
15
Ethernet RJ45 Maintenance Connector
16
Status Light Emitting Diodes (LEDs)
17
Push To Test Switch
Figure 2-6: SDU Front Panel legend.
2.3.9. Weight and Dimensions
For overall dimensions refer to Figure 2-7
Form Factor: ARINC 600, 6 MCU
Mass: 9.5 kg (21 lb) maximum
2.3.10. SDU Electrical Characteristics
Supply voltage: 100 to 122 Vrms, ac, Frequency Range 360 to 800 Hz
Power consumption: 255 W maximum
RF Power Rating: variable up to 30W for continuous operation
Max Power Rating, Watts: 120W peak RF power 4 channels @ 7.5W each
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
17
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
Figure 2-7: SDU Overall Dimensions. NOTE: all measurements given are in mm.
© THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval.
18
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
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Page intentionally left blank
© THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval.
19
Issue 2
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
2.4.
Ref: TFS062/J-03/003
Interfaces
The SDU interfaces with various aircraft systems.
2.4.1. Aircraft Power Utility Service
The TFS interfaces with the aircraft primary power generator as per depicted in
Figure 2-8 below.
18
19
Aircraft Power
Supply
115 Vac Cold
BP01
115 Vac Hot
BP05
BP03
115 Vac Cold
DLNA
IGA
115 Vac Hot
Chassis Ground
MP01D
115V AC - 5 AMP Type A Circuit Breaker, as
per ARINC 781 recommendation.
22
Power Source 12 VDC
SCM Power Return
SCM
MP02D
SDU
Figure 2-8: TFS example of aircraft power distribution diagram.
2.4.2. Avionics interfaces
The following avionics interfaces are supported:
Specific to type Cabin Network domain
ADL (Aircraft Data Loader), PDL (Portable Data Loader)
IRS, GPS (Global Positioning System)
In order to comply with transmit burst time, INMARSAT requires the SDU to be
provided with the aircraft present position within 1500m in three dimensions,
referenced to WGS-84 (GPS). In order to comply with this requirement the TFS SDU
requires ARINC 429 Nav Data labels as referenced in Figure 2-9. The values apply
to aircraft configurations where only on Nav Data bus is connected.
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Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
20
Issue 2
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
PARAMETER
Ref: TFS062/J-03/003
ARINC 429 LABEL
Latitude GNSS – Hybrid
254
Longitude GNSS – Hybrid
255
Ground Speed GNSS – Hybrid
175
Track Angle True GNSS – Hybrid
137
True Heading – Hybrid
132
Pitch Angle
324
Roll Angle
325
GNSS Height (HAE) or Hybrid Altitude MSL
370 or 261
GNSS UTC (Binary)
150
GNSS Date
260
GNSS Sensor Status
273
GNSS HDOP
101
Figure 2-9: ARINC 429 Nav Data Labels – Hybrid.
2.4.3. Maintenance Interfaces
The SDU supports the following maintenance interfaces:
Aircraft Data Loader (ADL), ARINC 615/615A
Portable Data Loader (PDL), ARINC 615A
Thales Maintenance Terminal
NOTE: For more information concerning data loading tools contact the Thales TFS
product support representative at the following address:
86 Bushey Road
Raynes Park, London
SW20 0JW, UK
Tel. +44 (0)20 8946 8011 (Switchboard)
Tel. +44 (0)20 8946 5169 (Hot desk).
2.5.
Configuration Straps
In the case of using the mandatory configuration straps the SDU is configurable via
the SDU ARINC 600 configuration straps as defined in ARINC 781.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
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The straps input values will be read only at unit power-up to determine the system
configuration. The SDU configuration will be selectable by multiplexing the
Configuration Straps inputs with the service availability discrete outputs as per
ARINC 781 Attachment 1-4 Note 17.
2.5.1. Mandatory Configuration Pins
Pins TP (Top plug) 3D and TP3E must be used on all aircraft installations as they
may be used as hardware implemented safety override to force the internal HPA
function into low power mode when connected to an external HPA.
Pin TP3G must be used on all aircraft installations since one of its functions is to
indicate whether all other configuration pins (excluding TP3D, TP3E, TP3F, TP3G,
and TP4D) should be used by the SDU. Pin TP4D should be used on all aircraft
installations since it indicates the SDU number (1 or 2).
Pin TP3F must be used on all aircraft installations since it indicates that the number
of all configuration pins (excluding TP3D) including the parity pin itself connected to
service availability discrete (or TP3D) is odd.
2.6.
SDU Interconnections
2.6.1. ARINC 600 Standard Interwiring Connector
The SDU ARINC 600 connector provides:
Input/Output connections
DO160E EMC filtering to input and output interfaces
ESD (Electrostatic Discharge) protection for ATE connections
The SDU is provided with a low insertion force, size 2-shell receptacle in accordance
with ARINC 600 Attachment 19. This connector accommodates coaxial and signal
interconnections in the top plug (TP) insert, Quadrax and signal interconnections in
the middle plug (MP) insert, and coaxial, fibre and power interconnections in the
bottom plug (BP) insert. The contact arrangements are as follows:
Insert arrangement 08 receptacle in accordance with ARINC Specification
600, Attachment 11 for the top insert (Size 1 Coax cavity and Size 22
Signal sockets)
Insert arrangement 120Q2 receptacle in accordance with ARINC
Specification 600, Attachment 20, Figure 20-6.5.5 for the middle insert
(Size 8 Quadrax cavities for pin components and Size 22 Signal sockets)
Insert arrangement 12F5C2 receptacle in accordance with ARINC
Specification 600, Attachment 19, and Figure 19-49.19 for the bottom
insert (Size 12 Electrical pins, Size 16 Electrical pin, Size 5 Coax cavities,
and Size 16 Optical cavities).
Index pin code 081 in accordance with ARINC Specification 600,
Attachment 18 should be used on both the SDU and the aircraft rack
connectors
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
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2.6.1.1. ARINC 600 Pin Assignment
The layout of the rear panel ARINC 600 connector and the Pin assignment are
shown in the figures 2-10, 2-11, 2-12, and 2-13. For further Information regarding the
ARINC 600 connector refer to Figure 2-15.
Top Plug
Middle Plug
Index code 81 (5,2,2)
Note: The index code pins dark
colour represents the post.
