| Download: |  |
| Mirror Download [FCC.gov] | |
| Document ID | 3659344 |
| Application ID | Y+M0ShuXiITZDqCgX0kggQ== |
| Document Description | User Manual |
| Short Term Confidential | No |
| Permanent Confidential | No |
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| Document Type | User Manual |
| Display Format | Adobe Acrobat PDF - pdf |
| Filesize | 421.48kB (5268525 bits) |
| Date Submitted | 2017-11-30 00:00:00 |
| Date Available | 2018-01-14 00:00:00 |
| Creation Date | 2014-06-18 09:40:22 |
| Producing Software | Adobe Acrobat 11.0.7 |
| Document Lastmod | 2014-12-31 09:31:28 |
| Document Title | Iridium SATCOM System Welcome Package |
| Document Creator | Adobe Acrobat 11.0.7 |
| Document Author: | Technical Publications |
Iridium ®
Welcome
Package
Airbus Iridium SATCOM System
100 Cattlemen Road, Sarasota, Florida 34232
Telephone: 941-371-0811 Facsimile: 941-377-5591
Welcome!
Dear Valued Customer,
All of us at L-3 Aviation Recorders take this opportunity to say “thank you” for your selection of the L-3
Airbus Iridium Satellite Communication (SATCOM) system.
This SATCOM system, also identified as the Automated Flight Information & Reporting System (AFIRS),
is a multi-function voice and data communication system that provides a link between the aircraft and
ground using the existing Iridium satellite constellation. The system consists of:
Satellite Data Unit (SDU)
SDU Configuration Module (SCM), which houses the system SIM card
Iridium Antenna
Coaxial Cable
These system elements are described in further detail in the following sections of this Welcome Kit
package. The system performs the following primary functions:
Satellite Phone
The Iridium SATCOM System contains a single-channel Iridium satellite phone along with an internal
Private Branch Exchange (PBX) system. The AFIRS 228 SDU includes telecom functions integrated into
the cockpit audio system for the flight crew and separate calling capability through conventional two-wire
“tip and ring” telephony devices. Cockpit dialing and control functions can be performed by using the
aircraft's Multipurpose Control Display Units (MCDUs). Up to two wired or eight cordless handsets can be
added in the cabin for intercom, call transfer, conference calling, camp-on calling and noise-cancelling
features. The aircraft can call or be called from any conventional telephone, as well as any other similarlyequipped aircraft. This provides the crew with worldwide access to MedLink or other emergency medical
services.
ACARS Satellite Data Unit
For ACARS-equipped aircraft, the Iridium SATCOM System can function as a standard ARINC
741/761 Satellite Data Unit (SDU) when interfaced to the aircraft's ACARS Communication Management
Unit (CMU). The system uses a dedicated Iridium satellite channel for data services. The Iridium SATCOM
System receives messages from the CMU, prioritizes the messages, and transmits them over the Iridium
satellite link. ACARS messages received from the satellite link are routed to the CMU for processing.
Confidential
Page 1
100 Cattlemen Road, Sarasota, Florida 34232
Telephone: 941-371-0811 Facsimile: 941-377-5591
Electronic Flight Bag (EFB) Interface
If desired, the Iridium SATCOM System SDU provides an EFB with an interface to the EFB message
transport system. An Ethernet port provides the physical connection between the devices – using industry
standard IEEE 802.3 LAN technologies. Once physically connected, the SDU routes to the EFB a webbased portal that can be accessed by EFB applications using a defined IP based protocol, supporting text
messaging and other functions.
L-3 Aviation Recorders manufactures and services the Iridium SATCOM system. To learn more about L-3
products, please visit the company’s website at: http://www.l-3ar.com/ .
This Welcome Package includes the following useful information for you to obtain support for effective
operation of your Iridium SATCOM system:
L-3 Contact Information
Authorized Service Facility Information
Compliance Package (Export Compliance Certification, End-Use/User Statement)
Technical Documentation (Quick Guide, and Installation & Operation Manual)
Customer Training Schedule
CD – includes all Welcome Package documentation & a Component Maintenance Manual
Thank you again for your interest in our products. We look forward to working with you to bring your new
Airbus Iridium SATCOM System on-line in your fleet operations, and to meeting your needs and
expectations in the support and service of your Airbus Iridium SATCOM System.
Mike Phillips
Product Support Manager
L-3 Aviation Recorders
Confidential
Page 2
100 Cattlemen Road, Sarasota, Florida 34232
Telephone: 941-371-0811 Facsimile: 941-377-5591
Table of Contents
This Welcome Package includes the documents listed in the table below.
Keep in mind, these documents may not be the latest up-to-date revisions. Please check the L-3 Customer
Support website for the latest update available at: http://www.l-3ar.com/customer/index.htm
Documents
Welcome Letter
L-3 Contact Details
Airbus Iridium SATCOM System Quick Start Guide
Iridium SIM Card Registration
Installation Manual Airbus Iridium SATCOM System
Airbus Iridium SATCOM System Component Maintenance Manual
Confidential
Page 1
Sarasota,
t Florida
Fl id 34232
CAGE Code 06141
Phone: (941) 371–0811 | FAX: (941) 377–5591
http://www.l-3ar.com/
Iridium Customer Support
pp
Technical support, Reliability, Product support
Daren Welker
Carlo Mammelli
Dave Dowding
Product Support Engineer
Publications Supervisor
Senior Product Support Engineer
Phone
Cell
Fax
Email
Phone
Cell
Fax
Email
Phone
Cell
Fax
Email
941.379.1620
941
941.372.2313
372 2313
941.377.5591
daren.welker@l‐3com.com
Mike Phillips
Product Support Manager
Phone
Cell
Fax
Email
941.377.5547
941.726.0107
941.377.5591
mike.phillips@l‐3com.com
941.377.5550
941.726.9050
941
726 9050
941.377.5591
charles.mammelli@l‐3com.com
941.377.5551
941.284.3048
941
284 3048
941.377.5591
david.dowding@l‐3com.com
Technical
Documentation
For access to Technical documentation, please log on to:
Website: http://www.l‐3ar.com/customer/technical.htm
For specific requests on technical documentation, contact:
Email: charles.mammelli@l‐3com.com
Training
Customer Iridium Operator training is provided
three (3) times a year at the L3AR Facility in
Sarasota, FL.
2014 Training Dates
Feb. 18‐20, 2014
Jun. 23‐25, 2014
Oct. 20‐22, 2014
For more details concerning
g L3AR Training
g please
use this link:
Website: http://www.l‐3ar.com/services/training_aviation.htm
For questions about product training, contact:
Email: daren.welker@l‐3com.com
Sarasota,, Florida 34232
CAGE Code 06141
Phone: (941) 371–0811 | FAX: (941) 377–5591
http://www.l-3ar.com/
Authorized Service Facility
A European service facility will be established later in 2014. Until such
time, all Iridium repairs will be performed at L‐3 Factory.
Address:
L‐3 Communications Aviation Recorders
100 Cattlemen Rd. Sarasota, Florida 34232
Attention: Repair Station – 941‐377‐5517
941 377 5517
Repair Station Manager: Gerald Godbee
Phone: 941.377.5531Email: gerald.godbee@l‐3com.com
Airbus Iridium SATCOM System
Airbus Iridium SATCOM System
Quick Start Guide
SDU L-3 part number 228E5733-00
SCM L-3 part number 418E5733-00
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Airbus Iridium SATCOM System
SECTION 1 ‐ OVERVIEW
1. Airbus Iridium SATCOM System Overview
The Airbus Iridium SATCOM System will be certified to TSO C‐159a for voice and data safety‐services. It
has a dual‐channel Iridium link, one dedicated for data ‐ with the capability to send and receive standard
ACARS messages between the aircraft’s Air Traffic Service Unit (ATSU), and the other prioritized for
voice via a certified terrestrial service provider.
The Automated Flight Information Reporting System (AFIRS) provides a satellite voice and data
communications (SATCOM) link with the Public Switched Telephone Network (PSTN) via the Iridium®
satellite network. The system uses a standard ARINC 741/761 SATCOM interface to the flight crew’s
Audio Integrating System and ARINC 739A Multi‐Purpose Control and Display Units (MCDUs) in the
cockpit, as well as providing 3‐extension Public Branch Exchange (PBX) capability for up to 2 handsets in
the cabin.
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Airbus Iridium SATCOM System
Satellite Data Unit (SDU)
2. SDU Configuration Module (SCM)
The SCM is housed in a small enclosure, which is designed to be mounted within 24” of the SDU rear
connector. The SCM and antenna connect directly to the SDU. The SDU is the heart of the system and
provides all of the interfaces to other aircraft systems.
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Airbus Iridium SATCOM System
SECTION 2 – SYSTEM CONFIGURATION
You configure the Airbus Iridium SATCOM System Satellite Data Unit (SDU) via Ethernet using a laptop,
web browser, and the AFIRS Maintenance User Interface (MUI). An RJ‐45 Maintenance Port jack is
located behind the access door on the front panel of the SDU.
IMPORTANT: READ BEFORE CONFIGURING SATCOM SYSTEM
The MUI only accepts English‐language characters and numbers.
The aircraft’s status must be deemed “On‐Ground” to access Maintenance Mode and make any
system changes. If the aircraft is deemed “In‐Air”, the Enter Maintenance Mode button will be,
or will become, unavailable. If the aircraft status changes to “In‐Air” while in Maintenance
Mode, the system will reboot automatically and return to Operational Mode without saving any
changes.
Entering Maintenance Mode disables all MCDU functions.
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Airbus Iridium SATCOM System
1. Install SIM Card
1. Remove the four screws from the plate on the SCM.
2. Remove the plate on the SCM to reveal
the SIM enclosure.
3. Slide the SIM Enclosure to release.
4. Lift the SIM Enclosure.
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Airbus Iridium SATCOM System
5. Slide the SIM card in the slot. It will fit only one way; do not force.
6. Close the SIM Enclosure and slide to the left to lock.
The SIM Card is now installed.
7. Replace the plate.
8. Replace the four screws using a small amount of threading Loctite 222.
9. Proceed to “Access the Maintenance User Interface (MUI)” below.
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Airbus Iridium SATCOM System
3. Access the Maintenance User Interface (MUI)
1. With system power on, connect an Ethernet cable to the Maintenance Port via the front
panel access door of the SDU.
2. Connect the other end of the cable to a laptop with a web browser (Mozilla FireFox® is
recommended).
3. Confirm that the green link light is illuminated. The light can be steady or flashing – flashing
means that data is being transmitted.
4. Set the laptop network adapter to the following:
IP = 192.168.128.10
Subnet Mask =255.255.255.0
Note: The Maintenance port can auto‐negotiate the best speed (10/100) and mode (full/half duplex).
5. Open the laptop’s web browser and clear the cache.
6. In the Address bar, type the following default IP address: 192.168.128.1. The Airbus Iridium
SATCOM System Home page will display with the General tab information displayed.
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Airbus Iridium SATCOM System
1 ‐ Login area
2 ‐ Menu of available links to pages accessible to various users upon login
3 ‐ Tabs: GENERAL, ARINC, and DISCRETE IN
4 ‐ System and Link status display area
5 ‐ System information data display area
6 ‐ Mode: OPERATIONAL, MAINTENANCE, INITIALIZING, etc.
7. Proceed to “Access Maintenance Mode” below.
4. Access Maintenance Mode – On Ground Status Required
1. You are now connected to the Airbus Iridium SATCOM System MUI Home Page; type the
following in the Login fields:
Default User Name: AFIRSMAINT
Default Password: 228MAINT
2. Click Login.
3. Click Enter Maintenance Mode. A message displays, prompting for confirmation to enter
Maintenance Mode.
4. Click OK. The MUI – Maintenance Home Page will display.
5. Modify Owner Requirements Table (ORT) Parameters
1. You are logged into the MUI as a Maintenance User from the previous process. You will now
be able to customize parameters for the individual aircraft operator based on operational
requirements or preferences.
2. Click Enter Maintenance Mode. A confirmation message displays.
3. Click OK.
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Airbus Iridium SATCOM System
4. Click the ORT link on the left side of the screen to open the ORT page. The Owner
Requirements Table will display.
Field
Call Progress Tones
Extension 1
Low Priority Calls
Additional ACARS
Header
Air Traffic Service (ATS)
Available Options
North American
European
Yes – Calls from cockpit can be placed manually
No – Calls from cockpit can only be placed from address book
Yes – Low priority calls can be received/made from cockpit
No – Low priority calls cannot be received/made from cockpit
None – SITA Service
ARINC – ARINC Service
Yes – SIM card with ATS
No – SIM card without ATS
6. Create an Address Book
1.
2.
3.
4.
Click Downloads from the left menu.
Choose the Address Book option.
Click Download.
Choose the Save File option.
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Airbus Iridium SATCOM System
5. Click OK.
An Address Book template will download to the computer as a comma‐separated‐values file
(adb.csv). If the computer does not have Microsoft Excel®, the file can be opened as a
Microsoft WordPad® file.
Example of Microsoft Excel® Address Book file.
Example of Microsoft WordPad® Address Book file.
6. Locate and open the adb.csv file.
7. Add entries to the address book (up to 300) and modify as necessary.
There are no list numbers in the adb.csv file to identify individual entries.
Important: The template (adb.csv) entries must adhere to the parameters exactly.
Phone Number
Name
Priority
Use only ATS‐
enabled Iridium
SIM cards.
Protected
Directory
Speed Dial 1
Speed Dial 2
Speed Dial 3
Address Book Parameters
Up to 18 digits (Always include country code)
Up to 23 upper‐case alpha‐numeric characters (A‐Z, 0‐9, +, ‐, /, space)
4 – Public
3 – Non‐Safety
2 – Safety
1 – Emergency
0 – No
1 – Yes
4 – Public
3 – Non‐Safety
2 – Safety
1 – Emergency
0 (not currently used)
0 (not currently used)
8. When finished modifying the Address Book, save and close the file.
Important: The filename must remain adb.csv or the file will not load.
9. Click Upgrades from the left menu.
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Airbus Iridium SATCOM System
10. Click Browse and locate the adb.csv file that you just created.
11. Click Upload.
12. Click Apply.
13. Click Exit Maintenance Mode when updates are complete. A message displays, prompting
for confirmation to exit Maintenance Mode.
14. Click OK. The system saves changes, reboots, and returns to Operational Mode.
15. Proceed to “Enter Administrator Role” below.
7. Enter Administrator Role ‐ On‐Ground Status Required
1. You are still connected to the Airbus Iridium SATCOM System MUI Home Page; type the
following in the Login fields:
Default User Name: AFIRSADMIN
Default Password: ADMIN228
2. Click Login.
3. Click Enter Maintenance Mode.
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Airbus Iridium SATCOM System
8. Update User Access Table (UAT) Parameters
The User Access Table (UAT) is used to set up user access privileges for up to 20 users. These
settings may be changed as needed to meet operational requirements.
1. Click the UAT (Security) link on the left side of the screen to open the UAT page.
2. Add security roles as necessary based on the following parameters.
Field
User Name
Password
Security Level
Parameter
4 ‐ 20 upper‐case alpha‐numeric characters
4 ‐ 20 upper‐case alpha‐numeric characters
Data Collector (default)
Maintenance
Administrator
Privileges
Roles
Guest
(no login required)
Data Collector
Maintenance
Administrator
ORT
Parameters
Modifications
UAT
(User
Address Access
Book
Table)
S/W
Upgrades
Software/Data Loading (Upload)
UAT
ADB
(User
ORT
(Address Access
ICT
(Complete) Book)
Table)
No
No
Yes
No
No
No
No
No
No
No
Yes
Yes
No
No
Yes
Yes
No
No
No
Yes
No
No
Yes
Yes
No
No
Yes
Yes
Note: All users can download fault logs, except Guest.
3. When finished, click Exit Maintenance Mode for the system to reboot and save changes.
4. Proceed to “Section 3 ‐ Testing” or “Download Backup UAT File (Optional)” below.
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No
No
Yes
Yes
Airbus Iridium SATCOM System
a. Download Backup UAT File (Optional)
You may want to download a backup UAT file that you could upload in the event that
the system file should fail.
1. On the Home Page, type the following in the Login fields:
Default User Name: AFIRSADMIN
Default Password: ADMIN228
2. Click Login.
3. Click Downloads.
4. Select the UAT option from the Configurations section.
5. Click Download.
6. Choose Save.
7. Click OK.
8. Proceed to “Section 3 ‐ Testing” below.
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Airbus Iridium SATCOM System
SECTION 3 – TESTING
1. Test System Voice Connectivity
Perform the following steps to ensure that the system is working properly. If you do not have
voice transmission available, proceed to Test System Data Connectivity. For information on
Built‐in Tests and Fault Indicators, see the Installation and Operations Manual.
a. Call from Landline Phone to Iridium SATCOM Phone
NON‐ATS (Air Traffic Service) SIM
1. Call Iridium Call Service
U.S.
1‐480‐768‐2500
Non‐U.S.
001‐480‐768‐2500
2. Enter Iridium 12 digit phone number and follow with the # symbol.
ATS (Air Traffic Service) SIM
1. Call Iridium Call Service
U.S.
1‐480‐730‐3900
Non‐U.S.
001‐480‐730‐3900
2. Enter Iridium 12 digit phone number and follow with the # symbol.
3. Enter the following information when prompted and follow each entry with the
# symbol. This information is provided by SIM card provider.
User ID
PIN
Priority level
o Emergency
o Safety
o Non‐Safety
o Public
Plane ID
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Airbus Iridium SATCOM System
b. Call from Iridium SATCOM Phone to Landline Phone (Manual)
1. Select Manual Dial from the MCDU screen.
2. Punch in the phone number and select the button directly next to the open field
to populate the field.
3. Choose a priority by using the Page Up and Page Down buttons.
4. Choose Pre‐Select.
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Airbus Iridium SATCOM System
5. The system is ready to connect the call.
6. Initiate the call.
c. Call from Iridium SATCOM Phone to Landline Phone
(Directory)
IMPORTANT: If manual dialing has been disabled, the ability to use dual‐tone multi‐
frequency signaling (DTMF) will also be disabled. This means that you will not be able to
punch in an extension number after reaching a switchboard via Directory dialing.
1. Select Directory from the MCDU screen.
2. Choose a directory.
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Airbus Iridium SATCOM System
3. Locate the number to call.
4. Initiate the call.
2. Send Data Message from Iridium SATCOM
1. Go to the MCDU.
2. Choose a free text and send a test message to Dispatch or Maintenance. The system
will automatically queue and send the message. Optionally, you can have the
message receiver send you a message back.
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Iridium Status Indicator Summary
Note: LED indicators require power to the Iridium SATCOM system. Every indicator will be off if no power is applied.
Indicator Color
Status
Indicator Name
OFF
GREEN
YELLOW
RED
System
Never Off
Operational Mode
No Failure/Fault
Initialization Mode or
Maintenance Mode or
Fault/Event
Critical Failure
ISVM Link
Never Off
Operational Mode
No Failure/Fault
Fault/Event
Never Red
ISDM Link
Never Off
Operational Mode
No Failure/Fault
Fault/Event
Never Red
GPS Link
Internal GPS Active
Parameter Set to Inactive
Operational Mode
No Failure/Fault
Fault/Event
Never Red
Not Used or Fault
Steady = Link OK
Flashing = Data Being Transmitted
Never Yellow
Never Red
Ethernet Link
(for each port)
L‐3 Aviation Recorders Proprietary
L-3 Iridium SATCOM System - Built-in Test and Fault Indicators
DATA CHECKS
Indicator Description
LED Off
Operational,
No Failure/Fault
Fault Light
Discrete Output
Fault Name
BIT Check
Configuration
CONFIG FAIL
Table Failure
Raise Fault/Failure Condition
The “Configuration Table Failure”
will be raised if the system is
unable to read or write the
Configuration Data stored in the
memory
The “SCM Compatibility Fault” will
be raised if the SDU software load
is not compatible with the valid
Configuration Data stored in the
SC
Clear Fault/Failure
Condition
ON
OFF
Fault/Event
Critical Failure
Front Panel LEDs
System
ISVM
ISDM
MCDU Indicators
GPS
Comment
Operable
SDU
SCM
The “Configuration Table
Failure” cannot be cleared
once raised.
No
N/A
N/A
Critical Error. Verify ICT and
ORT files in MUI. If files are
valid for A/C, replace SDU.
The “SCM Compatibility
Fault” cannot be cleared
once raised.
No
N/A
N/A
Transition to Configuration
Invalid State. Verify
software load in MUI.
CONFIG
FAULT
SCM
Compatibility
Fault
NVM FAIL
NR-NVM
Failure
The “NR-NVM Failure” will be
raised if missing or not detected,
does not initialize or is judged to be
defective.
The “NR-NVM Failure”
cannot be cleared once
raised.
Yes
FAIL
OK
Internal memory failure.
FLASH CARD
FAULT
Flash card
status
Flash card removed or can not be
read
Flash card inserted and can
be read.
Yes
FAIL
OK
Verify flash card is inserted
and can be read.
L‐3 Aviation Recorders Proprietary
L-3 Iridium SATCOM System - Built-in Test and Fault Indicators
POWER CHECKS
Indicator Description
LED Off
Operational,
No Failure/Fault
Fault Light
Discrete Output
Fault Name
LOW VOLTS
BIT Check
Raise Fault/Failure Condition
ON
OFF
Critical Failure
Front Panel LEDs
SCM
The “Low Voltage Status” will be The “Low Voltage Status” will be
Low Voltage
raised if the system enters the Low cleared if the system exits the
Status
Input Voltage state.
Low Input Voltage state.
Yes
OK
OK
Check input voltage if
persistent.
The “Alternate Power Status”
will be cleared if the voltage at
the Alternate Input is within an
inclusive range of 18.0 V to 32.2
V.
Yes
OK
OK
Check input voltage.
The “Power Loss Status” will be
cleared if the system exits the
Power Failure state.
No
FAIL
No
Check input voltage.
Alternate
Power Status
POWER LOSS
Power Loss
Check
The “Power Loss Status” will be
raised if the system enters the
Power Failure state.
ISVM
L‐3 Aviation Recorders Proprietary
ISDM
GPS
Comment
SDU
ALTERNATE
POWER
System
MCDU Indicators
Operable
The “Alternate Power Status” will
be raised if the voltage at the
Alternate Input is below 18.0 V or
above 32.2 V.
Clear Fault/Failure Condition
Fault/Event
L-3 Iridium SATCOM System - Built-in Test and Fault Indicators
TEMPERATURE CHECKS
Indicator Description
LED Off
Operational,
No Failure/Fault
Fault Light
Discrete Output
Fault Name
BIT Check
CONFIG FAIL
Temperature
Sensor Fault
CONFIG
FAULT
System Low
Temperature
Status
NVM FAIL
Raise Fault/Failure Condition
Clear Fault/Failure
Condition
ON
OFF
Fault/Event
Critical Failure
Front Panel LEDs
System
ISVM
A “Temperature Sensor Fault” will be
The “Temperature Sensor
raised if one or more of the temperature Fault” will be cleared if all of
sensors are considered unreasonable.
the temperature sensors
report a reasonable
temperature
The “System Low Temperature Status”
The “System Low
will be raised if the system enters the Temperature Status” will be
System Low Temperature state.
cleared if the system exits
the System Low
ISVM Elevated The “System
System High Temperature Status”
Status
The “System
System High
Temperature
will be raised if the system enters the Temperature Status” will be
Status, or ISVM
System High Temperature state.
cleared if the system exits
High
the System High
Temperature
Temperature state.
Status, or System
High
L‐3 Aviation Recorders Proprietary
ISDM
MCDU Indicators
GPS
Comment
Operable
SDU
SCM
Yes
OK
OK
Yes
OK
OK
Temperature is
below -15 C.
Yes
OK
OK
Temperature is
above 70 C.
L-3 Iridium SATCOM System - Built-in Test and Fault Indicators
INTERNAL CHECKS
Indicator Description
LED Off
Operational,
No Failure/Fault
Fault Light
Discrete Output
Fault Name
ISVM DPL
FAIL
ISVM AT FAIL
ISDM FAIL
SIM CARD
FAIL
GPS FAIL
BIT Check
Raise Fault/Failure Condition
Clear Fault/Failure
Condition
ON
OFF
Fault/Event
Critical Failure
Front Panel LEDs
System
ISVM
The “ISVM Voice
The Iridium Satellite Voice Modem
ISVM Voice
Communication Failure”
(ISVM) failure will be raised if the
Communication
ISVM driver reports no communication will be cleared if the ISVM
Failure
driver reports
with the ISVM DPL port after three
communication with the
retry attempts.
ISVM.
ISDM
MCDU Indicators
GPS
Operable
Yes
SDU
FAIL
SCM
OK
Comment
Voice communications not
available. Link should
reestablish within a few
minutes. If link does not
reestablish within 20 minute
period, replace SDU.
Non-Safety Services Data
Communications inoperable.
Link
Li k should
h ld reestablish
t bli h
within a few minutes. If link
does not reestablish within
20 minute period, replace
SDU.
Safety Services Data
Communications inoperable.
Link should reestablish
within a few minutes. If link
does not reestablish within
20 minute period, replace
SDU.
ISVM Data
The “ISVM Data Communication
The “ISVM Data
Communication Failure” will be raised if the Iridium All Communication Failure”
Failure
F il
Off Mode
M d iis not Active
A i and
d the
h ISVM will
ill bbe cleared
d if the
h ISVM
driver reports
driver reports no communication with
communication with the
the ISVM AT port after three retry
ISVM AT port.
attempts.
Yes
FAIL
OK
The “ISDM Voice
ISDM
The Iridium Satellite Data Modem
Communication Failure”
Communication
(ISDM) failure will be raised if the
Failure
ISDM driver reports no communication will be cleared if the ISDM
driver reports
with the ISDM DPL port after three
communication with the
retry attempts.
ISDM.
Yes
FAIL
OK
The “SIM Communication Failure” will The “SIM Communication
SIM
Communication be raised if the system fails to read or Failure” will be cleared if
the system successfully
write to the SIM card.
Failure
reads and writes to the SIM
card.
Yes
OK
FAIL
Voice Communications not
available. Verify SIM card is
installed and SCM is
operational.
OK
GPS not available, Link
should reestablish within a
few minutes. If link does not
reestablish within 20 minute
period, replace SDU. If still
present verify Iridium/GPS
antenna and cable
cable.
The “GPS Communication Failure” will The “GPS Communication
GPS
Communication be raised if the GPS Receiver reports no Failure” will be cleared if
Fail
communication with the GPS after three the GPS Receiver reports
communication with the
retry attempts.
GPS.
Yes
L‐3 Aviation Recorders Proprietary
FAIL
L-3 Iridium SATCOM System - Built-in Test and Fault Indicators
EXTERNAL CHECKS
Indicator Description
LED Off
Operational,
No Failure/Fault
Fault Light
Discrete Output
Fault Name
A717
INACTIVE
BIT Check
Raise Fault/Failure Condition
Clear Fault/Failure
Condition
ON
OFF
System
ISVM
An “ARINC 429 Receiver Port
A raised “ARINC 429
A429 RXnn
ARINC 429
Inactive Fault” will be raised if an Receiver Port Inactive Fault”
INACT (nn = Receiver Port ARINC 429 Receiver Port that is will be cleared if a recognized
Port Number) Inactive Fault configured as Generic 429 has not
label with correct parity is
The “ACARS
ACARS 1 Receiver Port
A raised “ACARS
ACARS
1 Receiver
Inactive Fault” will be raised if an
ARINC 429 Receiver Port
configured as ACARS 1 has not
received a recognized label with
correct parity for 4 seconds in a
The “ACARS 2 Receiver Port
Inactive Fault” will be raised if an
ARINC 429 Receiver Port
configured as ACARS 2 has not
received a recognized label with
ACARS 1
Receiver Port
Inactive Fault
ACARS2 RX
INACT
ACARS 2
Receiver Port
Inactive Fault
MCDU1 RX
INACT
The “MCDU 1 Receiver Port
Inactive Fault” will be raised if an
MCDU 1
ARINC 429 Receiver Port
Receiver Port configured as ARINC 739 MCDU 1
Inactive Fault has not received a recognized label
with correct parity for 4 seconds in
a row.
MCDU2 RX
INACT
The “MCDU 2 Receiver Port
Inactive Fault” will be raised if an
ARINC 429 Receiver Port
MCDU 2
Receiver Port configured as ARINC 739 MCDU 1
Inactive Fault has not received a recognized label
with correct parity for 4 seconds in
a row.
Critical Failure
Front Panel LEDs
ARINC
The “ARINC 573/717 Receiver fault
The ARINC 573/717
573/717
will be raised if the ARINC 573/717 Receiver Fault will be cleared
Receiver
is configured Active data and the
if ARINC 573/717 data
Inactive Fault
data is not present.
resumes.
ACARS1 RX
INACT
Fault/Event
Port Inactive Fault” will be
cleared if a recognized label
with correct parity is received
for 4 seconds in a row over
the port for which the
A raised “ACARS 2 Receiver
Port Inactive Fault” will be
cleared if a recognized label
with correct parity is received
for 4 seconds in a row over
A raised “MCDU 1 Receiver
Port Inactive Fault” will be
cleared if a recognized label
with correct parity is received
for 4 seconds in a row over
the port for which the “MCDU
1 Receiver Port Inactive
Fault” was raised.
A raised “MCDU 2 Receiver
Port Inactive Fault” will be
cleared if a recognized label
with correct parity is received
for 4 seconds in a row over
the port for which the “MCDU
1 Receiver Port Inactive
Fault” was raised.
L‐3 Aviation Recorders Proprietary
ISDM
MCDU Indicators
GPS
Comment
Operable
SDU
SCM
Yes
OK
OK
Verify ARINC 573/717
data.
Yes
OK
OK
Verify ARINC 429 data on
indicated receiver port.
Yes
OK
OK
Verify ACARS 1 receiver
data.
Yes
OK
OK
Verify ACARS 2 receiver
data.
No
(MCDU
1)
OK
OK
Display on MCDU 1
inoperable. Check MCDU
1.
No
(MCDU
2)
OK
OK
Display on MCDU 2
inoperable. Check MCDU
2.
L-3 Iridium SATCOM System - Built-in Test and Fault Indicators
EXTERNAL CHECKS
Indicator Description
LED Off
Operational,
No Failure/Fault
Fault Light
Discrete Output
Fault Name
BIT Check
Raise Fault/Failure Condition
Clear Fault/Failure
Condition
A717
INACTIVE
ARINC
The “ARINC 573/717 Receiver fault
The ARINC 573/717
573/717
will be raised if the ARINC 573/717 Receiver Fault will be cleared
Receiver
is configured Active data and the
if ARINC 573/717 data
Inactive Fault
data is not present.
resumes.
MCDU3 RX
INACT
The “MCDU 3 Receiver Port
Inactive Fault” will be raised if an
MCDU 3
ARINC 429 Receiver Port
Receiver Port configured as ARINC 739 MCDU 1
Inactive Fault has not received a recognized label
with correct parity for 4 seconds in
a row.
A429 TXn FAIL
(n = Port
Number)
ARINC 429
Transmitter
Port
Loopback
Failure
An “ARINC 429 Transmitter Port
Loopback Failure” will be raised if
an active ARINC 429 Transmitter
Port is configured as a GP Bus or
CFDS and the loopback from the
port is not detected.
ACARS TX
FAIL
ACARS
Transmitter
Port
Loopback
Failure
The “ACARS Transmitter Port
Loopback Failure” will be raised if
an ARINC 429 Transmitter Port is
configured as ACARS and the
loopback from the port is not
detected.
ACARS Loop
ACARS FAULT
Test Fault
ON
OFF
Fault/Event
Critical Failure
Front Panel LEDs
System
ISVM
A raised “MCDU 3 Receiver
Port Inactive Fault” will be
cleared if a recognized label
with correct parity is received
for 4 seconds in a row over
the port for which the “MCDU
1 Receiver Port Inactive
Fault” was raised
A raised “ARINC 429
Transmitter Port Loopback
Failure” will be cleared if the
loopback is detected from the
port for which the “ARINC
429 Transmitter Port
Loopback Fault” was raised.
A raised “ACARS Transmitter
Port Loopback Failure” will
be cleared if the loopback is
detected from the port for
which the “ACARS
Transmitter Port Loopback
Failure” was raised.
The “ACARS Loop Test Fault” will
be raised if an ACARS Loop Test
does not pass on at least one
ACARS system.
L‐3 Aviation Recorders Proprietary
ISDM
MCDU Indicators
GPS
Comment
Operable
SDU
SCM
Yes
OK
OK
Verify ARINC 573/717
data.