Bottom Plug
Figure 2-10: ARINC 600 Connector Layout.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
23
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RF TX
To HPA or DLNA
ATE
Pin 1
ATE
Pin 2
ATE
Pin 3
ATE
Pin 4
ATE
Pin 5
ATE
Pin 6
ATE
Pin 7
ATE
Pin 8
ATE
Pin 9
ATE
Pin 10
ATE
Pin 11
ATE
Pin 12
ATE
Pin 13
ATE
Pin 14
ATE
Pin 15
ATE
Pin 16
ATE
Pin 17
ATE
Pin 18
ATE
Pin 19
ATE
Pin 20
Ethernet 1
TX
Ethernet 1
RX
Empty
Cavity
Config
Pin 1
Config
Pin 2
Config
Pin 3
Config
Pin 4
SPARE
ISDN 1
TX
ISDN 1
RX
Ethernet 1
RX
Ethernet 1
TX
Empty
Cavity
Config
Pin 5
Config
Pin 6
Config
Pin 7
Config
Pin 8
SPARE
ISDN 1
RX
ISDN 1
TX
Empty
Cavity
Empty
Cavity
Empty
Cavity
Config
Pin 9
Config
Pin 10
Config
Pin 11
Config
Pin 12
(Spare)
SPARE
SPARE
SPARE
Ethernet 2
TX
MCDU 3
Ethernet 2
RX
Ethernet 2
RX
MCDU 3
Ethernet 2
TX
Empty
Cavity
Config
Pin 13
(Spare)
Config
Pin 14
(Spare)
Config
Pin 15
(Spare)
Config
Pin 16
(Spare)
SPARE
ISDN 2
TX
ISDN 2
RX
Empty
Cavity
Config
Pin 17
(Spare)
Config
Pin 18
(Spare)
Config
Pin 19
(Spare)
Config
Pin 20
(Spare)
SPARE
ISDN 2
RX
ISDN 2
TX
Figure 2-11: ARINC 600 Connect Arrangement For Top Plug (TP) Insert
Figure 2-12: ARINC 600 Connections Arrangement For Bottom Plug (BP) Insert.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
24
TopFlight Satcom SDU & SCM
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Figure 2-13: ARINC 600 Connect Arrangement For Middle Plug (MP) Insert.
2.6.2. Electric Interconnection Diagram
The SDU interconnection diagram is given in Figure 2-14. It illustrates all the
necessary connection between the SDU and all the other interfaced equipment.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
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TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
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Aircraft
Power
Supply
115V AC - 5 AMP
Type A Circuit
Breaker, as per
ARINC 781
recommendation.
115 Vac Cold
115 Vac Hot
D/LNA
18
22
(Note 5)
BP01
D/LNA BITE
D/LNA BITE Return
RX Port
115 Vac Cold
BP05
SDU RF Input from D/LNA
115 Vac Hot
BP03
SDU RF Output to D/LNA
Chassis Ground
BP07
TP71
(Note 2)
TX Port
D/LNA Control
Antenna Port
BITE Input Top/Port BSU/Ant (A)
BITE Input Top/Port BSU/Ant (B)
10
11
Antenna
(Note 2)
(Note 4)
MP08C
MP08D
MP02A
Navigation Data
Primary Nav Data (A)
MP02B
Primary Nav Data (B)
MP01J
Navigation Data
(Note 14)
MP01E
Multi-Control Output (A)
MP01F
Multi-Control Output (B)
Secondary Nav Data (A)
MP01K
Secondary Nav Data (B)
SCM Power Source
MP01D
SCM Power Return
MP02D
15
TP3D
External HPA
not fitted
See Note 13
for Signal
Details
External
Reset
Config Pin 1
TP3E
Data to SCM (A) MP03D
Data to SCM (B) MP04D
SCM
Config Pin 2
(Note 3)
Data from SCM (A)
MP1G
SPARE
Data from SCM (B)
MP05D
MP06D
See Note 1
for Signal
Details
System
Failed
Indication
TX Mute
MP8F
TP01C
(Note 11)
Service Availability Discrete 2
TX Mute Input
TP01A
RX +
RX -
ARINC 615A
Data Loader
Connector
TX +
TX -
MP11F
Rear Ethernet TX (A)
Rear Ethernet TX (B)
Ethernet 3 TX (A) Q1 1T-1
Ethernet 3 TX (B) Q1 1T-3
RX +
RX (Note 6)
TP01B
TP01D
Rear Ethernet RX (A)
Ethernet 3 RX (A) Q1
Rear Ethernet RX (B)
Ethernet 3 RX (B) Q1
1T-2
TX +
TX -
1T-4
Client
Ethernet Port
Connector
SDU
(Note 12)
Front Panel RJ-45
(Notes 1,7,10)
RX+
RX1
TX+
TX-
TX+
TX(Note 8)
RX+
Maintenance
Terminal
Connector
RX-
NOTE: See Figure 2 -15 for list of Explanatory Notes
Figure 2-14: TFS System Interconnection Block Diagram – Single Aisle Configuration.
© THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval.
26
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Notes
ARINC 600
SDU Connector
defined in ARINC 781 - see Note 1
Note 1: System interconnections are as per ARINC781 - refer to ARINC 781 for clarification / further detail.
Size 1 Coax Plug. Radiall
P/N: 620 001 (male center contact)
71
Note 6: Uses “Star-Quad” cable as defined in ARINC 664 Part 2. Cross-over to be provided in cable.
Note 7: Pins not required are not listed and should be left ‘Not-Connected’.
Note 8: Cross-over to be provided in cable, when using standard RJ-45 Ethernet connections.
Note 9: Radiall P/No: 620-600-700 does not include all necessary contacts; 1 x Size 5 Crimp Socket Coaxial Contact must also be ordered: Radiall P/No: 620-021.
Note 10: Pigtails for wiring shields/screens are to be made as short as possible to reduce susceptibility to interference.
Note 11: Uses “Shielded, Twisted Pair” cable as defined in ARINC 664 Part 2.
Note 12: The Maintenance Terminal interface will only be connected during maintenance activities.
Note 13: For the External Reset discrete input signal, ground state defined as input voltage less than 3.5V and resistance to airframe dc ground less than 20 mohms. Open
state defined as input voltage higher than 14V and resistance to airframe dc ground higher than 100000 ohms.
Note 14: A second Nav Data bus might be required for some aircraft installations.
Note 2
RF Cable Losses
IGA/HGA Power and Control Connector
Note 4
SDU to D/LNA
RF Loss
Loss ≤ 1.4 dB
D/LNA to Antenna
Loss ≤ 0.3 dB
D/LNA to SDU
6 dB ≤ Loss ≤ 25 dB
Quadrax Insert 1T
Quadrax Insert 2T
14
13
The IGA mount RF connector (J2), the DLNA mount Antenna connector (J1)
and the DLNA mount RX (SDU input) connector (J2) are all TNC Jack (female)
type connectors.
15
12
The DLNA mount TX (SDU output) connector (J3) is a N-Type Jack (female)
type connector.
21
16
11
20
22
17
10
Index code
81 (5,2,2)
11
10
12
Size 5 Coax Plug. Radiall P/N:
620 121 (female center contact)
See Note 9.