No
(MCDU
3)
OK
OK
Display on MCDU 3
inoperable.
Yes
FAIL
OK
Verify ARINC 429 data on
indicated transmitter port.
Yes
FAIL
OK
Verify ACARS transmitter
port.
Yes
OK
OK
Verify ACARS system.
L-3 Iridium SATCOM System - Built-in Test and Fault Indicators
EXTERNAL CHECKS
Indicator Description
LED Off
Operational,
No Failure/Fault
Fault Light
Discrete Output
Fault Name
A717
INACTIVE
MCDU TX FAIL
BIT Check
Raise Fault/Failure Condition
Clear Fault/Failure
Condition
ON
OFF
Critical Failure
Front Panel LEDs
SCM
ARINC
The “ARINC 573/717 Receiver fault
The ARINC 573/717
573/717
will be raised if the ARINC 573/717 Receiver Fault will be cleared
Receiver
is configured Active data and the
if ARINC 573/717 data
Inactive Fault
data is not present.
resumes.
Yes
OK
OK
Verify ARINC 573/717
data.
A raised “MCDU Transmitter
Port Loopback Failure” will
be cleared if the loopback is
detected from the port for
which the “MCDU
MCDU
Transmitter Port Loopback
Failure” was raised.
No
FAIL
OK
Verify MCDU system.
A raised “RS-232/422
A “RS-232/422 Receive Fault” will
Receiver Fault” will be
be raised for any active RScleared if the data is received
232/422 Serial Port for which a
without error over the port for
received data error is reported.
which the fault was raised.
Yes
OK
OK
Verify received serial data
on indicated port.
Yes
FAIL
OK
Verify serial data on
indicated port.
Yes
FAIL
OK
Verify discrete output on
indicated port.
OK
Verify indicated Ethernet
port. Access to MUI may
be impacted, may need to
access MUI through
another Ethernet port.
The “MCDU Transmitter Port
Loopback Failure” will be raised if
an ARINC 429 Transmitter Port is
configured as ARINC 739 MCDU
d the
h lloopback
b k ffrom the
h port iis
and
not detected.
The “RS-232/422 Transmission
RS-232/422
SERIALn FAIL
Loopback Failure” will be raised for
Transmission
(n = Port
any Active RS-232 Serial Port
Loopback
Number)
whose loopback is not detected
Failure
after three loopback attempts.
ISVM
The “RS-232/422
Transmission Loopback
Failure” cannot be cleared
once raised.
The “Discrete Output Failure”
A “Discrete Output Failure” will be
will be cleared if the expected
DOUTn FAIL (n
Discrete
raised for any Discrete Output Port
voltage is output from the
= Port Number) Output Failure that is Active and does not output
port for which the fault was
the expected voltage.
raised.
The “Ethernet Link Fault” will be The “Ethernet Link Fault” will
Ethernet Link
raised if Ethernet is Monitored and
be cleared if Ethernet is
Fault
there is no link.
Monitored and there is a link.
ISDM
GPS
Comment
SDU
MCDU
Transmitter
Port
Loopback
Failure
System
MCDU Indicators
Operable
SERIALn
RS-232/422
FAULT (n =
Receive Fault
Port Number)
ETHERNETn
FAULT (n =
Port Number)
Fault/Event
Yes
L‐3 Aviation Recorders Proprietary
OK
L-3 Iridium SATCOM System - Built-in Test and Fault Indicators
EXTERNAL CHECKS
Indicator Description
LED Off
Operational,
No Failure/Fault
Fault Light
Discrete Output
Fault Name
A717
INACTIVE
BIT Check
Raise Fault/Failure Condition
Clear Fault/Failure
Condition
ON
OFF
NO GPS LINK
GPS Link
Status
NO ISVM LINK
ISVM Link
Status
The “ISVM Link Status” will
The “ISVM Link Status” will be
be cleared if the ISVM driver
raised if the ISVM driver reports no
reports a link for 5 seconds in
link.
a row.
Critical Failure
Front Panel LEDs
System
ISVM
ARINC
The “ARINC 573/717 Receiver fault
The ARINC 573/717
573/717
will be raised if the ARINC 573/717 Receiver Fault will be cleared
Receiver
is configured Active data and the
if ARINC 573/717 data
Inactive Fault
data is not present.
resumes.
The “GPS Link Status” will be
The “GPS Link Status” will be
raised if the internal GPS is
cleared if the GPS Receiver
configured as Active and the GPS
reports a navigation solution
t no navigation
i ti
Receiver
reports
for 5 seconds in a row.
solution for 5 seconds in a row.
Fault/Event
ISDM
MCDU Indicators
GPS
SDU
SCM
Yes
OK
OK
Verify ARINC 573/717
data.
OK
GPS not available, Link
should reestablish within a
few minutes. If link does
not reestablish within 20
minute period, replace
SDU. If still present verify
Iridium/GPS antenna and
cable.
OK
Voice communications not
available. Link should
reestablish within a few
minutes.
Yes
Yes
The “ISDM Link Status” will
The “ISDM Link Status” will be
be cleared if the ISDM driver
NO ISDM LINK
raised if the ISDM driver reports no
reports a link for 5 seconds in
link.
a row.
The “DTP Source Status” will
The “DTP Source Status” will be
be cleared if at least one of
Date, Time,
raised if DTP 1 interface, DTP 2
NO DTP
DTP 1 interface, DTP 2
Position
interface, DTP 3 interface, and
SOURCE
interface, DTP 3 interface, or
Source Status internal GPS are all not providing
internal GPS is providing
valid data.
valid data.
ISDM Link
Status
L‐3 Aviation Recorders Proprietary
Comment
Operable
OK
OK
Yes
OK
OK
Data communications not
available. Link should
reestablish within a few
minutes.
Yes
OK
OK
Verify DTP source.
Iridium SIM Card Registration
The Iridium network is based on the international Global System for Mobile
communications (GSM) standard and architecture. With any GSM cellular device, all Iridium
transceivers capable of voice require a Subscriber Identity Module (SIM) associated with the
mobile device. Though the SIM can be used for many functions, such as restricting call access or
to store information, its primary function is to assign the telephone number to the L-3 Satellite
Data Unit (SDU) transceiver. An exception is the Iridium Short Burst Data (SBD) modem, which
operates solely from an IMEI number assigned to each modem.
Often customers or installers are not familiar with the need to activate the SIM and IMEI
for service over the Iridium network prior to testing or use of the system. You may select any
valid Iridium Service provider. Our recommendation is to contact our partner, FLYHT Aerospace
Solutions Ltd., complete the following activation form, and send to FLYHT for processing.
There are two types of voice service plans to choose from:
• Air Traffic Service (ATS)
The operator will be able to prioritize calls to and from the cockpit and pre-empt
a lower priority call with a higher priority incoming call. The calls from ground-toair have additional security procedures; the user will be required to have a User
ID, PIN, plane ID, and set the call priority.
• Non-ATS
This service does not have call prioritization and the ground-to-air calls only
require the phone number of the SIM card to place a call.
You may need the following information when activating a SIM card:
•
•
•
Tail Number
Avionics MFR – L-3/FLYHT
Avionics Model - AFIRS 228S Satellite Data Unit
•
•
•
•
IMEI Voice Modem Number
IMEI Data Modem Number
Voice Modem Model 9523
Data Modem Model 9602
Congratulations on purchasing the FLYHT AFIRSTM 228S system.
In order to complete the activation of the voice and data services we require some additional
information.
Please review the following voice and data service options and email the completed form to us
at 228S Voice/Data Services@FLYHT.com. A FLYHT Service and Support Manager will contact
you to complete the activation process and to provide you with the assigned satcom phone
number.
1. Aircraft Information:
Model:
Serial Number:
Registration:
2. AFIRS 228 Information:
SDU Serial
Number:
SCM Serial
Number
3. Please select one of the following satcom voice service plan options:
Rate
Billing Intervals
Air to Ground
$1.45/min USD
20 seconds
Ground to Air
$1.45/min USD
20 seconds
Circuit Switch Data for EFB
$1.45/min USD
20 seconds
AFIRS Global Voice/Data Plan – NON ATS
Note 1: Calls to other SATCOM service providers will be charged at a rate of $8.50/min
Note 2: Minimum monthly fee of $50 will apply to all accounts
Rate
Billing Intervals
Air to Ground
$1.45/min USD
20 seconds
Ground to Air
$1.75/min USD
20 seconds
Circuit Switch Data for EFB
$1.45/min USD
20 seconds
AFIRS Global Voice/Data Plan – ATS
Note: Calls to other SATCOM service providers will be charged at a rate of $8.50/min
Note 2: Minimum monthly fee of $50 will apply to all accounts
4. Please indicate your ACARS satcom data service provider:
ARINC
SITA
Please note you will require a separate agreement with your selected ACARS satcom data
service provider.
5. Contact information:
Primary contact*
Billing Contact (if different)
Company
Name
Address:
email :
Phone:
*The satcom voice phone number will be provided to this contact upon activation.
Terms and Conditions
TERMS OF PAYMENT
Payment net thirty (30) days from date of invoice or as otherwise specified by Seller. Buyer
agrees to pay the entire net amount of each invoice from Seller pursuant to the terms of each
such invoice without offset or deduction. Orders are subject to credit approval by Seller, which
may in its sole discretion at any time change the terms of buyer’s credit, require payment in
cash, bank wire transfer or by official check and/or require payment of any or all amounts due
or to become due for Buyer’s order before shipment of any or all of the products. If seller
believes in good faith that Buyer’s ability to make payments may be impaired or if Buyer shall
fail to pay any invoice when due, Seller may suspend the delivery of any order or any remaining
balance thereof until such payment is made or cancel any order or any remaining balance,
thereof, and buyer shall remain liable to pay for any products already shipped and all Non‐
Standard Products ordered by Buyer. Buyer agrees to submit such financial information from
time to time as may be reasonably requested by Seller for the establishment and/or
continuation of credit terms. Checks are accepted subject to collection and the date of the
collection shall be deemed the date of payment. Any check received from Buyer may be applied
by Seller against any obligation owing from Buyer to Seller, regardless of any statement
appearing in or referring to Buyer shall pay interest on any invoice not paid when due from the
due date to the date of payment at the rate of one and one‐half (1‐1/2%) percent per month or
such lower rate as may be maximum allowable by law. If Buyer fails to make payment when due
Seller may pursue any legal or equitable remedies, in which event Seller shall be entitled to
reimbursement for costs of collection and reasonable attorneys fees.
PRIVACY POLICY
FLYHT Aerospace Solutions Ltd. (FLYHT) uses the information collected to fulfill your requests for
services and to facilitate billing. FLYHT will send personally identifiable information about you
and/or your company to other companies or people when: we need to share your information
to provide the service you have requested, we need to send the information to companies who
work on behalf of FLYHT to provide service to you (unless we tell you differently these
companies do not have any right to use the personally identifiable information we provide them
beyond what is necessary to assist us). Personally identifiable consumer information is shared
with third parties (such as banks and credit card processors) to the extent necessary for FLYHT
to collect payment for the services provided.
CUSTOMER AGREEMENT
As an individual or authorized representative of the company, I hereby certify that the
information provided on this form is true and correct. I authorize FLYHT Aerospace Solutions
Ltd. (FLYHT) to investigate financial references and all other relevant material. FLYHT has the
right to deny service to any account that is past due and also reserves the right to deny service
based upon information supplied. I understand that our company is responsible for all charges
and services up till the date our account is properly cancelled through FLYHT and the Iridium
network. I agree that FLYHT cannot be held liable for any claims due to unavailability, delay, or
interruption in satellite services. Such claims shall also extend to damage, expense, and loss of
life. I agree to the Terms of Payment and the Privacy Policy.
I have read and agree to the standard terms and conditions above. Signed this
Signature:
Print Name
Title
Company
Address:
email :
Phone:
day of
, 20
Installation Manual
Airbus Iridium SATCOM System
SDU L-3 part number 228E5733-00
SCM L-3 part number 418E5733-00
Publication Number: 165E5733-00
Issue: Rev. 02
21 January 2014
L-3 Aviation Recorders Proprietary
100 Cattlemen Road
Sarasota, FL 34232
EXPORT CONTROL STATEMENT IRIDIUM SATCOM
TECHNOLOGY / DATA:
“This Iridium SATCOM System Technical Data is being exported from
the United States in accordance with the Export Administration
Regulations (ECCN #7A994), No License Required (NLR). Diversion
contrary to U.S. law is prohibited. In accordance with U.S. Law (Title
15CFR Part 746 and Supplement No. 1 to Part 774; and Title 31CFR)
resale/re-export or transfer to certain designated countries is
prohibited without the prior written consent of the U.S. Department of
Commerce.”
HTSUS/Schedule B: 85439.09.000
This manual contains date sensitive information. To verify the latest
revision level of this manual, visit our document down-load site at
http://www.L3ar.net.
©Copyright 2013 by L-3 Communications.
All rights reserved. No part of this manual may be reproduced or
utilized in any form or by any means, electronic or mechanical,
including photocopying, recording, or by information storage and
retrieval system, without permission in writing.
Inquiries should be addressed to:
L-3 Communications,
Aviation Recorders Publications
Vendor Code: 06141 P. O. Box 3041
Sarasota, Florida 34230
Phone: (941) 371–0811;
FAX: (941) 377–5591
L-3 Aviation Recorders Proprietary
100 Cattlemen Road
Sarasota, FL 34232
Record of Revisions
Rev.
Issue Date
Description
00
01 November 2013
Initial issue.
All
CM
01
15 December 2013
Corrected SDU & SCM TopLevel Part Numbers.
All
CM/SC
02
21 January 2014
Corrected SDU & SCM TopLevel Part Numbers.