19
18
Note 3
PIN No
Pin
10
11
12
13
14
15
SCM Connector
Signal
Data to SDU A (RS422)
Data to SDU B (RS422)
Data from SDU A (RS422
Data from SDU B (RS422)
Reserved – RS232 GND
Spare
Chassis Ground
Power Input +8 to +15V
Reserved - Enable RS232
Reserved – 0V strap output 1
Spare
Reserved – RS232 Tx
Reserved – RS232 Rx
Spare
Power Return 0V
Description
Data to SDU A
Data to SDU B
Data from SDU A
Data from SDU B
Connection Not required
Connection Not required
Chassis Ground
SCM Power Input
Connection Not required
Connection Not required
Connection Not required
Connection Not required
Connection Not required
Connection Not required
SCM Power Return
The IGA/HGA Connector is a receptacle 13-35 insert of the MIL-C-38999 Series III
family: D38999/24FC35PN which mates
with D38999/26FC35S on the cable
The D/LNA Connector is MS3470L1210P which
mates with MS3476L1210S on the cable
View above is looking at the SDU mount connector, Radiall Part Number: 620-600-703.
Tray-mount mating half is supplied with all necessary inserts, except 1 x Size 5 Socket Coax
insert (male centre contact) (Radiall P/No: 620-021), which should be ordered separately. See
Radiall specification for 620-600-700 for further details on supplied inserts.
Serial SCRN
13
RS422 RXD A
14
RS422 RXD B
15
RS422 TXD A
16
RS422 TXD B
ATE Pin
115 Vac Hot
115 Vac Return
--Chassis Ground
17
18
19
20
21
22
DESCRIPTION
Connection Not Required
Connection Not Required
ARINC 429 from antenna
Screen for ARINC 429
ARINC 429 from antenna
ARINC 429 to antenna
Screen for ARINC429
ARINC 429 to antenna
BITE from D/LNA
Screen/RTN for D/LNA
D/LNA on/off control from antenna
Connection Not Required
Connection Not Required
Connection Not Required
Connection Not Required
Connection Not Required
Connection Not Required
Aircraft ac power
Aircraft ac power
Connection Not Required
Connection Not Required
Chassis Ground
D/LNA Power and Control Connector
Note 5
The SCM connector is a DB15 male connector, mating with a DB-15 female
connector on the cable, in accordance with MIL-DTL-24308 (15 pins - gauge 20).
ARINC 600 - Shell Size #2 Connector
10
11
12
SIGNAL
+28 Vdc
28 Vdc RTN
Antenna BITE A
Antenna BITE SCRN
Antenna BITE B
Antenna Control A
Antenna Control
SCRN
Antenna Control B
D/LNA BITE
D/LNA SCRN
D/LNA CTL
Pin
Pin A
Pin B
Pin C
Pin D
Pin E
Pin F
Pin G
Pin H
Pin J
Pin K
Signal
Chassis Ground
LNA Control
Future Spare
Future Spare
115 Vac Cold
115 Vac Hot
+28V DC Hot
LNA BITE
LNA BITE Return
+28V DC Return
Description
Chassis Ground
LNA Control
Connection Not required
Connection Not required
Aircraft AC Power
Aircraft AC Power
Connection Not required
LNA Bite
LNA BITE Return
Connection Not required
Fibre inserts are not required and will not be populated on the SDU mount connector, filler plugs
will be used to fill cavities. Size 5 Coax insert BP-6 is not required on the SDU mount connector
and will not be populated, a filler plug will be used to fill cavity.
Index Code: 81 (5,2,2)
(Top Insert: 08 / Middle Insert: 120Q2 / Bottom Insert: 12F5C2)
For the index code pins above, the dark colour represents the post.
Figure 2-15: TFS Interconnection Block Diagram – Single Aisle Configuration.
© THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval.
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TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
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Ref: TFS062/J-03/003
2.6.3. Interconnection Cables
2.6.3.1. RF Coaxial Cables
The SDU is connected to the DLNA and Antenna (see Figure 2-14), by means of a
RF low loss coaxial cable. The distance between the devices, and the cable selected
for the installation must be such that the cable losses remains within the limits
indicated within Figure 2-15, Note 2. All coaxial cable should be 50 Ohms nominally.
NOTE: Interconnect cables should be routed away from sources of potential
electromagnetic interference. Use shielded wires and cables where necessary.
2.6.3.1.1.
RF cable characteristics for the SDU to DLNA Tx port
Maximum Path Loss
Nominal Max Power
Frequency Range
1.4 dB (see Note)
60 Watts
1626.5 – 1660.5 MHz
2.6.3.1.2.
RF cable characteristics for the DLNA to SDU Rx port
Loss Range
Nominal Max Power
Frequency Range
6 – 25 dB (see Note)
0.5 Watts
1525 – 1559 MHz
2.6.3.1.3.
RF cable characteristics for the DLNA to Antenna port
Maximum Path Loss
Nominal Max Power
Frequency Range
0.3 dB (see Note)
46 Watts
1525 – 1660.5 MHz
NOTE: Applied to the complete RF cable path and not to each component within the
RF path.
2.6.3.2. Power Cables
The SDU mains power cable must be able to handle 115 Vac/5A (see note). The
recommended size is 20 AWG.
NOTE: Switch on surge is approximately 7A for the duration of 200ms.
The SDU to SCM power cable must be able to handle 12Vdc. Cable size is 22 AWG.
2.6.3.3. ARINC 429 connections
ARINC 429 connection cable must be a size 22 single twisted and shielded pair of
wires cable.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
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Installation and Maintenance Manual
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2.6.3.4. ETHERNET
The recommended Aerospace Grade 100Base-T Ethernet cable is P/N NF 24Q100.
The conductor AWG size (19 strands) is size 24.
Flammability requirements for this cable meet or exceed FAR25.869 requirements.
2.7.
SCM General Description
2.7.1. Hardware
The only SCM Part Number available is 82158A Series. This SCM is compatible with
the SA SDU Part Number 82155A Series and all other different SDU configurations.
The SCM hardware meets RTCA/DO-254 level D requirements.
The SCM contains four USIM (Universal Subscriber Identity Module) cards. The SCM
also contains an External Configuration Memory (ECM) storing the Owner
Requirement Table.
2.7.1.1. External Description
The SCM is composed by the following external elements:
The mounting plate with four attaching holes (1)
The 15-way D-type (male) socket (2)
The body of the SCM with one main identification label (3)
E1
SDU
MOD ONFI GURA
TION
ULE (S
CM)
MFR
SER
DMF
HW D
O-254
Level
Ins pe
ct
Am
dt A B
G CD
I J
PL
K L
PNR
M inor
REV.
SW P
NR
Suppl
y 12V
D.C .
CSD
10cm
Wt. 0.2
5k g M
AX
FAA T
Cx
FCC id
xxxxxx
-xx xx
Figure 2-16: Example of SCM external view.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
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TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
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2.7.1.2. Internal Description
The SCM is composed of the following internal parts:
One gasket between the D-type connector and the Body of the SCM (1)
One PEC card with a D-type connector attached (2)
Four USIM cards holders (3)
A plate attached to the body by four screws and washers (4)
A body attached to the single PEC card by four screws and washers (5)
P N R
M in
or
R E V
S W
PN R
S up
pl y 1
C SD
2V D
10 c m
.C .