All
CP
L-3 Aviation Recorders Proprietary
100 Cattlemen Road
Sarasota, FL 34232
Pages
By
Airbus Iridium SATCOM System
Table of Contents
1. Introduction ............................................................................................................................. 9
1.1 Applicability..................................................................................................................... 9
1.2 Model Designation .......................................................................................................... 9
1.2.1 Airbus Iridium SATCOM System ....................................................................... 9
1.3 Part Numbers ................................................................................................................. 9
1.4 Reference Documents .................................................................................................... 9
1.5 Definitions of Acronyms and Terms .............................................................................. 12
2. Description and Operation .................................................................................................... 16
2.1 System Overview .......................................................................................................... 16
2.2 System Architecture ..................................................................................................... 16
2.3 External System Interfaces ........................................................................................... 17
3. Equipment Specifications ..................................................................................................... 20
3.1 Satellite Data Unit (SDU) .............................................................................................. 20
3.1.1 General ............................................................................................................ 21
3.1.2
Mechanical Specifications ............................................................................... 21
3.1.3
Environmental Specifications – Airbus Iridium SATCOM System ................... 22
3.2 SDU Configuration Module (SCM) ............................................................................... 22
3.2.1 General ............................................................................................................ 22
3.2.2
Mechanical Specifications ............................................................................... 23
3.2.3
Environmental Specifications........................................................................... 25
3.3 Airbus Iridium SATCOM System Satellite Antenna ...................................................... 25
3.4 Antenna Coaxial Cable ................................................................................................. 26
3.5 Interface Specifications ................................................................................................ 26
SDU Rear Connector (J1) ............................................................................................ 27
3.5.1
Power Input...................................................................................................... 29
3.5.2
Chassis Ground ............................................................................................... 29
3.5.3
ARINC 429 Digital Serial Bus Input ................................................................. 30
3.5.4
ARINC 429 Digital Serial Bus Output .............................................................. 30
3.5.5
Ethernet ........................................................................................................... 30
3.5.6
Discrete Inputs ................................................................................................. 30
3.5.6.1 Configurable Inputs.......................................................................................... 30
3.5.7
165E5733-00
Issue, Rev. 02
Discrete Outputs .............................................................................................. 31
L-3 Aviation Recorders Proprietary
21 January 2014
Page 4
Airbus Iridium SATCOM System
3.5.7.1 Configurable Outputs ....................................................................................... 31
3.5.8
Two-Wire Phone .............................................................................................. 31
3.5.9
Microphone Input ............................................................................................. 31
3.5.10 Iridium / GPS Antenna ..................................................................................... 32
3.6
3.7
3.8
3.9
3.10
SDU Maintenance Connector (J2) ................................................................................ 32
SDU Configuration Module (SCM) ............................................................................... 32
ARINC 429 Receiver Protocols .................................................................................... 32
ARINC 429 Receiver Activity Status ............................................................................. 34
ARINC 429 Transmitter Protocols ................................................................................ 34
3.10.1 From SDU to ATSU / FWC .............................................................................. 34
3.10.2 From SDU to MCDU ........................................................................................ 35
3.10.3 From SDU to Airbus CFDS .............................................................................. 35
4. Installation Considerations .................................................................................................... 36
4.1 Satellite Data Unit (SDU) .............................................................................................. 36
4.2 SDU Configuration Module (SCM) ............................................................................... 37
4.3 Iridium Antenna System ............................................................................................... 37
4.3.1 Antenna ........................................................................................................... 37
4.3.2
Antenna Mounting............................................................................................ 39
4.3.3
Coaxial Cable .................................................................................................. 39
5. SATCOM Installation Materials ............................................................................................. 41
5.1 Required Materials ....................................................................................................... 41
6. System Interface Wiring ........................................................................................................ 42
6.1 General ......................................................................................................................... 42
6.2 Primary Power, Antenna, and SCM .............................................................................. 42
6.3 ARINC 429 Interfaces ................................................................................................... 42
6.3.1 Receiver Protocols........................................................................................... 43
6.3.2
6.4
6.5
6.6
6.7
6.8
6.9
6.10
Transmitter Protocols....................................................................................... 43
MCDU ........................................................................................................................... 44
ACARS ATSU............................................................................................................... 45
CFDIU Interface............................................................................................................ 46
Date, Time and Position ............................................................................................... 46
RS-232/422 Databus .................................................................................................... 46
Ethernet ........................................................................................................................ 47
Discrete Inputs.............................................................................................................. 48
6.10.1 Landing Gear Control Interface Unit (LGCIU) Input ......................................... 48
6.10.2 Function Assignment ....................................................................................... 49
165E5733-00
Issue, Rev. 02
L-3 Aviation Recorders Proprietary
21 January 2014
Page 5
Airbus Iridium SATCOM System
6.11 Discrete Outputs ........................................................................................................... 50
6.12 SATCOM ...................................................................................................................... 50
6.12.1 Audio Integrating System................................................................................. 50
7. SATCOM System Configuration ........................................................................................... 52
7.1 Accessing the Maintenance User Interface (MUI) ........................................................ 53
7.1.1 Home Page Tab Descriptions .......................................................................... 54
7.1.2
Faults Page...................................................................................................... 55
7.1.3
Part Numbers Page ......................................................................................... 56
7.2 Entering Maintenance Mode ......................................................................................... 57
7.2.1 Maintenance Mode Menu Descriptions ........................................................... 60
7.3 Configuring the Airbus Iridium SATCOM System ......................................................... 65
7.3.1 Address Book .................................................................................................. 65
7.3.2
Owner Requirements Table (ORT) Parameters .............................................. 66
7.3.3
Installation Configuration Table (ICT) .............................................................. 68
7.3.4
User Access Table (UAT) Parameters ............................................................ 68
7.4 Upgrading Airubs Iridium SATCOM System Software.................................................. 70
7.4.1 Upgrade Materials ........................................................................................... 70
7.4.2
Upgrade Procedure ......................................................................................... 70
7.5 Exiting Maintenance Mode ........................................................................................... 73
8. Maintenance and Checkout .................................................................................................. 75
8.1 Post-Installation Checkout ............................................................................................ 75
8.1.1 Before Power-On Tests ................................................................................... 75
8.1.2
Aircraft Systems Interface Tests ...................................................................... 76
8.1.3
Operational System Tests ............................................................................... 77
8.1.4
EMI Tests......................................................................................................... 78
8.2 Instructions for Continued Airworthiness ...................................................................... 78
List of Figures
Figure 2-1 – Airbus Iridium SATCOM System Operational Concept .......................................... 16
Figure 2-2 – Airbus Iridium SATCOM System Block Diagram .................................................... 17
Figure 2-3 – Airbus Iridium SATCOM System External Interfaces ............................................. 18
Figure 3-1 – Airbus Iridium SATCOM System Satellite Data Unit (SDU) ................................... 20
Figure 3-2 – SDU Outline Drawing ............................................................................................. 21
Figure 3-3 – Airbus Iridium SATCOM System SDU Configuration Module (SCM) ..................... 22
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Figure 3-4 – SCM Outline Drawing ............................................................................................. 23
Figure 3-5 – SCM Oblique View ................................................................................................. 24
Figure 3-6 – SCM Connector View Showing Location of Pin 1 .................................................. 25
Figure 3-7 – Airbus Iridium SATCOM System Antenna.............................................................. 25
Figure 3-8 – Iridium Antenna Coaxial Cable and Connectors .................................................... 26
Figure 3-9 – SDU Connector Map .............................................................................................. 29
Figure 4-1 – 2MCU Mounting Tray ............................................................................................. 36
Figure 4-2 – Iridium Antenna, Outline and Dimensions .............................................................. 38
Figure 4-3 – Iridium Antenna, Gasket ......................................................................................... 39
Figure 4-4 – Iridium Antenna, Coaxial Cable .............................................................................. 40
Figure 6-1 – Primary Power, Antenna, and SCM Interface ........................................................ 42
Figure 6-2 – MCDU Interface...................................................................................................... 44
Figure 6-3 – ACARS ATSU Interface ......................................................................................... 45
Figure 6-4 – CFDIU Interface ..................................................................................................... 46
Figure 6-5 – Serial Port Interface................................................................................................ 47
Figure 6-6 – Ethernet Interface ................................................................................................... 48
Figure 6-7 – Discrete Input Interfaces ........................................................................................ 50
Figure 6-8 – Latched ACP Audio Interface ................................................................................. 51
Figure 7-1 – Maintenance Port Location..................................................................................... 52
Figure 7-2 – Home Page – General Tab .................................................................................... 54
Figure 7-3 – Faults Page (Fault Log Tab)................................................................................... 55
Figure 7-4 – Faults Page (Fault History Tab) ............................................................................. 55
Figure 7-5 – Part Numbers Page (Software Tab) ....................................................................... 56
Figure 7-6 – Part Numbers Page (Hardware Tab)...................................................................... 56
Figure 7-7 – Entering Maintenance Mode Message ................................................................... 57
Figure 7-8 – Maintenance Mode Initial Display Screen .............................................................. 58
Figure 7-9 – Maintenance Mode Exit Screen ............................................................................. 59
Figure 7-10 – System Restart Screen ........................................................................................ 59
Figure 7-11 – Upgrades Screen ................................................................................................. 60
Figure 7-12 – Address Book ....................................................................................................... 66
Figure 7-13 – ORT Screen ......................................................................................................... 67
Figure 7-14 – UAT Page ............................................................................................................. 69
Figure 7-15 – Software Upgrade Progress ................................................................................. 71
Figure 7-16 – Software Loading Progress Screens .................................................................... 71
Figure 7-17 – Exit Maintenance Mode Message ........................................................................ 72
Figure 7-18 – Exit Maintenance Mode Progress Bar .................................................................. 72
Figure 7-19 – Exiting Prompt Message ...................................................................................... 73
Figure 7-20 – Restart Screen ..................................................................................................... 74
Figure 7-21 – Software Part Numbers Screen............................................................................ 74
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List of Tables
Table 1-1 – Part Numbers ............................................................................................................ 9
Table 1-2 – References ................................................................................................................ 9
Table 1-3 – Acronyms and Terms .............................................................................................. 12
Table 3-1 – J1A Top Plug (TP) Insert ......................................................................................... 27
Table 3-2 – J1B Middle Plug (MP) Insert .................................................................................... 28
Table 3-3 – J1C Bottom Plug (BP) Insert ................................................................................... 29
Table 3-4 – ARINC 429 Receiver Protocols – ATSU/FWC ........................................................ 32
Table 3-5 – ARINC 429 Receiver Protocols – CFDS ................................................................. 33
Table 3-6 – ARINC 429 Receiver Protocols – MCDU ................................................................ 33
Table 3-7 – ARINC 429 Receiver Port Monitoring ...................................................................... 34
Table 3-8 – ARINC 429 Transmitter Protocols SDU – ATSU/FWC ............................................ 34
Table 3-9 – ARINC 429 Transmitter Protocols SDU – MCDU .................................................... 35
Table 3-10 – ARINC 429 Transmitter Protocols SDU – FDS ..................................................... 35
Table 6-1 – Serial Port Pin Assignments .................................................................................... 46
Table 7-1 – Read Privileges by Role .......................................................................................... 62
Table 7-2 – Download Privileges by Role ................................................................................... 63
Table 7-3 – Modify Privileges by Role ........................................................................................ 64
Appendices
Appendix A – Wiring Diagram..................................................................................................... 79
Appendix B – ORT Worksheet.................................................................................................... 83
Appendix C – Environmental Qualification Forms ...................................................................... 85
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1.
INTRODUCTION
This section provides a general introduction to the Airbus Iridium SATCOM System and its applicable
standards and references.
1.1 Applicability
This Installation Manual provides the information necessary to plan the Airbus Iridium SATCOM
System installation and integration in the aircraft. It defines the mechanical and electrical interfaces for
each Line Replaceable Unit (LRU) and provides the procedures required to properly configure, test,
and maintain the Airbus Iridium SATCOM System. This manual is applicable to the following software
version(s):
Software Part Number: 840E5733-06
1.2 Model Designation
This manual covers model designation Airbus Iridium SATCOM System.
1.2.1 Airbus Iridium SATCOM System
The Airbus Iridium SATCOM System will be certified to TSO C-159a for voice and data safetyservices. It has a dual-channel Iridium link, one dedicated for safety-services data and the other
prioritized for safety-services voice.
1.3 Part Numbers
The following part numbers are defined for the LRUs of the Airbus Iridium SATCOM System.
Table 1-1 – Part Numbers
Part Number
Description
228E5733-00
Airbus Iridium SATCOM System Satellite Data Unit (SDU)
418E5733-00
Airbus Iridium SATCOM System SDU Configuration Module
(SCM)
1.4 Reference Documents
Table 1-2 – References
Ref.
Document Number Description
1.
ANSI/TIA/EIA-232F-1997
Interface Between Data Terminal Equipment and Data CircuitTerminating Equipment Employing Serial Binary Data Interchange
2.
ARINC 429-19
Mark 33 Digital Information Transfer System (DITS)
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Ref.
Document Number Description
3.
ARINC 573-7
Mark 2 Aircraft Integrated Data System (AIDS Mark 2)
4.
ARINC 600-16
Air Transport Avionics Equipment Interfaces
5.
ARINC 619-3
ACARS Protocols For Avionic End Systems
6.
ARINC 664-2
Aircraft Data Networks
7.
ARINC 702-6
Flight Management Computer System
8.
ARINC 702A-3
Advanced Flight Management Computer System
9.
ARINC 717-14
Flight Data Acquisition and Recording System
10. ARINC 718-4
Mark 3 Air Traffic Control Transponder (ATCRBS/MODE S)
11. ARINC 718A-2
Mark 4 Air Traffic Control Transponder (ATCRBS/MODE S)
12. ARINC 739A-1
Multi-Purpose Control And Display Unit
13. ARINC 741-13
Aviation Satellite Communication System
14. ARINC 758-2
Communications Management Unit (CMU) Mark 2
15. ARINC 761-4
Second Generation Aviation Satellite Communication System,
Aircraft Installation Provisions
16. FAA TSO C-159a
Technical Standard Order, Avionics Supporting Next Generation
Satellite Systems (NGSS)
17. GAMA Publication
No. 11, Ver. 5.1
ARINC 429, General Aviation Subset
18. IEEE 802.3-2008
IEEE Standard for Information Technology-Specific Requirements
- Part 3: Carrier Sense Multiple Access with Collision Detection
(CMSA/CD) Access Method and Physical Layer Specifications
19. RTCA/DO-160G
Environmental Conditions and Test Procedures for Airborne
Equipment
20. RTCA/DO-214
Audio Systems Characteristics and Minimum Operational
Performance Standards for Aircraft Audio Systems and
Equipment
21. RTCA/DO-262A
Minimum Operational Performance Standards for Avionics
Supporting Next Generation Satellite Systems (NGSS)
22. TIA/EIA-422-B
Electrical Characteristics of Balanced Voltage Digital Interface
Circuits
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Ref.
Document Number Description
23. ABD0100 Issue I
List of Affective ABD0100 Modules
24. ABD0100.0.0D
General
25. ABD0100.1.1E
General Technical Requirements Applicable to all Technical
Domains
26. ABD0100.1.2G
Environmental Conditions and Tests Requirements Associated to
Qualification
27. ABD0100.1.3E
Safety – Reliability - Requirements
28. ABD0100.1.4F
Maintainability Requirements
29. ABD0100.1.5F
Off – Aircraft Test and Testability Requirements
30. ABD0100.1.6D
Material Requirements
31. ABD0100.1.7E
Mechanical Requirements
32. ABD0100.1.8E
Electrical and Installation Requirements
33. ABD0100.1.9H
Electronic Equipment Design and Parts Requirements
34. ABD0100.1.10G
Software Requirements Related to Product
35. ABD0100.1.11C
Optical and Installation Requirements
36. ABD0100.1.12B
Conventional Instruments Requirements
37. ABD0100.1.13A
Cabin Requirements
38. ABD0100.1.14B
Obsolescence Management
39. ABD0100.1.15A
Supportability Engineering
40. ABD0100.1.16A
Equipment Functional Robustness
41. ABD0100.2.1C
Purchaser-Supplier Relations Requirements
42. ABD0100.2.2F
Supplier Organization Requirements
43. ABD0100.2.3E
Equipment General Design Assurance Process
44. ABD0100.2.4G
Software Design Assurance Process
45. ABD0100.2.5D
Hardware Design Assurance Process
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Ref.
Document Number Description
46. ABD0100.2.6B
Sub-Contracted Item Design Assurance
47. ABD0100.2.7G
Design Validation/Verification Process and Reviews
48. ABD0100.2.8F
Formal Qualification and Purchaser Acceptance Process
49. ABD0100.2.9G
Configuration Management Process
50. ABD0100.2.10A
Design Quality Assurance
51. ABD0100.2.11C
Electronic Hardware Design Assurance Process
52. ABD0100.3.0H
Documentation Requirements
53. ABD0012G
Supplies – Tool and Test Equipment
54. ABD0031F
Fire/Smoke/Toxicity
55. ABD0024E
Aircraft MFR – Tools and test equipment
56. ABD0046D
Units of Measurement
57. AP1013C
GRESS: General Requirements for Equipment and System
Supplier
1.5 Definitions of Acronyms and Terms
Table 1-3 – Acronyms and Terms
Acronym
Definition
ACARS
Aircraft Communications Addressing and Reporting System
ACP
Audio Control Panel
ADB
Address Book
AFIRS
Automated Flight Information Reporting System
ANSI
American National Standards Institute
APU
Auxiliary Power Unit
ATE
Automatic Test Equipment
ATS
Air Traffic Service
ATSU
Air Traffic Service Unit
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Acronym
Definition
ARINC
Aeronautical Radio Incorporated
AWG
American Wire Gauge
BCD
Binary Coded Decimal
BITE
Built-In Test Equipment
BOP
Bit Oriented Protocol
BP
Bottom Plug
BSP
Board Support Package
CF
Compact Flash
CFDS
Centralized Fault Display System (Airbus)
CNSSA
Core Non-Safety Services Application
CTS
Clear To Send
DITS
Digital Information Transfer System
DTP
Date Time Position
EFB
Electronic Flight Bag
EIA
Electronics Industry Association
ELA
Embedded Logic Application
FAA
Federal Aviation Administration
F/W
Firmware
FWC
Flight Warning Computer
GAMA
General Aviation Manufacturers Association
GFI
General Format Identifier
GPS
Global Positioning System
GSE
Ground Service Equipment
HBP
Harvard Bi-Phase
HYB
Hybrid
ICA
Instructions for Continued Airworthiness
ICAO
International Civil Aviation Organization
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Acronym
Definition
ICD
Interface Control Document
ICE
Iridium Certified Equipment
ICT
Installation Configuration Table
IEEE
Institute of Electrical and Electronics Engineers
IMEI
International Mobile Equipment Identifier
ISO
International Organization for Standardization
LGCIU
Landing Gear Control Interface Unit
LED
Light Emitting Diode
LRU
Line Replaceable Unit
LSK
Line Select Key
MCDU
Multi-Purpose Control and Display Unit
MOPS
Minimum Operational Performance Specifications
MP
Middle Plug
MUI
Maintenance User Interface
N/C
Normally Closed
NGSS
Next Generation Satellite Systems
N/O
Normally Open
ORT
Owner Requirements Table
PBX
Public Branch Exchange
PC
Personal Computer
P/N
Part Number
PSTN
Public Switched Telephone Network
PTT
Push To Talk
RMS
Root-Mean-Square
RTS
Request To Send
RTCA
Radio Technical Commission for Aeronautics
RX
Receive
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Acronym
Definition
SAL
System Address Label
SATCOM
Satellite Communications
SCM
SDU Configuration Module
SDI
Source/Destination Identifier
SDU
Satellite Data Unit
SIM
Subscriber Identity Module
SSA
Safety Service Application
SSM
Signed Status Matrix
SW
Software
TIA
Telecommunications Industry Association
TNC
Threaded Neill–Concelman
TP
Top Plug
TX
Transmit
TSO
Technical Standard Order
UAT
User Access Table
UTC
Coordinated Universal Time
VAC
Volts Alternating Current
VDC
Volts Direct Current
WPS
Words Per Second
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2.
DESCRIPTION AND OPERATION
This section describes the system operation and architecture.
2.1 System Overview
The Airbus Iridium SATCOM System provides multiple voice and data communications functions in
the aircraft. The Automated Flight Information Reporting System (AFIRS) provides a satellite voice
and data communications (SATCOM) link with the Public Switched Telephone Network (PSTN) via
the Iridium® satellite network. The system uses a standard ARINC 741/761 SATCOM interface to the
flight crew’s Audio Integrating System and ARINC 739A Multi-Purpose Control and Display Units
(MCDUs) in the cockpit, as well as providing 3-extension Public Branch Exchange (PBX) capability for
up to 2 handsets in the cabin.
Figure 2-1 – Airbus Iridium SATCOM System Operational Concept
The Airbus Iridium SATCOM System provides a dedicated safety-services data channel with the
capability to send and receive standard ACARS messages between the aircraft’s Air Traffic Service
Unit (ATSU) and a safety-services certified terrestrial service provider.
2.2 System Architecture
The Airbus Iridium SATCOM System consists of modular avionics components that can be tailored to
meet customer needs. The core system components are the Satellite Data Unit (SDU), the SDU
Configuration Module (SCM), and the Iridium Antenna (see Figure 2-2). Optional components include
Cabin Handset(s) (Wired or Cordless).
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Figure 2-2 – Airbus Iridium SATCOM System Block Diagram
2.3 External System Interfaces
The Airbus Iridium SATCOM System has a number of external interfaces, which are listed below and
described in detail in this section.
Audio System Interface (1)
ARINC 429 Transmitters (6) and Receivers (16)
RS-232/422 Serial Ports (4)
Ethernet Ports (4)
Discrete Outputs (8) and Inputs (16)
Iridium Antenna (1)
User Media Interfaces – SIM (1), CF (1)
Maintenance Interfaces – Ethernet (1)
Voice Modem – Iridium 9523
Data Modem – Iridium 9602
Figure 2-3 illustrates the interfaces that the Airbus Iridium SATCOM System provides to external
aircraft systems or to the user.
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Figure 2-3 – Airbus Iridium SATCOM System External Interfaces
Audio System Interface (1)
This interface consists of a Microphone Input to the SDU and an Interphone Output from the SDU
to connect to a standard (DO-214) Audio Integrating System (e.g. Audio Panel) in the aircraft.
Software selectable discrete inputs and outputs can be configured to support this interface (e.g.
Mic On, Chime, Chime Reset, End Call functions).
ARINC 429 Transmitters (6) and Receivers (16)
These interfaces can be software-configured to connect to various aircraft systems to support both
the display and control functions of the Airbus Iridium SATCOM System. Typical interfaced
systems include MCDUs, ACARS ATSUs, Airbus Centralized Fault Display Systems (CFDS), etc.
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RS-232/422 Serial Ports (4)
These interfaces can be software-configured to connect to different aircraft systems. Typical
interfaced systems include EFB, Global Positioning System (GPS), etc.
Ethernet Ports (4)
These interfaces can be used to connect to several different systems. Typical interfaced systems
include EFB, CFDS, etc. One of these ports can also be used to provide a remote maintenance
port interface (e.g. in the flight compartment).
Discrete Outputs (8) and Inputs (16)
Discrete inputs and outputs can be used to provide or supplement various flight crew control and
display interactions, particularly for voice functions. Discrete inputs can also be used to determine
the states of various aircraft systems when this information is not available on a databus (e.g.
Weight-on-Wheels, Doors Closed, etc.).
Iridium Antenna (1)
An antenna mounted on the top of the fuselage is used to communicate with both the Iridium
satellite network and the GPS satellite network.
User Media Interfaces – SIM (1), CF (1)
There are two types of media available for the user to insert or remove from the Airbus Iridium
SATCOM System. The SCM contains a user accessible Subscriber Identity Module (SIM) card
slot for storage of the Iridium communications management information. The SDU contains a
front panel accessible Compact Flash (CF).
Maintenance Interfaces – Ethernet (1)
An RJ45 jack on the front panel provides Maintenance Port access using an Ethernet connection.
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3.
EQUIPMENT SPECIFICATIONS
This section describes the mechanical and environmental specifications of the components of the
Airbus Iridium SATCOM System.
3.1 Satellite Data Unit (SDU)
This section describes the mechanical and environmental specifications of the components of the
Satellite Data Unit (SDU) – see Figure 3-1.
Figure 3-1 – Airbus Iridium SATCOM System Satellite Data Unit (SDU).
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3.1.1 General
The SDU is housed in an ARINC 600 2MCU enclosure, which is designed to be mounted in a
standard ARINC 600 mounting tray. See Figure 3-2 for an outline of this component.
Figure 3-2 – SDU Outline Drawing (dimensions in [millimeters] and inches)
3.1.2 Mechanical Specifications
Dimensions:
7.81” x 2.27” x 15.02” (198.3mm x 57.7mm x 381.5mm)
(See Figure 3-2)
Weight:
7.7 lbs. (3.49 kg) Max.
Material/Finish:
Aluminum Alloy with Black Polyurethane Finish
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Mounting:
ARINC 600 2MCU Mounting Tray
Rear Mating Connector:
Size 2 ARINC 600 Receptacle
Radiall P/N: NSXN2P201S0004
Maintenance Connector: RJ45 (8P8C) Modular Connector Jack
Flash Card:
CompactFlash® (Type I or Type II)
3.1.3 Environmental Specifications – Airbus Iridium SATCOM System
Refer to Appendix C – Environmental Qualification Forms for environmental testing conditions,
categories and descriptions of the conducted tests of the SDU.
Note:
DO-160G Categories for the Airbus Iridium SATCOM System are as specified by the design.
Qualification tests on the Airbus Iridium SATCOM System SDU have not been completed to date.
3.2 SDU Configuration Module (SCM)
This section describes the mechanical and environmental specifications of the components of the
SDU Configuration Module (SCM) – see Figure 3-3.
3.2.1 General
The SCM is housed in a small enclosure, which is designed to be mounted within 24” of the SDU rear
connector.
Figure 3-3 – Airbus Iridium SATCOM System SDU Configuration Module (SCM)
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Typically, the SCM will be mounted on or near the ARINC 600 mounting tray used for the SDU. See
Figure 3-4 for an outline of this component.
Figure 3-4 – SCM Outline Drawing (dimensions in [millimeters] and inches)
3.2.2 Mechanical Specifications
Dimensions:
1.00” x 2.00” x 4.69” (25.4mm x 50.8mm x 119.1mm)
Weight:
0.4 lbs. (0.18 kg) Max.
Material/Finish:
Aluminum alloy with clear chromate per MIL-DTL-5541, Type II,
Class 3 on all surfaces
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Figure 3-5 – SCM Oblique View (Note 1: Resistance between mounting plate and module not to exceed
20 milli-ohms. Also, resistance between mounting plate and aircraft structure not to exceed 20 milli-ohms.)
Figure 3-6 – SCM Connector View Showing Location of Pin 1 (Note 2: Connector is a 9-pin D-Sub,
P/N ABS1145A09P03B.)
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3.2.3 Environmental Specifications
Refer to Appendix C – Environmental Qualification Forms for environmental testing conditions,
categories and descriptions of the conducted tests of the SCM.
3.3 Airbus Iridium SATCOM System Satellite Antenna
The antenna is a Commercial Off the Shelf (COTS) unit that is mounted on the top of the aircraft’s
fuselage – see Figure 3-7. It provides satellite connectivity for both the GPS and Iridium satellite
systems.
Figure 3-7 – Airbus Iridium SATCOM System Antenna
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3.4 Antenna Coaxial Cable
For details on the selection and installation of the antenna coaxial cable, please see Section 4.3.4,
which provides recommended coaxial cable types to be used which meet the Airbus Iridium SATCOM
System requirements. Figure 3-8 illustrates the Iridium antenna coaxial cable and connectors.
Figure 3-8 – Iridium Antenna Coaxial Cable and Connectors
3.5 Interface Specifications
This section describes the interface specifications of the Airbus Iridium SATCOM System
components.
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SDU Rear Connector (J1)
Table 3-1 – J1A Top Plug (TP) Insert
Ethernet
3B
Tx+
Ethernet
3B
Rx+
Ethernet
2B
Tx-
Ethernet
3B
Rx-
Ethernet
3B
Tx-
Ethernet
4B
Tx-
10
11
12
13
14
15
Ethernet
1A
Tx+
Ethernet
1A
Rx+
Ethernet
1A
Rx-
Ethernet
1A
Tx-
Ethernet
2B
Tx+
Ethernet
2B
Rx+
Ethernet
2B
Rx-
Ethernet
4B
Tx+
Ethernet
4B
Rx+
Ethernet
4B
Rx-
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Table 3-2 – J1B Middle Plug (MP) Insert
No. 1
A429Rx
No. 1
A429Rx
No. 1
A429Tx
No. 1
A429Tx
Ext. 1
Mic Audio
Hi
Ext. 1
Mic Audio
Lo
Ext. 1
Audio Out
Hi
Ext. 1
Audio Out
Lo
No. 2
A429Rx
No. 2
A429Rx
No. 3
A429Rx
No. 3
A429Rx
No. 4
A429Rx
No. 4
A429Rx
No. 2
A429Tx
No. 2
A429Tx
SCM
Power
SCM
Ground
No. 1
Discrete
Output
LGCIU 1
Discrete
Input
No. 2
Discrete
Input
No. 3
Discrete
Input
No. 4
Discrete
Input
No. 5
Discrete
Input
No. 6
Discrete
Input
No. 7
Discrete
Input
SCM
Data
SCM
Clock
No. 5
A429Rx
No. 5
A429Rx
No. 6
A429Rx
No. 6
A429Rx
No. 7
A429Rx
No. 7
A429Rx
No. 8
A429Rx
No. 8
A429Rx
No. 9
A429Rx
No. 9
A429Rx
No. 10
A429Rx
No. 10
A429Rx
No. 3
A429Tx
No. 3
A429Tx
No. 4
A429Tx
No. 4
A429Tx
No. 11
A429Rx
No. 11
A429Rx
No. 1
RS232
Com
No. 4
RS232
Com
No. 8
Discrete
Input
No. 2
Discrete
Output
No. 12
A429Rx
No. 12
A429Rx
No. 3
Discrete
Output
No. 9
Discrete
Input
No. 4
Discrete
Output
No. 10
Discrete
Input
No. 13
A429Rx
No. 13
A429Rx
No. 2
RS232
Com
No. 3
RS232
Com
No. 5
A429Tx
No. 5
A429Tx
No. 1
No. 1
No. 1
No. 1
No. 2
No. 2
RS422Tx- RS422Tx+ RS422Rx+ RS422Rx- RS422Tx- RS422Tx+
RS232TXD RS232RTS RS232RXD RS232CTS RS232TXD RS232RTS
No. 2
No. 2
No. 3
No. 3
No. 3
No. 3
No. 4
No. 4
No. 4
No. 4
10 RS422Rx+ RS422Rx- RS422Tx- RS422Tx+ RS422Rx+ RS422Rx- RS422Tx- RS422Tx+ RS422Rx+ RS422RxRS232RXD RS232CTS RS232TXD RS232RTS RS232RXD RS232CTS RS232TXD RS232RTS RS232RXD RS232CTS
11
No. 11
Discrete
Input
No. 12
Discrete
Input
No. 13
Discrete
Input
No. 14
Discrete
Input
No. 15
Discrete
Input
LGCIU
HPP
No. 5
Discrete
Output
No. 6
Discrete
Output
No. 7
Discrete
Output
No. 8
Discrete
Output
12
No. 14
A429Rx
No. 14
A429Rx
No. 6
A429Tx
No. 6
A429Tx
A717Rx
A717Rx
No. 15
A429Rx
No. 15
A429Rx
No. 16
A429Rx
No. 16
A429Rx
13
Fault
Output
N/C
Fault
Output
N/O
14
Chime
Output
15
Phone
Ext. 2
Tip
Phone
Ext. 2
Ring
Phone
Ext. 3
Tip
Phone
Ext. 3
Ring
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Table 3-3 – J1C Bottom Plug (BP) Insert
Pin Size
Description
20
Not Used
12
Primary 28 VDC Power Input
12
Power Ground
20
Not Used
20
Not Used
20
Not Used
12
Not Used
12
Chassis Ground
16
Not Used
10
16
Not Used
11
16
Not Used
12
Not Used
13
Iridium/GPS Antenna
Figure 3-9 – SDU Connector Map
3.5.1 Power Input
The Airbus Iridium SATCOM System is powered by +28 VDC.
3.5.2 Chassis Ground
For redundant chassis ground connection only. Not to be used as a normal current carrying
conductor.
Quantity:
Format:
DC Chassis Ground
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3.5.3 ARINC 429 Digital Serial Bus Input
Quantity:
16
Format:
DITS, ARINC 429 Low or high speed
Low Speed Data Rate:
12.5 Kbps ± 1%
High Speed Data Rate:
100 Kbps ± 1%
SSM/SDI/Data Definition:
Software Selectable Protocols
3.5.4 ARINC 429 Digital Serial Bus Output
Quantity:
Format:
DITS, ARINC 429 Low or high speed
Low Speed Data Rate:
12.5 Kbps ± 1%
High Speed Data Rate:
100 Kbps ± 1%
SSM/SDI/Data Definition:
Software Selectable Protocols
3.5.5 Ethernet
Quantity:
Format:
802.3 10BASE-T/100BASE-TX, half- and full-duplex
modes (auto-negotiated)
ARINC 664P2 Physical Layer
3.5.6 Discrete Inputs
Quantity:
16 Configurable
Input Impedance:
>10 kΩ
Fault Current:
<15 mA
DIN+ Voltage Range:
Logic High: 7.0 – 36.0 VDC
Logic Low: 0 – 3.5 VDC
Pulse Width (Min):
100 ms
3.5.6.1 Configurable Inputs
Each configurable discrete input is individually software-configurable for the following:
Signal Level: Open-Ground (Negative-Seeking) or Open-28V (Positive-Seeking)
Logic Assignment: Active Low or Active High
Function: Selected from list.
Refer to §6.10 for additional information on use of configurable inputs.
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3.5.7 Discrete Outputs
Each discrete output transitions between an ‘Open Circuit’ (high-impedance-to-ground) and a ‘Closed
Circuit’ (low-impedance-to-ground) state to indicate a change in output logic.
Quantity:
8 Configurable
‘Open Circuit’ Impedance:
>100 kΩ
‘Open Circuit’ Voltage (Max.):
36 VDC
‘Closed Circuit’ Current Limit (Min.):
500 mA
Voltage Across ‘Closed Circuit’:
<1.25 V
3.5.7.1 Configurable Outputs
The Discrete Outputs use ‘Open-Closed’ signal levels, where the output is either high-impedance to
ground (Open) or low-impedance to ground (Closed). Each configurable discrete output is individually
software-configurable for the following:
Logic Assignment: Active Low (Closed) or Active High (Open)
Function: Selected from list.
Refer to §6.11 for additional information on use of configurable outputs.