W t. 0
.2 5 k g
F AA T
M AX
C x
FC C
id x
xxxxx
-xxxx
HW
D O25
4 L ev
el C
In s p
e ct
DM F
AB
GH CDE
PL A I J K F
L E1
S DU
M O D C O N F IG
U LE
MF R
( S C M R A T IO N
S E R
Figure 2-17: SCM exploded view.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
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TopFlight Satcom SDU & SCM
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2.7.2. ORT Parameters
The ORT is represented by a database containing a set of configuration data for the
exclusive use of the SDU. The ORT is partitioned for two types of parameters in
accordance with ARINC 781:
User parameters, for operator use
Secure parameters, for aircraft specific configurations
The ORT parameters are stored within the SCM and SDU, and are used to customise
the operation of the TFS system, allowing various preferences to be set to enable the
efficient use of the equipment within different platform configurations. The SDU and
SCM are delivered with a default ORT.
2.7.3. ORT Synchronisation
At each power up the SDU reads the ORT from the SCM, and compares it with its
locally stored copy. In normal condition the SDU and SCM ORTs should be the same,
but if different the SDU overwrites its local copy with the ORT read from the SCM.
The SDU uses that ORT until the SDU is powered down.
The SDU stores the local copy of the SCM Secure and User ORTs over a power
down in case one of the ORTs from the SCM is not valid when the SDU next powers
up.
NOTE: For more information concerning the operation of the SDU when it determines
that an ORT is not valid refer to the ARINC 781 specification section 3.4.2
‘Configuration & Identification Data’.
NOTE: For more information concerning changes or updates regarding ORT contact
the Thales TFS product support representative.
2.7.4. Basic Operation
When operating, the SCM interfaces with the SDU CCM via the SDU CPM. The SCM
operation will not commence until an input voltage from the SDU is detected.
Alternatively, when removed form the aircraft the SCM will also acknowledge an input
voltage from a personal computer (PC), and will operate as if it were connected to an
SDU.
A single USIM card is required for each Swift Broadband channel operated by the
SDU.
The SCM contains an External Configuration Memory (ECM). The ECM is a nonvolatile memory, which stores the ORT database.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
32
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2.7.5. Environmental Condition
Refer to Table 2-4.
2.7.6. Identification Label
The main manufacturer label gives the following information (Figure 2-18):
MFR
SER
DMF
Supply 12V D.C.
CSD 10 cm
Wt. 0.25 kg MAX
FAA TC x
FCC id xxxxxx-xxxx
HW DO-254 Level D
PLA
Minor
REV.
SW PNR
Amdt
PNR
A B C D E F
G H I J K L
SDU CONFIGURATION
MODULE (SCM)
E1
HW PNR: Equipment part number in alphanumeric form and bar code form
Minor rev: Minor revisions
SW PNR: For Owner Requirement Table (ORT)
MFR: Manufacturer code in alphanumeric and bar code form
SER: Basic part number and serial numbering alphanumeric and barcode
from.
DMF: Date of final factory inspection (month and year)
Amdt: Amendments
CSD: Compass Safe Distance
Wt: Weight
FAA TC: Federal Aviation Administration Type Certificate
FCC id: Federal Communications Commission identification
INSPECT
Figure 2-18: Example of SCM Identification Label.
2.7.7. SCM Electrical Characteristics
Power input: 8 to 15 Vdc. SDU typical supplied voltage 12 Vdc
Power consumption: 3.6 W or less
Max current: 300 mA at 12 Vdc
2.7.8. Weight and Dimensions
For overall dimensions refer to Figure 2-19
Mass = 0.25kg (0.44Lbs)
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
33
Issue 2
TopFlight Satcom SDU & SCM
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Ref: TFS062/J-03/003
110
SER
SW PNR
DMF
Supply 12VD.C.
CSD10cm
Wt. 0.25kg MAX
FAATC x
FCC idxxxxxx-xxxx
HWDO-254Level C
A B CD E F
G H I J KL
MFR
Minor
REV.
Amdt
88.9
PNR
Inspect
1.5
22.5
6.1
101
SDU CONFIGURATION
MODULE(SCM)
E1
83.8
PLA
13.1
Figure 2-19: SCM Overall Dimensions.
NOTE: All measurements given in Figure 2-19 are in mm.
2.7.9. SCM Connector
The SCM connector is a DB15 (15 pins – gauge 20) male connector (see Figure 2-20
below), mating with a DB-15 female connector on the cable. For complete description
of Pin Assignment refer to Figure 2-15, Note 3.
Chassis Stud
(GND Bonding)
Figure 2-20: Front View of the 15 Pin D-Type Connector.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
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TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
2.7.10. Equipment Electric Interconnection Diagram
The SDU interconnection diagram is given in Figure 2- 21 below. The diagram
illustrates all the necessary connection between the SCM and the SDU. For
description of detailed pin-to-pin connection refer to Figure 2-14 and 2-15.
15 way D-type connector (PL1)
+12V
0V
RS422_Rx_A
SDU
RS422_Rx_B
RS422_Tx_A
RS422_Tx_B
SCM
Figure 2-21: SDU/ SCM Interconnection Diagram.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
35
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
3.
INSTALLATION GUIDELINES
3.1.
Introduction
Issue 2
Ref: TFS062/J-03/003
The SDU and SCM should be installed in the aircraft in a manner consistent with
acceptable workmanship and engineering practices, and in accordance with the
instructions set forth in this manual.
To ensure that the system has been properly and safely installed in the aircraft the
installer should make a through visual inspection and conduct an overall operational
check of the system on the ground prior to commissioning to the Customer and or a
flight.
NOTE: Before installing any components or cabling, read all notes contained within
drawings.
3.2.
Interchangeability
The SDU and SCM will operate in any installation that complies with ARINC 781.
Therefore, the SDU and SCM are interchangeable only with identical system
components as covered in this manual.
3.3.
SDU / SCM Location and Accessibility Guidelines
Where possible the SDU should be installed in a pressurized zone that is also
partially temperature controlled, and mounted on an appropriate ARINC 600
compliant mounting rack. The SDU requires external forced air-cooling.
The SCM should be installed as close to the SDU as possible in order to keep the
cable runs to a minimum.
To determine the best location, the installer must select equipment locations to allow
easy access to these components and their connectors. Equipment location will vary
with aircraft type and design/installation specifications.
The electronic bay, and the cabin hat rack are suitable places to install this unit.
The SDU must be installed in a location that allows the following facilities to be
accessible:
Front Panel LEDs
Front Panel TFS system Test Push Button
Software loading RJ45 connector
CAUTION
BEFORE EQUIPMENT INSTALLATION ENSURE THAT THE AIRCRAFT POWER
SUPPLY CIRCUIT BREAKER IS POSITIONED IN THE OFF CONDITION.