3.5.8 Two-Wire Phone
Quantity:
Format:
Standard 2-Wire Tip and Ring Loop
Loop Battery:
48 ±4 VDC
Ring Signal:
20 Hz ±10%, 90 ±10 VAC RMS
Hook Flash:
<700 ms
Load Impedance (Nom.):
600 Ω
Polarity Sensitivity:
None
Audio Band Pass:
300 – 3400 Hz
3.5.9 Microphone Input
Quantity:
Format:
Standard DO-214 Microphone Input
Dynamic Range:
20 mV to 1.5 V RMS
Input Impedance:
150 Ω ± 20%
Mic. Bias (No Load):
16 ± 0.5 V
Mic. Bias Ripple:
<1 mV RMS in the 300 – 3400 Hz band
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Sidetone:
Provided by System to Interphone Output
Sidetone Level:
Software Configurable
Audio Band Pass:
300 – 3400 Hz
3.5.10 Iridium / GPS Antenna
Coaxial Cable Insertion Loss (Max.):
3 dB @ 1626.5 MHz
3.6 SDU Maintenance Connector (J2)
The Airbus Iridium SATCOM System SDU provides an RJ-45 Maintenance Port connector on the
front panel which provides for Ethernet connection to Ground Service Equipment (GSE) e.g. a laptop
or Personal Computer with a standard web browser.
3.7 SDU Configuration Module (SCM)
The SCM and antenna connect directly to the SDU. The SDU is the heart of the system and provides
all of the interfaces to other aircraft systems.
3.8 ARINC 429 Receiver Protocols
Table 3-4 – ARINC 429 Receiver Protocols – ATSU/FWC
Source:
ATSU / FWC
Label
Speed: High
(Configurable)
Parameter
Format
Transmit Rate
BCD
1s
172
ATSU Identifier Word
214
ATSU ICAO Address Word 1
Boolean
word
200 ms
216
ATSU ICAO Address Word 2
Boolean
word
200 ms
270
ATSU Status Word and Monitoring
Boolean
word
600 ms
307
SDU SAL
HYB
377
ATSU Equipment Identifier
BCD
1s
BOP (GFI=Eh)
ISO 5
N/A
ARINC BOP (GFI=Eh)
618
Block
Downlink
ISO 5
N/A
ARINC
618
Block
Uplink
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Table 3-5 – ARINC 429 Receiver Protocols – CFDS
Source: Airbus CFDS
Speed: Low
(Configurable)
Label
Parameter
Format
Transmit Rate
125
Time (UTC)
BCD
1s
126
Flight Phases
BNR
1s
155
Aircraft Configuration (Printer, ACARS, etc.)
Discrete
word
1s
156
Aircraft Type
Discrete
word
1s
157
Aircraft Configuration (ATSU2, ATSU1)
Discrete
word
1s
227
CFDS BITE Command
ISO 5
120 ms
233
Flight Number 1, 2
ISO 5
4s
234
Flight Number 3, 4
ISO 5
4s
235
Flight Number 5, 6
ISO 5
4s
236
Flight Number 7, 8
ISO 5
4s
260
BCD Date YY/MM/DD
BCD
1s
301
Aircraft Identification 1,2,3 (ORT parameter)
ISO 5
4s
302
Aircraft Identification 4,5,6 (ORT parameter)
ISO 5
4s
303
Aircraft Identification 7,8,9 (ORT parameter)
ISO 5
4s
304
Fleet Identification, Aircraft Type
ISO 5
4s
Table 3-6 – ARINC 429 Receiver Protocols – MCDU
Source: ARINC 739A MCDU
Label
Speed: Low
(Configurable)
Parameter
Format
Transmit Rate
BCD
1s
377
MCDU Identifier
270
Discrete Word #1
Discrete
word
1s
350
Maintenance Word #1
Discrete
word
1s
307
SDU SAL
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3.9 ARINC 429 Receiver Activity Status
Defines the criteria the Airbus Iridium SATCOM System uses for determining whether a receiver port
is active. A bus is generally declared active when 4 consecutive words at the specified rate are
received, and declared inactive when 4 consecutive samples fail.
Table 3-7 – ARINC 429 Receiver Port Monitoring
Receiver
Activity Label
ATSU / FWC
Min. Update Rate
270
1 Hz
ARINC 739A MCDU
270 / 377
1 Hz
Airbus CFDS
125 / 260
1 Hz
3.10 ARINC 429 Transmitter Protocols
Table 3-8 – ARINC 429 Transmitter Protocols SDU – ATSU/FWC
3.10.1 From SDU to ATSU / FWC
Destination: ATSU / FWC
Label
Speed: High (Configurable)
Parameter
Format
172
SDU Identifier
270
SDU Status Word and Monitoring
304
ATSU SAL
Transmit
Rate
Update Rate
BCD
1s
–
Boolean
word
1s
HYB
ARINC 618 BOP (GFI=Eh)
Block Uplink
ISO 5
N/A
ARINC 618
Block
Downlink
ISO 5
N/A
BOP (GFI=Eh)
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Table 3-9 – ARINC 429 Transmitter Protocols SDU – MCDU
3.10.2 From SDU to MCDU
Destination: ARINC 739A MCDU
Label
Parameter
Speed: Low (Configurable)
Format
Transmit
Rate
Update Rate
172
Subsystem Identifier
BCD
1s
–
377
Equipment Identifier
BCD
1s
–
220
MCDU Address Label for MCDU#1
221
MCDU Address Label for MCDU#2
222
MCDU Address Label for MCDU#3
Table 3-10 – ARINC 429 Transmitter Protocols SDU – CFDS
3.10.3
From SDU to Airbus CFDS
Destination: Airbus CFDS
Label
354
356
377
Speed: Low (Configurable)
Parameter
Format
Transmit Rate Update Rate
LRU Identification (PN, SN)
ISO 5
500 ms
–
Fault Status
ISO 5
200 ms
ARINC 429 Equipment Identifier
BCD
1s
–
Notes:
1. Label 356 is only transmitted when the system is in Operational or Maintenance mode and there are
no active failures or faults.
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4.
INSTALLATION CONSIDERATIONS
This section provides information on the installation considerations for each of the Airbus Iridium
SATCOM System components.
4.1 Satellite Data Unit (SDU)
The SDU is housed in an ARINC 600 2MCU enclosure, which is designed to be mounted in a
standard ARINC 600 mounting tray. Figure 4-1 shows a typical ARINC 600 2MCU tray used for the
SDU.
Figure 4-1 – 2MCU Mounting Tray
While the SDU does not require forced-air cooling, every attempt should be made to place the SDU in
a benign and well-ventilated environment. Placing the SDU on a plenum shelf in the Electronics Bay
of the aircraft and using a mounting tray that provides cooling air to the SDU is preferred.
The SDU tray should be electrically bonded to the airframe (<20 milliohms). It is recommended that
the SDU be located where easy front panel access is available to facilitate replacing the flash card or
connecting to the Maintenance Port.
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4.2 SDU Configuration Module (SCM)
The SCM can be mounted on or near the SDU tray within 24 inches of the SDU rear connector. The
SCM should be electrically bonded to the airframe (<20 milliohms). It is recommended that the SCM
be located to provide easy access to the cover if ever the SIM card requires replacement. Refer to
Figure 3-4 for the SCM mounting footprint.
4.3 Iridium Antenna System
The Airbus Iridium SATCOM System has a single combined Iridium/GPS RF connection on the rear
interface connector, which is to be connected to a single combined Iridium/GPS Antenna. The
antenna system is comprised of all the components from the rear interface connector up to and
including the antenna. The total gain of the antenna system must be greater than 0 dB at 1626.5 MHz
(measured at the antenna zenith).
Most Iridium antennas have a gain of +3 dBic at the zenith; therefore the maximum attenuation in the
rest of the antenna system must be less than 3 dB. If an antenna with a different gain is selected, the
maximum loss of the rest of the antenna system must be adjusted accordingly.
4.3.1 Antenna
Iridium SATCOM System Antenna: This is a passive antenna designed to cover the frequency range
from 1565 MHz to 1626.5 MHz for Iridium transmit / receive operations and GPS reception. It is a
low-profile, circular device that can be mounted directly to the aircraft fuselage. This antenna
connects to the Iridium SDU through a coaxial cable – see Figure 3-8 Figure 3-7.
The antenna specifications are listed below:
Weight (Typical)
0.170 kg (6 oz.)
Overall Dimensions (Typical)
Height:
16.8 mm (0.66 inches)
Diameter:
89 mm (3.5 inches)
Manufacturer’s Specification Reference Number
Drawing 009E5733-00, Revision – Iridium Antenna – Passive, 1565 – 1626.5 MHz,
RHCP – see Figure 4-2.
Iridium SATCOM System Supplier Equipment Specification,
Document No. 905-E5750-07, Revision –
Environmental Specifications
The Iridium SATCOM System antenna meets the environmental requirements of RTCA DO262A where applicable as referenced in Document No. 905-E5809-42, Revision A.
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Testing was performed to DO-160F, MIL-STD-810, EN-60068, ISO-2669, and the applicable
ABDs unless otherwise noted.
Temperature:
-55° C (-67° F); to +85° C (+185° F)
Altitude:
-100 to +55,000 FT
Vibration:
10 G’s (DO-160D/E F2-AB)
Electrical Specifications
Frequency:
1616.0 – 1625.5 MHz
VSWR:
≤ 1.5:1
Impedance:
50-Ohms
Polarization:
RHCP
Axial Ratio:
≤ 3.0 db @ zenith
Power Handling:
60 Watts CW
Figure 4-2 - Iridium Antenna, Outline and Dimensions
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4.3.2 Antenna Mounting
A .020 Thick Conductive Gasket is provided. L-3 recommends using (4) screws, MS24693-C274 for
mounting the Airbus Iridium Antenna – see Figure 4-3.
Figure 4-3 - Iridium Antenna, Gasket
4.3.3 Coaxial Cable
Iridium SATCOM System Coaxial Cable: This is an RF Cable designed to cover the frequency range
from 1565 MHz to 1626.5 MHz for Iridium transmit / receive operations and GPS reception. It is a
low-loss, aircraft-grade cable that will be mounted in the aircraft fuselage. This cable provides the
interconnection between the Iridium SATCOM System Satellite Data Unit and the Iridium Antenna.
The Coaxial Cable has an ARINC Size 5 coaxial contact installed on one end and a TNC male
connector installed on the other.
There are three possible lengths for this Coaxial Cable. They are designated by the last two digits of
the part number (01, 02 or 03) as listed below:
024E5733-01
024E5733-02
024E5733-03
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Airbus Iridium SATCOM System
The antenna coaxial specifications are listed below:
Weight (Typical)
024E5733-01 - 1.633 kg (57.6 oz)
024E5733-02 – 1.497 kg (52.8 oz)
024E5733-03 – 1.470 kg (51.8 oz)
Overall Dimensions (Typical)
Length:
024E5733-01 – 11.3 m (445.0 inches)
024E5733-02 – 10.2 m (402.0 inches)
024E5733-03 – 9.95 m (392.0 inches)
Diameter:
8.1 mm (0.317 inches)
Manufacturer’s Specification Reference Number
Drawing 024E5733-00, Revision B; Iridium Antenna Coax Cable – see Figure 4-4.
Iridium SATCOM System Supplier Equipment Specification,
Document No. 905-E5750-07, Revision –
Environmental Specifications
The Iridium SATCOM System Coaxial Cable meets the environmental requirements of RTCA
DO-262A where applicable as described in Document No. 905E5836-42. Testing was
performed to DO-160F, EN 4604, EN 3475, and the applicable ABDs unless otherwise noted.
Figure 4-4 – Iridium Antenna Coaxial Cable
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5.
SATCOM INSTALLATION MATERIALS
In addition to the Airbus Iridium SATCOM System LRUs (SDU and SCM), the materials described in
this section are generally required as part of a typical Airbus Iridium SATCOM System installation.
Note:
The system integrator is responsible to ensure that all installation materials used meet the regulatory
requirements for the intended aircraft installation environment.
5.1 Required Materials
ARINC 600 2MCU mounting tray
ARINC 600 Size 2 connector, with contacts
ARINC 600 ground block, with contacts
Iridium antenna (ref.4.3.1)
Antenna coaxial cable(s) (ref. §4.3.3)
System interface wiring (ref. §6)
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6.
SYSTEM INTERFACE WIRING
This section provides information on the system interface wiring required for the Airbus Iridium
SATCOM System.
6.1 General
All wire types and installation practices must comply with the requirements for the aircraft. Unless
otherwise noted, minimum wire size is 22 AWG for standard copper wire or 24 AWG for high strength
copper alloy wire.
Terminate all shields at ground block or ground stud on SDU tray. Keep shield drains and unshielded
conductor lengths as short as practicable (<3”).
6.2 Primary Power, Antenna, and SCM
The primary power, antenna, and SCM connections shown in Figure 6-1 are required for all Airbus
Iridium SATCOM System installations. The system will start and continue to operate whenever power
(20.5 – 32.2 VDC) is available at the Primary Power Input pin (J1C-2).
Figure 6-1 – Primary Power, Antenna, and SCM Interface
6.3 ARINC 429 Interfaces
The Airbus Iridium SATCOM System has 16 ARINC 429 receive ports and 6 ARINC 429 transmit
ports. Each port is software-configurable for high or low speed, and the receive ports are also
individually software-configurable for odd, even or no parity checking. The transmit ports always
transmit odd parity.
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6.3.1 Receiver Protocols
Each of the ARINC 429 receivers can be configured in software for the proper protocol of the external
aircraft system to which it is interfaced. Below is a list of the available ARINC 429 receiver protocols.
(See §3.8 for the label specifications for each receiver protocol.) Once a protocol (except “None” is
selected for any given receive port, it is no longer available for assignment to any of the other ports.
None
ACARS 1
ACARS 2
Airbus CFDS
A739 MCDU 1
A739 MCDU 2
A739 MCDU 3
When an input is not connected to an active system (e.g. no connection, or wiring provisions only are
installed), the port should be configured as “None” to avoid triggering bus inactivity faults.
6.3.2 Transmitter Protocols
Each of the ARINC 429 transmitters can be configured in software for the proper protocol of the
external aircraft system to which it is interfaced. Below is a list of the available ARINC 429 transmitter
protocols. (See §3.10 for the label specifications for each transmitter protocol.) Once a protocol
(except “None”) is selected for any given port, it is no longer available for assignment to any of the
other ports.
None
ACARS
A739 MCDU
Airbus CFDS
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6.4 MCDU
If an ARINC 739A MCDU is installed, MCDU 1 should be connected to ARINC 429 Tx 1 and ARINC
429 Rx 1. For MCDU 2 and 3, ARINC 429 Rx ports 2 and 3 are used as shown in Figure 6-2, but any
Rx port from 2 to 16 may be used.
Figure 6-2 – MCDU Interface
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6.5 ACARS ATSU
The ACARS ARINC 429 Tx interface provides safety-services data functionality for the Airbus Iridium
SATCOM System. It is recommended that if the ACARS ATSU ARINC 429 Rx connection will not be
utilized, that the wires be capped and stowed near the connectors as shown. ARINC 429 Rx port 4 is
shown in Figure 6-3, but any Rx port from 2 to 16 may be used.
Figure 6-3 – ACARS ATSU Interface
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6.6 CFDIU Interface
The SDU communicates with the Airbus Centralized Fault Display Interface Unit (CFDIU) over
two ARINC 429 Low Speed busses, (1) input and (1) output as shown in Figure 6-4.
Figure 6-4 – CFDIU Interface
6.7 Date, Time and Position
The Airbus Iridium SATCOM System uses date, time and position information for numerous purposes,
including information tags attached to various reports and events. Date, time and position information
is provided by the system’s internal GPS.
6.8 RS-232/422 Databus
The Airbus Iridium SATCOM System has four serial ports (transmit and receive). Each port is
software-configurable for RS-232 or RS-422 mode. The speed, data bits, parity, stop bits, and flow
control settings for each port are also software-configurable. See Figure 6-5.
Each serial port is assigned 5 pins on the rear connector. The function of these pins is dependent on
whether RS-232 or RS-422 mode is being used.
Table 6-1 – Serial Port Pin Assignments
RS-232
RS-422
Port 1
TXD
Tx-
9E
RTS
Tx+
RXD
Port 3
Port 4
9J
10C
10G
9F
9K
10D
10H
Rx+
9G
10A
10E
10J
CTS
Rx-
9H
10B
10F
10K
Com
Not Used
7J
9A
9B
7K
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When configured for RS-232 mode, the serial ports support software (Xon/Xoff) and hardware
(RTS/CTS) handshaking. If hardware handshaking is not being used, the RTS and CTS pins do not
need to be connected.