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Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
36
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
3.4.
Issue 2
Ref: TFS062/J-03/003
Mounting Tray
The mounting tray used for the installation of the SDU must comply with the design
specifications for the 6 MCU (Modular Concept Unit) form factor. Refer to the ARINC
600 Specification for detailed information regarding the design of compatible
equipment and airframe installations.
Figure 3-1: Example of an ARINC 600, 6 MCU Mounting Tray.
3.5.
Cooling
The SDU is designed to accept an installation configuration able to provide forced aircooling as defined in Section 3.5 of the ARINC Specification 600.
In normal operation the SDU will be cooled by forced convection with air supplied
from the platform services at a maximum flow rate of 50 kg/hr and a temperature of
up to 400 C. The cooling air will enter the equipment chassis at the bottom via a
plenum chamber and exhaust at the top.
3.6.
Power Requirements
It is the responsibility of the installer to select the appropriate gauge of wire for power
connections, and to ensure that the required safety and voltage drop requirements
are complied with.
For SDU power supply specifications refer to:
2.3.10: ‘SDU Electrical Characteristics’
Figure 2.8: ‘ Aircraft Power Distribution’
Figure 2-14: ‘TFS System Interconnection Diagram’
For SCM power supply specifications refer to:
2.7.8: ‘SCM Electrical Characteristics’
Figure 2-14: ‘TFS System Interconnection Diagram’
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Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
37
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
3.7.
Issue 2
Ref: TFS062/J-03/003
SDU RF Connections
The SDU is connected to the DLNA through a RF coaxial cable. Installation designer
must be aware that the shorter the cable is, the better system performance.
As the SDU/DLNA low loss cable is sometimes almost rigid and it could have a
diameter not compatible with the IGA and DLNA connectors, it is recommended to
install a short portion of a smaller and more flexible cable at each end of this low loss
cable (pig tail type installation).
If necessary, secure the cable by means of evenly spaced collars to prevent the cable
from chafing on aircraft parts and surfaces. These collars must be of a design, which
avoids damaging the cable.
CAUTION
DO NOT EXCEED MINIMUM CABLE RADIUS OF CURVATURE FOR THE
COAXIAL CABLE. USE DUMMY CABLES FOR A FIRST INSTALLATION TO
DETERMINE CABLE RUNS. INSTALL FINAL CABLES ONLY AFTER THIS
MODELING OPERATION.
CAUTION
ONLY PREFORMED RF CABLES SHALL BE CONNECTED TO THE SATCOM
SYSTEM EQUIPMENT. ATTEMPTING TO FORM CABLES OR APPLYING STRESS
TO THE CABLES WHILE THEY ARE CONNECTED TO THE EQUIPMENT
CONNECTORS MAY CAUSE DAMAGE TO THE EQUIPMENT.
NOTE: Interconnect cables should be routed away from sources of potential
electromagnetic interference. Use shielded wires and cables where necessary.
3.7.1. RF Insertion Losses
The SDU RF interface with the Antenna via a DLNA device. The diplexer and LNA are
combined into one unit for installation. The Diplexer function couples transmit signals
from the SDU to the respective antenna. The LNA amplifies the very low level L-band
receive signal from its respective antenna and couples this amplified signal to the
SDU.
For detailed RF insertion losses refer to Figure 2-15 Note 2. To ensure these
requirements are met, some installations need the SDU to be installed in close
proximity to the antenna subsystem components or the use of low loss coaxial cable.
The total loss between the DLNA and the SDU must be in the range 6 to 25 dB. If the
RF cable type being used for a short cable length is less then 6 dB, an attenuator
must be fitted to ensure the required loss is achieved.
3.7.2. VSWR
The Voltage Standing Wave Ratio (VSWR) of all RF cables should be 1.2:1 or better.
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written approval.
38
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
3.8.
Issue 2
Ref: TFS062/J-03/003
Bonding Requirements
The bonding of all LRUs to the airframe must not exceed 20 milliohms. However
some aircraft manufacturers or design/installation organisation may require a lower
value than the recommended 20 milliohms.
3.9.
SDU Fitting Instructions
Unpack the SDU from the transportation packaging. Perform a visual inspection of the
unit for evidence of damage incurred during transportation. If a claim for damage is to
be made, save the shipping container to substantiate the claim, and contact your
Thales representative. Remove the ESD protection cap on the ARINC 600 connector.
CAUTION
THE SDU IS ELECTROSTATIC DISCHARGE SENSITIVE EQUIPMENT. OBSERVE
STANDARD ESD PROCEDURES WHEN HANDLING THE EQUIPMENT.
Ensure that the electrical supply to the mounting tray back connector is removed.
Carefully place the SDU on its mounting tray and slide it towards the mounting tray
back connector, following the direction of the arrow indicated in figure 3-3.
When the SDU is fully engaged into the connector raise the mounting tray Hold Down
Clamps (see Figure 3-3), over the hooks of the SDU and hand tight in the clockwise
direction.
As the LRU is tightened into position, and in order to prevent electrical pins from
bending, ensure that the SDU is uniformly inserted into the mounting tray back
connector.
SDU
installation direction
Hold Down Clamps
Figure 3-3: SDU Installation on to ARINC 600 Mounting Tray.
CAUTION
ENSURE THAT THE THUMBSCREW HOLD DOWN CLAMPS HAVE BEEN
FASTENED, AND THAT THE LRU IS SECURELY HELD INTO PLACE.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
39
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
3.10. SDU Removal Instructions
Ensure that the electrical supply to the mounting tray back connector is removed.
Loose mounting tray Hold Down Clamps (counter clockwise). Ensure that the Hold
Down Clamps are loosened so that the SDU is uniformly extracted out of the
mounting tray back connector. Clear the retaining hooks on the front of the SDU.
Separate the SDU from the mounting tray back connector and extract the SDU by
pulling on the carrying handle at the front of the SDU following the direction of the
arrow indicated in Figure 3-4.
Install an ESD protection cap on the SDU ARINC 600 back connector.
SDU
removal direction
Hold Down Clamps
Figure 3-4: SDU Removal from ARINC 600 mounting tray.
3.11. SCM Fitting Instructions
Unpack the SCM from the transportation packaging. Perform a visual inspection of
the unit for evidence of damage incurred during transportation. If a claim for damage
is to be made, save the shipping container to substantiate the claim, and contact your
Thales representative. Remove the ESD protection cap on the D Type connector.
CAUTION
THE SCM IS ELECTROSTATIC DISCHARGE SENSITIVE EQUIPMENT. OBSERVE
STANDARD ESD PROCEDURES WHEN HANDLING THE EQUIPMENT.
Place the SCM to the dedicated mounting fixture and insert the four (1) fixing screws
to finger tightness only. See Figure 3-5. After all four fixing screw have been inserted
tight the screws with an appropriate tool.