Figure 6-5 – Serial Port Interface
6.9 Ethernet
The Airbus Iridium SATCOM System has four Ethernet ports (see Figure 6-6). Each port can autonegotiate the best speed (10/100) and mode (full/half duplex). Port 1A is currently configured with a
static IP address.
A 4-conductor Ethernet cable must be used. The rear connector pin layout provides slightly better
noise immunity with a star-quad cable construction, but a twisted-pair cable construction can generally
also be used. For star-quad cables, the conductor lay order should be maintained without crossing the
conductors when terminating. For twisted-pair construction, the conductor twists should be maintained
right up to the rear connector. In either case, the best noise immunity is obtained by keeping the strip
length of the shield as short as physically possible, preferably <0.25 inches.
PIC P/N E51424 and ECS P/N 422404 are examples of aircraft-quality star-quad Ethernet cables that
are typically suitable for use. PIC P/N E40424 and ECS P/N 922404 are examples of aircraft-quality
twisted-pair Ethernet cables that are typically suitable for use.
Each of the Ethernet ports can be configured in software for the proper protocol of the external aircraft
system to which it is interfaced. Below is a list of the available protocols.
None
Not Monitored
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Monitored
Unused Ethernet ports should be configured as “None.” A “Monitored” port is one where the system
expects an active link and it will generate a fault if the Ethernet link to the external system is not
available. For example, if the SDU is connected by Ethernet to a Class 2 EFB that is routinely turned
off and stowed for take-off and landing, the port should be configured as “Not Monitored” or the
system will generate a fault whenever the EFB is disconnected.
Figure 6-6 – Ethernet Interface
6.10 Discrete Inputs
The Airbus Iridium SATCOM System has 16 Discrete Inputs, of which 14 are software-configurable for
Open-Ground or Open-28V signaling levels, Active High or Active Low logic, and the assigned
function.
6.10.1 Landing Gear Control Interface Unit (LGCIU) Input
Discrete Input No. 1 (Din 1) is dedicated for use as a Landing Gear Control Interface Unit (LGCIU1)
input. When there is only one LGCIU input (i.e. the LGCIU2 function is not assigned to a Discrete
Input; see §6.10.2) and the ‘LGCIU1’ input transitions to the active state, the system is signaled that
the aircraft is on the ground, and the inactive state indicates that the aircraft is in the air.
LGCIU1 (Din 1) is only an Open-Ground input; it cannot be configured as an Open-28V input. A
Hardware Programming Pin (HPP) is provided to set whether the LGCIU1 input is Active High or
Active Low. If the LGCIU HPP pin (J1B-11F) is tied low, LGCIU1 is configured as an Active Low input,
i.e. Ground = On Ground. If the LGCIU HPP pin is connected to ground, LGCIU1 is configured as an
Active High input, i.e. Ground = In Air.
If one of the configurable Discrete Inputs is configured for the LGCIU2 function (see §6.10.2), the
following logic is used to determine the aircraft’s Air-Ground status:
When the ‘LGCIU1’ discrete input is in the active state (as configured by the LGCIU HPP
strapping) and the ‘LGCIU2’ discrete input is in the active state (as defined by the ICT setting
for the discrete input configured as ‘LGCIU 2’), the aircraft is considered as ‘on the ground.’
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When any of the LGCIU discrete inputs are in the inactive state, the aircraft is considered as
‘in the air.
6.10.2 Function Assignment
The discrete inputs are software configurable. Once a function is selected for any given input, it is no
longer available for assignment to any of the other inputs. See Figure 6-7.
The ‘Mic On’, and ‘Call Light’ functions are used in conjunction with the Extension 1 audio interface
and are discussed in §6.12.1.1 below.
Discrete Input No. 1 (Din 1) is dedicated as a LGCIU input. Only Discrete Inputs Din 2 through Din 15
are software-configurable. Discrete Input No. 16 (Din 16) is dedicated as “aircraft on ground” (LGCIU
HPP).
None
When an input is not connected to an active system (e.g. no connection, or wiring provisions
only are installed), the input should be configured as “None.”
System Reset
The System Reset Discrete Input, when configured, will reset the system only after an inactive
to active transition. The system will reset only once even if the discrete input is left active. The
System Reset function is independent of the 'In-Air' or 'On-Ground' status of the aircraft.
Landing Gear Control Interface Unit 2 (LGCIU2)
A second Landing Gear Control Interface Unit input may optionally be provided to the AFIRS
system. Refer to §6.10.1 for the logic used when a ‘LGCIU2’ input is provided.
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Figure 6-7 – Discrete Input Interfaces
6.11 Discrete Outputs
The Airbus Iridium SATCOM System has 8 configurable Discrete Outputs, each of which is softwareconfigurable for Active High or Active Low logic and the assigned function. The Discrete Outputs use
‘Open-Closed’ signal levels, where the output is either high-impedance to ground (Open) or lowimpedance to ground (Closed).
Once a function (except “None”) is selected for any given output, it is no longer available for
assignment to any of the other outputs.
6.12 SATCOM
This section describes the interface and integration requirements for the Airbus Iridium SATCOM
System with an Audio Integrating System.
6.12.1 Audio Integrating System
Extension 1 is generally intended to be connected to the aircraft’s audio integrating system for flight
crew use. The interfaces required to fully support this functionality vary significantly depending on the
design of the audio integrating system. Generally, the MCDUs are used for control and display of the
SATCOM functions for Extension 1.
6.12.1.1 Audio Discrete Signals
There is one discrete input and one discrete output that can be used to support the integrated audio
interface.
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Mic On Input
The ‘Mic On’ function is dedicated as a ‘Latched ACP’ mode; therefore, Voice Extension 1
(Mic/Phone input) will answer an incoming call when the ‘Mic On’ input transitions to the active
state. Once a call is in progress, the microphone audio channel will function as long as the
‘Mic On’ input is in the active state. If a call is in progress and the ‘Mic On’ input toggles to the
inactive state, the call will be terminated. For outgoing calls when the ‘Mic On’ input is
configured for ‘Latched ACP’, the function is dependent on which control source is configured
for Extension 1. When an MCDU is the Extension 1 dialing control, setting the ‘Mic On’ input to
the active state will initiate the dialing process using the phone number preselected on the
MCDU.
Call Light Output
The ‘Call Light’ output is software configurable for either steady or flashing lights. When an
incoming voice call is ringing, the ‘Call Light’ output will transition to the active state; either in a
steady state or flashing at approximately a 1 Hz rate. When the incoming call is subsequently
answered, the ‘Call Light’ output will remain active in the steady state as long as the call is in
progress. When the call in progress is terminated, the ‘Call Light’ output will go inactive.
6.12.1.2 Latched ACP Configuration
If the Audio Integrating System provides a latched Mic On output, the following interface can be used.
When an incoming call is ringing and the SATCOM switch on the Audio Control Panel is pressed, the
call will be answered and microphone audio will always be live. The SATCOM switch on the Audio
Control Panel is pressed a second time to end the call. Calls cannot be answered and terminated on
the MCDU screen in this configuration.
The following diagram also shows how the Call Light output can be interfaced to an Audio Integrating
System that provides SATCOM visual and aural call indications. In this case, a Call Light, Chime and
Chime Reset switch are not required. See Figure 6-8.
Figure 6-8 – Latched ACP Audio Interface
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7.
SATCOM SYSTEM CONFIGURATION
You configure the Airbus Iridium SATCOM System Satellite Data Unit (SDU) via Ethernet using a
laptop, web browser, and the AFIRS Maintenance User Interface (MUI).
Note:
The MUI only accepts English-language characters and numbers.
IMPORTANT: This manual provides information on how to connect to the Maintenance Port and
access the Maintenance User Interface (MUI). It also provides general information on the steps
required to configure and update the Airbus Iridium SATCOM System.
The Airbus Iridium SATCOM System has an Ethernet interface for the Maintenance Port connection.
An RJ-45 Maintenance Port jack is located behind the access door on the front panel of the SDU as
shown in Figure 7-1.
Figure 7-1 – Maintenance Port Location
Note:
When performing the initial configuration of an installed system, perform and complete the Before
Power-On Tests in section 8.1 before applying power to the Airbus Iridium SATCOM System.
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7.1 Accessing the Maintenance User Interface (MUI)
You access the AFIRS MUI by connecting an Ethernet cable to the Maintenance Port of the SDU.
Alternatively, as described in section 6.9, Ethernet Port 1A can be used.
Also, if an Electronic Flight Bag (EFB) with a supported web browser installed is connected to one of
the rear Ethernet port connections, the EFB can be used as an AFIRS maintenance terminal and a
laptop is not required.
To access the Maintenance User Interface (MUI):
1. Connect an Ethernet cable either to the Maintenance Port via the front panel access door of
the SDU or through the rear Ethernet Port 1A connection. Note that the Airbus Iridium
SATCOM System power may be on or off.
2. Connect the other end of the Ethernet cable to a laptop that is running a web browser.
Note:
It is recommended to use Mozilla Firefox ® as the Internet browser with the SDU. The laptop
network adapter must be set to the same subnet mask as the SDU (i.e. 255.255.255.0).
3. If not already powered, apply power to the SDU.
4. Confirm that the green link light (adjacent to Maintenance Port RJ45 connector) is illuminated,
either steady or flashing (a flashing link light indicates that data is being transmitted).
5. Open a web browser on the laptop. In the Address bar, type one of the two following IP
addresses depending on the connection point:
192.168.128.1 (if connecting to the Maintenance Port at the front panel of the SDU –
see Figure 7-1.)
10.0.0.238 (if connecting to the rear Ethernet Port 1A. – see Figure 6-6).
Note:
Before opening the Web page, clear the cache of the Web browser or Ctrl+F5 and reopen the
Web page.
The Airbus Iridium SATCOM System Home page appears with the General tab information
displayed – see Figure 7-2 – Home Page – General Tab.
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Figure 7-2 – Home Page – General Tab
The default view opens to the Home page General tab (see Figure 7-2) which displays the
following information:
1 Login area
2 Menu of available links to pages accessible to various users upon login
3 Tabs: General, ARINC, and Discrete In
4 System and Link status display area
5 System information data display area
6 Mode: OPERATIONAL, MAINTENANCE, INITIALIZING, etc.
7.1.1 Home Page Tab Descriptions
To open the MUI Home Page, there is no user name and password required.
The General tab page displays:
UTC Date and Time: This is correlated to a GPS clock if ICT parameter ‘Internal GPS =
Active’. If no link is available (i.e. during startup) a default date is displayed.
Position: This is the AFIRS GPS position. If no GPS is fixed, no GPS will be displayed.
Phone Number: Displays the aircraft phone number (12 digits).
ISVM IMEI: Iridium Satellite Voice Modem International Mobile Equipment Identity (15 digits).
ISDM IMEI: Iridium Satellite Data Modem International Mobile Equipment Identity (15 digits).
Airbus Iridium SATCOM System Status Indicators:
System: Yellow (INIT) initializing; Green (OK), Yellow (FAULT), Yellow (blank) indicates that
system is in Maintenance Mode; Red indicates SDU Configuration Module (SCM) or Satellite
Data Unit (SDU) Hardware failure or other critical error.
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ISVM LINK: Yellow (NO LINK) no Iridium link if CSQ (Channel Signal Quality) is 0-1;
Green (OK) if CSQ is 2-5
ISDM LINK: Yellow (NO LINK) no Iridium link if CSQ (Channel Signal Quality) is 0-1;
Green (OK) if CSQ is 2-5
GPS LINK: Yellow (NO FIX), Green (OK)
The ARINC tab displays the status of the 16 ARINC 429 RX channels. The status of a configured
function is either ACTIVE (green) or FAULT (red). The ARINC 717 RX configuration is currently not
used.
The DISCRETE IN tab displays the state of the 16 Discrete Inputs. The state of the configured
functional input is either ACTIVE (green) or INACTIVE (blue).
7.1.2 Faults Page
The Faults page provides access to the system fault log (see Figure 7-3), and fault history (Figure
7-4). The FAULT tab displays only currently raised faults, while the HISTORY tab displays all raised
and cleared faults since the last system reboot.
Figure 7-3 – Faults Page (Fault Log Tab)
Figure 7-4 – Faults Page (Fault History Tab)
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7.1.3 Part Numbers Page
The Part Numbers page provides the status of the software (Figure 7-5) and hardware configuration
(Figure 7-6) of the Airbus Iridium SATCOM System.
Figure 7-5 – Part Number Page (Software Tab)
Figure 7-6 – Part Number Page (Hardware Tab)
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7.2 Entering Maintenance Mode
In order to enter Maintenance Mode, the aircraft must be deemed ‘On-Ground’. If the aircraft is
deemed ‘In-Air’, the [Enter Maintenance Mode] button will be or will become unavailable.
If the aircraft status changes to ‘In-Air’ while in Maintenance Mode, the system will reboot
automatically and return to Operational Mode.
Entering Maintenance Mode is granted to the following users after login with their assigned user name
and password:
Maintenance User
Administrator User
Entering Maintenance Mode provides the Upgrades page to the Maintenance User and Administrator
User. In addition, the Maintenance User is allowed to modify 5 parameters in the ORT page.
The Administrator User is allowed to modify parameters in the UAT page only.
Role based MUI permissions are provided in Table 7-1 through Table 7-3 at the end of this section.
To enter Maintenance Mode:
1. Once connected to the Airbus Iridium SATCOM System MUI, on the Home page, enter your
user name and password, then click Login.
2. If the aircraft is deemed ‘On-Ground’, the [Enter Maintenance Mode] button is available at the
top right corner of the screen. Click Enter Maintenance Mode.
A message appears (see Figure 7-7) prompting for confirmation to enter Maintenance Mode.
Figure 7-7– Entering Maintenance Mode Message
3. To enter Maintenance Mode, click OK.
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The Home screen appears as shown in Figure 7-8. The SYSTEM status indicates Yellow (blank).
Note:
Entering Maintenance Mode disables all MCDU functions.
Figure 7-8 – Maintenance Mode Initial Display Screen
To exit Maintenance Mode:
Upon completion of uploading of data or software files or modifying parameters, click Exit
Maintenance Mode for the changes to take effect – see Figure 7-9.
A dialog box will appear, asking you to confirm that you want to save changes. Click OK, then the
system will restart, displaying the screen shown in Figure 7-10.
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Figure 7-9 – Maintenance Mode Exit Screen
Figure 7-10 – System Restart Screen
Note:
Exiting Maintenance Mode enables all MCDU functions.
If the aircraft status changes to ‘In-Air’ while in Maintenance Mode, the system will reboot
automatically and return to Operational Mode, disregarding incomplete file uploads.
The following sections describe the functionality of the additional menu items available in
Maintenance Mode.
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7.2.1 Maintenance Mode Menu Descriptions
Entering Maintenance Mode provides the Upgrades page to the Maintenance User and Administrator
User.
1. Click Upgrades to upload software or data files. The screen shown in Figure 7-11 will be
displayed.
2. Click Browse to navigate and select the software or data file to be uploaded.
Figure 7-11 – Upgrades Screen
3. Click Upload to start the uploading process. Upon successful completion of the Upload step,
the blue progress bars turn green. The uploaded data files display a CRC code, the uploaded
software file displays the part number of the software. Non-compatible files will be rejected
and an error message displays.
4. Click Apply to start the verification process. Upon successful completion of the verification
step, the blue progress bars turn green. Non-compatible files will be rejected and an error
message displays
5. Click Reset in order to upload another file.
6. For changes to take effect, the system must be rebooted. Click Exit Maintenance Mode.
Note:
If the aircraft status changes to ‘In-Air’ before the Upload process is completed, the system
will reboot automatically and return to Operational Mode, disregarding incomplete uploads.
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7. Maintenance User can modify only 5 ORT parameters:
a. Click ORT (Owner Requirements Table) to configure customized settings for specific
aircraft and or operator requirements.
8. Administrator User can modify any UAT parameter:
a. Click UAT (User Access Table) to configure user access privileges.
9. Click Exit Maintenance Mode for changes to take effect. The system reboots and returns to
Operational Mode
Note:
If the aircraft status changes to ‘In-Air’ before the Upload process is completed, the system will
reboot automatically and return to Operational Mode, disregarding incomplete uploads.