Insert the cable from the SDU to the D Type connector (other half from the SDU) and
tighten the aircraft mating connector into the two (2) female screw locks.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
40
Issue 2
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Ref: TFS062/J-03/003
Fixing Screw (1)
Screw locks (2)
D Type Connector (3)
Figure 3-5: SCM Installation.
CAUTION
ENSURE THAT THE FIXING SCREWS HAVE BEEN FASTENED, AND THAT THE
LRU IS SECURELY HELD INTO POSITION.
3.12. SCM Removal Instructions
Ensure power to the SDU is disconnected.
Loosen the two (2) screw locks that secure the 15-pin D Type connector to the SCM.
See Figure 3-6.
Disconnect the D connector. Bag and stow the cable as required.
Install an ESD protection cap on the SCM D Type connector.
Assuming that the mounting fixture is equipped with anchor nuts, loosen and remove
the four fixings screws that retain the SCM to its mounting fixture while supporting the
SCM. Retain the screws for future installation.
Remove the SCM, and visually inspect it for any signs of damage.
Fixing Screws (4 off)
Figure 3-6: SCM Removal.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
41
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
4.
INSPECTION AND SYSTEM CHECKOUT
4.1.
Inspection/Check procedure
Issue 2
Ref: TFS062/J-03/003
Table 4.1 below provides a visual inspection/check procedure that should be
performed during or after the SDU/SCM installation, or as a periodic maintenance
inspection check of the installation.
EQUIPMENT
INSPECTION/CHECK PROCEDURE
•
•
Wiring and RF
cables
•
•
•
•
•
SDU
•
•
•
•
SCM
•
Ensure that a continuity check of all the installation wiring
harness had been carried out, and that all the sources are
correctly rated on the correct pins
Check that none of the cables have been damaged, and
cannot be damaged by components that are installed later
Check that the cable runs are spaced away from any
moving or hot part that could damage cables when in use
Verify that the various RF cables are within their minimum
radius of curvature tolerances
Check that any attenuators that may have been used for
the installation have not been omitted or mismatched
Examine the assembly for external condition (absences of
fractures, dents, deformations, cracks, and/or any other
abnormal damage)
Check that the unit is properly installed and that hold down
clamps are firmly tightened
Check screws and nuts general condition
Check that the contact resistance between the SDU/SCM
and a point on the aircraft structure close to the
component does not exceed 20 milliohms
Check that the correct air cooling and air flow is provided
to the SDU
Examine the assembly for external condition (absences of
fractures, dents, deformations, cracks, and/or any other
abnormal damage)
Check that the unit is properly installed, that all fixing
screws are firmly tightened, and the cable to the SDU is
secure
Table 1: Installation Inspection/Check procedure.
4.2.
System Checkout
At this stage of the installation it is assumed that a continuity check of the wiring has
been made, a visual check of the installation harness and RF cabling has been
performed, and that the inspection/check procedure has been carried out.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
42
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
4.2.1. Post-installation Test
This test requires that all the Satcom system LRUs (SDU, SCM, DLNA, Antenna) be
connected and operating properly, with a means of displaying any system faults
detected by the LRUs during the BITE (Built In Test Equipment) test. The results of
the test are indicated on the SDU front panel LEDs. Refer to the Testing and Fault
Isolation section for information on the SDU fault detection capabilities.
If no system faults are indicated by the BITE test, then the subsystem installation
should be considered acceptable. If any subsystem LRU fails the test, it must be
returned to the vendor (refer to your vendor customer support).
WARNING
THE RF POWER RADIATED BY THE TFS SYSTEM ANTENNA CAN CAUSE
BODILY HARM. A PERSON IS IN DANGER IN A ZONE WHERE THE POWER
FLUX IS 1 MW/CM2, OR GREATER. DURING SATCOM OPERATION THE
SAFETY DISTANCE FROM THE ANTENNA MUST BE NO LESS THAN 3.5M OR
12 FEET (INTERMEDIATE GAIN ANTENNA). SINCE THERE ARE VARIOUS
POSSIBLE ANTENNA LOCATIONS, IT IS THE RESPONSIBILITY OF THE
OPERATOR TO DETERMINE THE AREA OF HAZARD FOR THEIR TFS SYSTEM
CONFIGURATION AND TO TRAIN PERSONNEL IN GROUND SAFETY
PROCEDURES.
WARNING
DURING ANTENNA OPERATION (TRANSMISSION), ENSURE MINIMUM
EXPOSURE OF ALL PERSONNEL TO ANY REFLECTED, SCATTERED, OR
DIRECT BEAMS.
CAUTION
WHEN TESTING THE COMPLETE TFS SYSTEM (ANTENNA SYSTEM INCLUDED)
REFER TO THE SPECIFIC ANTENNA IMM FOR FURTHER SAFETY
REQUIREMENTS AND SPECIFICATIONS. THE SDU MUST NOT BE POWERED
WITHOUT AN ANTENNA OR SUITABLE LOAD CONNECTED ON THE HIGH
POWER TRANSMIT OUTPUT PORT.
CAUTION
NEVER CONNECT OR DISCONNECT A SATCOM LRU WHEN POWER IS
APPLIED, IN ADDITION, NEVER APPLY HIGH-LEVEL RF SIGNAL TO A
POWERED-DOWN LRU.
CAUTION
ENSURE THAT THE APPROPRIATE ORT DATABASE IS INSTALLED IN THE SCM
AND/OR SDU BEFORE PERFORMING SYSTEM OPERATIONS.
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Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
43
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
5.
MAINTENANCE
5.1.
Introduction
Issue 2
Ref: TFS062/J-03/003
Field lubrication or other maintenance procedures are not required. The design of the
SDU and SCM is such that they do not require field maintenance to maintain
airworthiness. If functional problems occur, the SDU Built-in-Test Equipment (BITE)
capability identifies the faulty LRU. The SDU and SCM maintenance is limited to
replacement on verified failure.
CAUTION
TO AVOID INJURY TO PERSONNEL OR DAMAGE TO EQUIPMENT, ENSURE
ADEQUATE PRECAUTIONS ARE TAKEN WHILE PERFORMING ANY WORK IF
THE ELECTRICAL POWER IS APPLIED TO THE LRUs.
CAUTION
TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFT POWER OFF
BEFORE REMOVING OR INSTALLING LRUs.
5.2.
Cleaning of Mechanical Parts
Equipment chassis covers give the necessary protection to keep dust away from
electronic circuits. If cleaning is required this has to be limited to the removal of
particles of dust, oil, grease, condensation, etc and only limited for those equipment
accessible parts. Before any cleaning action is carried out ensure that the equipment
is disconnected from all electrical power sources, and all the necessary ESD
precautions are observed.
For mechanical part cleaning:
For dust removal use a cleaning wipe, a silk paintbrush or low-pressure
compressed air
For removal of finger marks, grease, etc, clean the parts with a cleaning wipe
and isopropyl alcohol, exercising care to not damage information labels
CAUTION
MOISTURE AND DIRT CAN CAUSE DAMAGE TO EQUIPMENT.
5.3.
Periodic Checks
See Inspection/ Check procedure in Table 1.
5.4.
Cabling and Connections
Periodically check cable connectors (recommended) and if required, tighten
connectors as needed with connector manufacturer’s specifications.
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Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
44
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
6.
Issue 2
Ref: TFS062/J-03/003
TESTING AND FAULT ISOLATION
Information within this section describes how the TFS system, SDU, SCM, and
Antenna failures are monitored detected, and reported.
6.1.
BITE Function
The primary purpose of BITE is to assist aircraft maintenance personnel in the
correct maintenance of avionics equipment in a cost effective manner. The BITE
does not contribute to the required function of the TFS system, but makes it easier to
test or debug it.
The SDU controls the TFS system BITE. It collects BITE information from other
LRUs, and can request other LRUs to run tests. The BITE automatically detects
failures, providing a mechanism to discover erroneous behaviour of TFS system
components.
Fault information is reported to a local maintenance system (e.g. CFDS system or
other OMS), and this information is made available to maintenance personnel by
means of discretes and/or LEDs on the SDU front panel. Failures can also be
reported to a dedicated local maintenance function through SNMP (Simple Network
Management Protocol) and the MIB (Management Information Base).
The System BITE failure data is stored in the SDU within a Non-Volatile Memory
(NVM) area. The BITE operates at various levels as indicated in Figure 4-1 below.
Figure 6-1: Example of BITE communication for TFS system.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
45
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
6.2.
Issue 2
Ref: TFS062/J-03/003
Test Functions
An operator can verify the operational serviceability of the SDU and SCM by means
of a set of testing facilities installed within the SDU. The SDU performs two distinctive
types of test:
A Power On Self-Test (POST) is automatically activated at SDU start up
A Person Activated Self Test (PAST) can be initiated by an operator by
depressing a Self-Test push button located on the front panel of the SDU,
(see Figure 2-5 item 17)
6.2.1. POST
At SDU start up (Power On), and with aircraft in the ‘on ground’ condition the FPL
(Front Panel LEDs) will display the following test sequence:
Start
Apply
pow er
A ll LE D s illum inate A m ber for
approxim ately 90 seconds
LED s flash G reen for
approxim ately 3-5 seconds
LE D s rem ain in O ff condition
for the duration of
approxim ately 75 seconds
LE D s driven to indicate a
steady G reen condition
Figure 6-2: POST LEDs sequence.
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Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
46
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
6.2.2. PAST
The PAST function is initiated by depressing the front panel Test Button (This
function is only possible with aircraft on ground). To acknowledge PAST initialisation
all the front panel LEDs start to flash green at the frequency of 2Hz. After
approximately 75 seconds the SDU will transit into Operational Mode with the LEDs
displaying the TFS system serviceability condition.
This feature represents an interactive, manual test facility, which assists in the
following:
Active search of failures by triggering a series of system diagnostic tests
Verification testing e.g. after the installation of a replacement unit
Failure confirmation purpose
NOTE: PAST test can only be initiated after the POST test has completed.
Start
Push front
panel Test
Button
All LEDs extinguish and
remain in Off condition for
approximately 90 seconds
LEDs flash Green for 3-20
seconds
Time variations are
due to ORT
synchronisation
LEDs driven to Indicate
a steady Green condition
Figure 6-3: PAST LEDs sequence.
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Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
47
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
6.3.
Issue 2
Ref: TFS062/J-03/003
Fault Isolation
6.3.1. Failures
Failures are reported to an operator by means of a set of multicoloured LEDs located
on the SDU front panel. LEDs can enter the following steady states:
Normal equipment operation indicated by the relevant LEDs displayed in a
steady Green condition
Equipment Hard Failures are indicated by all relevant LEDs displayed in a
steady Red condition
Partial equipment failures are indicated by all relevant LEDs displayed in a
steady Amber condition
An LED in OFF (extinguished) condition indicates that the relevant
equipment and or a resource is not active or not installed
6.3.2. Front Panel Indications
Table 2 provides LED status decoding information.
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Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
48
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
LED Name
Flashing Green
Steady Green
Amber
Issue 2
Ref: TFS062/J-03/003
Red
Off
Partial Failure (Not Indicted) or
ARINC 429 / AFDX / RS-422
Bus Failure3
SCM Memory Fail
(Not Indicted)1 or RS-422 Bus
Failure3
Partial Failure (Not Indicted)1 or
ARINC 429 Bus Failure 3
SDU Failed (Indicted)2
SDU Not Powered
USIM Read/Write Fail. No
attempt at SBB registration
SCM Not Installed or SDU
Not Powered
Antenna Failed (Indicted) 2
SDU Not Powered
DLNA OK
N/A
DLNA Failed
(Indicted)2
SDU Not Powered
SDU in Self-Test
NA
NA
NA
NA
Ext. BSU
SDU in Self-Test
NA
NA
NA
NA
Ext. Data
Bus
SDU in Self-Test
All Data Buses (ARINC 429
/ AFDX / RS-422) OK
Nav Data not available. ARINC
429 Bus from IRS(s) inactive or
IRS Data invalid 4
Bus Failed3 (ARINC 429 /
AFDX / RS-422)
SDU Not Powered
SDU Not Powered
SDU
SDU in Self-Test
SCM
SDU in Self-Test
SCM/USIM(s) OK
Antenna
SDU in Self-Test
Antenna OK
DLNA
SDU in Self-Test
Ext. HPA
SDU OK
ORT/Config.
SDU in Self-Test
ORT(s)/Hardware
Configuration Straps
ORT Minor Failure
(Not Indicted)1
ORT Major Failure6 or
Hardware Configuration
Straps Parity Failure
(Indicted)2
Sat. Link #1
SDU in Self-Test
Channel #1 Service
Available, ie Logged-On or
Registered
Channel #1
attempting Log-On or
Registration
N/A
Channel #1 Not attempting
Log-On or Registration7
Sat. Link #2
SDU in Self-Test
Channel #2 Service
Available, ie Logged-On or
Registered
Channel #2
attempting Log-On or
Registration
N/A
Channel #2 Not attempting
Log-On or Registration7
NOTE: See next page for list of Explanatory Note.
Table 2: Front Panel indications.
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without the company’s prior written approval.
49
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
List of Explanatory Notes for Table 2
1.
Not Indicted means that there is an equipment ‘partial’ failure such that
service Registration / Log-On is still attempted.
2.
Indicted means that there is an equipment failure such that Registration / LogOn is not attempted.
3.
In the event of a Bus Inactive Failure, the ‘Data Bus’ LED illuminates Red and
the appropriate LRU status LEDs illuminate Amber, e.g. if the SDU reports
that the Antenna to SDU bus is inactive or the Antenna reports that the SDU
to Antenna bus is inactive, then the ‘Data Bus’ LED illuminates Red and the
SDU and Antenna LEDs illuminates Amber.
4.
This is a special case. There will be frequent legitimate occurrences of IRS(s)
being switched off whilst On-Ground and even after an IRS is switched on;
there is an alignment period, during which the Nav Data is invalid. Under
these circumstances, the only action is to illuminate the ‘Data Bus’ LED
Amber, irrespective of whether in On-Ground or In-Air state.
5.
The ORT/Configuration LED illuminate Amber in the following circumstances:
a. Type 1 ORT Synchronization Minor Failure – Secure ORT within SCM
- If the Secure ORT read from the SCM is not valid and if ‘local copy’
Secure ORT is valid.
b. Type 4 ORT Synchronization Failure - User ORT within SCM - If the
User ORT read from the SCM is not valid AND if ‘local copy’ User
ORT is valid.
c. Type 5 ORT Synchronization Failure - User ORT in SDU - if SDU User
ORT is invalid.
6.
The ORT/Configuration LED illuminates Red in the following circumstances:
a.
Type 1 ORT Synchronization Major Failure - Secure ORT within SCM
- If the Secure ORT read from the SCM is not valid AND if ‘local copy’
Secure ORT is not valid.
b. Type 2 ORT Synchronization
c. Type 3 ORT Synchronization Failure - Secure ORT in SDU that is
integral part of SW - if SDU Secure ORT is invalid.
d. Hardware Straps Parity Failure. SDU be indicted.
7.
There are many reasons why a channel will not attempt Log-On or
Registration, including (but not limited to), OCXO warming up, equipment
indictment, commanded Log-Off or De-Registration.
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Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
51
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
6.3.3. Fault Logging
All information of degraded and abnormal equipment function will be logged internally
and made available to a dedicated local maintenance system (e.g. CFDS).
6.3.4. Service Availability Discretes
The status of various system functions can be reported by means of the Service
Availability Discretes available on the ARINC 600 connector.
Function
Pin
Allocation
Steady State Open Circuit
Steady Ground1
SDU Not Powered
MP 15F
SDU Powered
SDU Not Powered
System Failed
MP 11F
System OK
System Failed2
SDU Failed
MP 12E
SDU OK
SDU Failed3
SCM Failed
MP 12F
SCM OK or not installed
SCM Failed4
Ext HPA Failed
MP 13E
Ext HPA OK or not installed
Ext HPA Failed
DLNA Failed
MP 13F
DLNA OK
DLNA Failed
Antenna Failed
MP 14E
Antenna OK
Antenna Failed
Ext BSU Failed
MP 14F
BSU OK or not installed
BSU Failed
Bus Failed5
MP 15E
All external data buses OK
(ARINC 429/AFDX/RS422)
Bus Failed (ARINC
429/AFDX/RS422)
Sat Link #1 Not
Available
MP 11E
Satcom Channel #1 Logged
On/Registered
Sat Link #2 Not
Available
TP 01K
Satcom Channel #2 Logged
On/Registered
Satcom Channel #1
Not Logged On/Not
Registered
Satcom Channel #2
Not Logged On/Not
Registered
Table 3: SDU Service Availability Discretes.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
52
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
Issue 2
Ref: TFS062/J-03/003
List of Explanatory Notes for Table 3
1.
The ‘Steady Ground’ state corresponds to the equivalent LED Red state,
except for the Sat Link #1 and #2 Not Available discretes, for which the
‘Steady Ground’ state corresponds to the equivalent LED Off or Amber states.
2.
The System Failed discrete ‘Steady Ground’ state corresponds to one or
more LEDs being illuminated red.
3.
SDU Failed discrete only to be asserted in the event that an SDU H/W or S/w
failure is detected, not in the event that there is an ORT or configuration
straps parity failure. In the latter case, only the System Failed discrete should
be asserted.
4.
SCM Failed discrete only to be asserted in the event that an SCM H/W failure
is detected, not in the event that there is an ORT failure. In the latter case,
only the System Failed discrete should be asserted.
5.
The Bus Failed discrete provides no indication of activity on the Ethernet
buses.
6.3.5. Service Availability Discrete Lamps
The Service Availability Discretes have open circuit and ground states that are
capable of driving incandescent lamps connected to an external supply.
Typically, each discrete is fed via one or two (in parallel) incandescent lamps to an
aircraft 28 Vdc supply. This 28 Vdc supply can be dimmed to approximately 14 Vdc
for night time operation. The 28 Vdc is a nominal value and can vary as defined in
RTCA/DO-160E. A typical incandescent lamp would be 28Vdc, 20mA.
Each Service Availability Discrete is able to continuously sink at least 50mA and be
capable of holding a cold inrush current of up to 490 mA during the first 10
millisecond of activation as per ARINC 781.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
53
TopFlight Satcom SDU & SCM
Installation and Maintenance Manual
7.
Issue 2
Ref: TFS062/J-03/003
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
Maintenance requirements and instructions for continued airworthiness of the TFS
SDU and SCM components are contained in the paragraphs that follow.
Installation of SDU and SCM on an aircraft by an amendment to the Type Certificate
(TC), Supplemental Type Certificate (STC) or Form 337 obligates the aircraft
operator to include the maintenance information supplied by this manual (and listed
below) in the operator’s Aircraft Maintenance Manual and the operator’s Aircraft
Scheduled Maintenance Program.
Maintenance information for SDU and SCM, TFS LRUs (system
description, removal, installation, testing, etc.)
The part numbers (see section 2) of the LRUs being installed (SDU and
SCM) should be placed into the aircraft operator’s appropriate aircraft
Illustrated Parts Catalogue (IPC).
Wiring connection information contained in this manual (see sections 2
and 3) should be placed into the aircraft operator’s appropriate Wiring
Diagram Manual.
The SDU maintenance is considered as an “On-condition”, and as such
no additional maintenance is required other than a check for security and
operation at normal inspection intervals.
The SCM equipment is subject to minimal preventative maintenance,
which is specific to life limitations associated to the internal USIM cards.
For further details refer to your Thales representative.
If a system LRU is inoperative remove the specific unit, secure cables and
wiring, collar applicable switches and circuit breakers, and placard them
inoperative. Revise equipment list and weight and balance as applicable
prior to flight and make a log book entry that the unit was removed (refer
to section 91.213 of the FAR or the aircraft’s Minimum Equipment List
(MEL).
SDU and SCM can be repaired by an Approved Maintenance
Organization
Once repaired, reinstall the LRU in the aircraft in accordance with the
original Form 337 approved data or instructions in this manual. Perform a
Return to Service test of the system and approve it for return to service
with a logbook entry required by section 43.9.
© THALES AVIONICS Ltd. This document and any information included are the property of
Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior
written approval.
54

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