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Table 7-1 - Read Privileges by Role
Read Privileges
Status and Part Numbers
Fault
Status
Part Numbers:
ICT P/N,
ORT P/N,
ISVM F/W Ver.,
ISDM F/W Ver.,
S/W P/N,
SDU P/N,
SCM P/N,
SCM S/N
Yes
Yes
Yes
Yes
Yes
Yes
Yes
Yes
Yes
Yes
Yes
Yes
Status: Operating Mode,
GPS Source, Configured
Phone Number, ISVM IMEI,
ISDM IMEI, Status LEDs
(System, GPS, ISVM, ISDM)
ARINC 429 Rx
Channels Status
(Active/
Inactive)
Yes
Yes
Data Collector
Yes
Maintenance
Administrator
Roles
Guest
(no login
required)
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Configurations
Discrete Inputs
Status (Active/
Inactive)
UAT
ADB
ICT
(Address
Book)
(User
Access
Table)
No
No
No
No
Yes
No
No
No
No
Yes
Yes
Yes
(Limited)
No
Yes
No
Yes
Yes
No
No
Yes
Yes
ORT
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Table 7-2 - Download Privileges by Role
Download Privileges
Logs
Roles
Failures
In‐Air
Faults
On‐
Ground
Faults
Configurations
Status (Link
Changes)
Debug
ICT
ORT
ADB
UAT
(Address
Book)
(User Access
Table)
Guest (no login required)
No
No
No
No
No
No
No
No
No
Data Collector
Yes
Yes
Yes
Yes
Yes
No
No
No
No
Maintenance
Yes
Yes
Yes
Yes
Yes
Yes
Yes
Yes
No
Administrator
Yes
Yes
Yes
Yes
Yes
No
No
No
Yes
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Table 7-3 – Modify Privileges by Role
Modify Privileges
Modifications
Software/Data Loading (Upload)
UAT
Roles
ORT
Parameters
ICT
Parameters
Address Book
(User
Access
Table)
UAT
ADB
S/W
Upgrades
ICT
ORT
(Complete)
(Address
Book)
(User
Access
Table)
Guest (no login required)
No
No
No
No
No
No
No
No
No
Data Collector
No
No
No
No
No
No
No
No
No
Maintenance
Yes (Limited)
No
No
No
Yes
Yes
Yes
Yes
Yes
Administrator
No
No
No
Yes
Yes
Yes
Yes
Yes
Yes
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7.3 Configuring the Airbus Iridium SATCOM System
This section provides basic information on how to configure the Airbus Iridium SATCOM
System.
User access privileges are required to modify parameters as follows:
Maintenance User – 5 ORT parameters
Administrator User – UAT parameters
The above listed users are required to log in with a user name and password and enter
Maintenance Mode.
Note: The aircraft status must be ‘On-Ground’ when Entering Maintenance Mode.
The following sections are intended to provide you with information on the configuration process
and data inputs required to install and verify a system as operational: For the purposes of
installation, system configuration and verification, the following steps should be completed:
1. Address Book to upload
2. ORT parameters for Maintenance User
3. ICT file to upload
4. UAT parameters for user roles
7.3.1 Address Book
The Address Book can be uploaded as a comma-separated-values file (adb.csv) by the
Maintenance User or Administrator User after login with a user name and password, and
Entering Maintenance Mode when the aircraft status ‘On-Ground’.
The Address Book can be viewed in the MUI by the Maintenance User or Administrator User
after login in Operational Mode. Up to 300 Address Book entries can be made.
Note: Address Book entries can be viewed and, if unprotected, modified via the MCDU in
Operational Mode.
The Address Book can be downloaded as ‘adb.csv’ file in the MUI (including modifications that
have been made via the MCDU) by the Maintenance User after login in Operational Mode.
The following restrictions and limitations apply to the parameters of a compatible adb.csv file:
Phone Number – up to 18 digits
Name – up to 23 alphanumeric characters; A-Z, 0-9, +, -, /, space
Priority – 4 (Public), 3 (Non-Safety), 2 (Safety), 1 (Emergency)
Protected – 0 (No), 1 (Yes)
Directory - 4 (Public), 3 (Non-Safety), 2 (Safety), 1 (Emergency)
Speed Dial 1 - 1
Speed Dial 2 – 0 (currently not used)
Speed Dial 3 – 0 (currently not used)
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To view the Address Book in the MUI:
1. In Operational Mode, log in as Maintenance User or Administrator User.
2. Click Address Book to display the Address Book entries (see Figure 7-12).
Figure 7-12 – Address Book
3. View the Address Book entries in the MUI:
Order#: Up to 300 address book entries.
Note: This parameter is not part of the adb.csv file.
Phone Number: From 6 to 18 digits
Contact Name: Up to 23 alphanumeric characters
Default Call Priority and Directory: Options displayed are Emergency, Safety,
Non-Safety, and Public.
Protected: YES indicates that the Address Book entry is ‘protected’ from being
modified. NO indicates that the Address Book entry is ‘not protected’, and can be
modified or deleted via the MCDU in Operational Mode.
Extension 2 and 3 Speed Dial: Currently not used.
7.3.2 Owner Requirements Table (ORT) Parameters
The following user access privileges are required to modify ORT parameters:
Maintenance User – 5 ORT parameters
The Owner Requirements Table (ORT) for Maintenance User (see Figure 7-13) contains the
parameters that may be customized by the individual aircraft operator. These settings may be
changed as required to meet operational requirements or preferences.
The ORT file can be uploaded and downloaded as a binary file by the Maintenance User.
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The file name of an up-loadable ORT file has a part number; for example, ‘852E5927-00.bin’. It
is version-controlled and the CRC is calculated and displayed during the upload process for
verification.
The default file name of a downloaded ORT file is ‘ort.bin’.
Figure 7-13 – ORT Screen
Note:
An ORT Configuration Worksheet is provided in Appendix B to assist the operator in selecting
and documenting the correct ORT configuration settings.
To access and modify ORT parameters:
1. Log in with user name and password as Maintenance User.
2. Click Enter Maintenance Mode.
Note:
The aircraft status must be ‘On-Ground’ to be able to Enter Maintenance Mode.
3. Click the ORT link on the left-hand side of the screen to open the ORT page.
4. AIR TO GROUND CALLS - CALL PROGRESS TONES: The call progress tones can be
configured to either North American or European. The default is NORTH AMERICAN.
5. ALLOW MANUAL DIALING - EXTENSION 1: If set to YES, manually dialed phone
calls can be placed from the cockpit, in addition to using the directory. If set to NO,
phone calls from the cockpit can be placed only by using the directory.
Note:
If set to NO, the MANUAL DIAL prompt will not be available on the MCDU.
IMPORTANT! To obtain operational approval for safety-services voice in accordance with
FAA AC20-150A, Extension 1 must be configured YES to allow manual dialing for the flight
crew.
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6. OTHER CALL PARAMETERS – ALLOW LOW PRIORITY CALLS IN COCKPIT: Lowpriority calls are considered PUBLIC or Priority 4. If set to YES, low-priority calls can be
received in the cockpit, and low-priority calls can be placed from the cockpit. If set to
NO, low-priority incoming calls will not ring in the cockpit, and no low-priority calls can be
placed from the cockpit.
Note:
If set to NO, the PUBLIC directory prompt will not be available on the MCDU.
7. SAFETY SERVICES (Airbus Iridium SATCOM System) – ADDITIONAL ACARS
HEADER PARAMETER: The default configuration of NONE corresponds to SITA;
alternatively, select ARINC.
8. ATS ENABLED: If set to YES, the Iridium SIM card installed in the SCM must be ATSenabled. If set to NO, the Iridium SIM card installed in the SCM is not ATS-enabled.
7.3.3 Installation Configuration Table (ICT)
The Installation Configuration Table (ICT) parameters may not be viewed or modified.
The ICT file can be uploaded and downloaded as a binary file by the Maintenance User.
The file name of an uploadable ICT file has a part number; for example, ‘852E5910-00.bin’. It is
version-controlled and the CRC is calculated and displayed during the upload process for
verification.
The default file name of a downloaded ICT file is ‘ict.bin’.
7.3.4 User Access Table (UAT) Parameters
The following user access privileges are required to modify UAT parameters:
Administrator User
The User Access Table (UAT), shown in Figure 7-14, is used by the Administrator User to set
up user access privileges for up to 20 users. These settings may be changed as required to
meet operational requirements.
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Figure 7-14 – UAT Page
To access and modify UAT parameters:
1. Log in with user name and password as Administrator User
2. Click Enter Maintenance Mode.
Note:
The aircraft status must be “On-Ground” to be able to Enter Maintenance Mode.
3.
4.
5.
6.
Click the UAT (Security) link on the left-hand side of the screen to open the UAT page.
USER NAME: From 4 to 20 upper-case alphanumeric characters
PASSWORD: From 4 to 20 upper-case alphanumeric characters
SECURITY LEVEL: Select either DATA COLLECTOR (default) or MAINTENANCE or
ADMINISTRATOR.
Up to 20 Users can be configured.
To exit Maintenance Mode:
Upon completion of modifying parameters, click Exit Maintenance Mode for the system to
reboot and the changes to take effect.
Note:
Exiting Maintenance Mode enables all MCDU functions.
If the aircraft status changes to ‘In-Air’ while in Maintenance Mode, the system will reboot
automatically and return to Operational Mode.
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7.4 Upgrading Airbus Iridium SATCOM System Software
The Airbus Iridium SATCOM System software is field-upgradeable using the Upgrade function
of the MUI in Maintenance Mode.
One of the following user privileges is required to login and enter Maintenance Mode to upload
software and data files:
Maintenance User
Administrator User
Note:
The aircraft status must be ‘On-Ground’ to enter Maintenance Mode.
7.4.1 Upgrade Materials
Make sure you have the following materials available before beginning the upgrade procedure.
A notebook computer with an Ethernet port, running the Microsoft Windows operating
system and a web browser such as Internet Explorer (see Section 7.1 Accessing the
Maintenance Port).
A standard, straight-through Ethernet patch cable.
The software release folder that contains the upgrade file (upgrade.tgz).
The software release notes to identify any changes to functionality or special upload
instructions.
7.4.2 Upgrade Procedure
Before beginning the upload procedure, make sure you have saved the applicable software
release folder that includes the upgrade.tgz file to an accessible location on your laptop. Make
sure you review the software release notes for any special instructions that may apply.
To upgrade the Airbus Iridium SATCOM System Software:
1. From the left-hand menu, click Upgrades.
The Upgrades screen displays.
2. Click Browse to locate the software file to upload (upgrade.tgz).
3. Once you have selected the software file you want to upload, click Upload to start the
upload process.
Blue progress bars indicate the file uploading status. When the upload is complete and
successful, the progress bars turn green, and the new Software Part Numbers of the
new software image will be displayed (see Figure 7-15).
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Figure 7-15 – Software Upgrade Progress
Note:
Incompatible files will be rejected. The progress bars turn red, and an error message
displays next to the progress bars. Click Reset to restart the upgrade process.
If you uploaded an incorrect file, but have not yet clicked Apply, click Reset to restart the
upgrade process.
4. Click Apply to verify and load the software into non-volatile memory.
Blue progress bars indicate the status of the software file being installed on the SDU.
When the software verification is completed successfully, the progress bars turn green,
and the message displays that the system must be restarted for the changes to take
effect (see Figure 7-16).
Figure 7-16 – Software Loading Progress Screens
Note:
If the aircraft status changes to ‘In-Air’ at any time during the Upgrade process, the system
will reboot automatically and return to Operational Mode, disregarding any incomplete
upgrades.
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To activate the newly installed software, you must Exit Maintenance Mode and restart the
SDU.
5. To exit Maintenance mode, click Exit Maintenance Mode at the top-right corner of the
MUI screen,
A confirmation message displays prompting to confirm that you want to exit Maintenance
Mode (see Figure 7-17).
Figure 7-17 – Exit Maintenance Mode Message
6. Click OK.
The SDU automatically restarts and applies the newly installed software. A message
displays indicating that the AFIRS system reboots (see Figure 7-18).
Figure 7-18 – Exit Maintenance Mode Progress Bar
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7. When the restart is complete, verify that the SDU is in Operational Mode and
functioning as expected. To verify that the correct software version and
configurations have been loaded, check the following:
a. From the Home page, click on the General, ARINC, and Discrete In tabs to
review the system and link status, and the status of the ARINC 429 Rx and
Discrete In connections.
b. Click on the Faults page to view if any faults are currently raised.
c. Click on the Part Numbers page to verify that the software part number
displayed matches the software version and part number as noted in the release
notes or upgrade instructions
d. Enter User Name and Password (Maintenance User) and click Login.
e. Maintenance User - Click ORT and review the ORT configurations to confirm that
they are correct.
f.
Click Logout after your review is complete and satisfactory.
7.5 Exiting Maintenance Mode
To save changes and uploaded configuration data, you need to exit maintenance mode for
the changes to take effect
1. In the top-right hand corner of the screen, click Exit Maintenance Mode.
2. A Message displays prompting for confirmation to exit Maintenance Mode
(see Figure 7-19).
Note:
If you click Cancel, your changes are still active but not saved.
Figure 7-19 – Exiting Prompt Message
3. Click OK to exit Maintenance Mode, save your changes and reboot the system.
4. The following message displays (see Figure 7-20):
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Figure 7-20 – Restart Screen
5. Once the system reboots to Operational Mode, verify your changes and confirm that
the correct software and data files have been installed.
6. Click the Part Numbers page and review the Software tab for the correct Part
Numbers
7. The Part Numbers screen displays as shown in Figure 7-21.
Figure 7-21 – Software Part Numbers Screen
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8.
MAINTENANCE AND CHECKOUT
This section provides instructions on post-installation checkout procedures and information on
Instructions for Continued Airworthiness.
8.1 Post-Installation Checkout
8.1.1 Before Power-On Tests
1. Before installing the SDU in the mounting tray, confirm that all aircraft interface wiring is
correct as per the aircraft wiring integration design.
2. Confirm that a valid SIM card is installed in the SDU Configuration Module (SCM).
3. Set the system circuit breaker for the Main power source and confirm that 28 VDC power
is available between pins J1C-2 and J1C-3. Pull the circuit breaker and ensure that Main
power is removed.
4. Place the SDU in the mounting tray and secure the front hold-down.
5. Open the front panel door and confirm that a flash card is installed in the SDU.
Note:
If no flash card is present, a FLASH CARD FAULT is generated in the MUI, and an SDU
FAIL will display on the MCDU SATCOM BITE STATUS page. Only FLYHT P/N 5021180-x flash cards should be used in the Airbus Iridium SATCOM System.
6. If installed, the cockpit FAULT indication should be illuminated when power is not
applied to the system.
7. Set the system circuit breaker for the Main power source. The SYSTEM LED indicator
on the front panel of the SDU will be amber indicating that the system is initializing.
Note:
The first time an SDU is installed in an aircraft, the SYSTEM LED indicator will typically
remain amber even after it has initialized. The MUI will display an SCM Configuration
Fault indicating that the proper configuration settings have not yet been made.
8. Connect an Ethernet cable to the Maintenance Port in the front panel and follow
procedures to open the Maintenance User Interface (MUI) as described in Section 7.
9. Log in to the MUI as Maintenance User and Enter Maintenance Mode to install ICT and
ORT files in accordance with the procedures contained in Section 7. Exit Maintenance
Mode to reboot the system. Keep the laptop connected to the Maintenance Port after
finishing the configuration procedure.
10. Once the system resets, the SYSTEM LED indicator on the front panel of the SDU will
turn green once the system is operational.
11. The cockpit FAULT annunciator should remain illuminated whenever the SYSTEM
STATUS indicator is amber, and extinguish when the SYSTEM LED indicator turns
green.
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8.1.2 Aircraft Systems Interface Tests
Note:
The tests listed in this section are generic in nature and are not intended to be used as a
test plan for any specific aircraft installation. They should only be used by the aircraft
systems integrator as a guide in developing the correct and complete aircraft-specific
integration tests. The aircraft systems integrator’s test plan should ensure that the
aircraft and its systems are in a safe condition for each test to be performed.
8.1.2.1 Main Power Test
1. Confirm that 28 VDC power is available at the Main power input, and that the Airbus
Iridium SATCOM System is initialized and operating.
2. Using the MUI Home page General tab, confirm that the System status and Datalinks
are green.
8.1.2.2 ARINC 429 Databus Interface Tests
1. On the MUI, click on the ARINC tab on the Home page.
2. Confirm the aircraft systems connected to the databus ports being tested are operational
and transmitting on the databus.
3. Confirm that the ARINC 429 Rx (1-16) channels used are shown as ACTIVE.
8.1.2.3 MCDU Tests
Confirm SATCOM functionality on each MCDU as follows:
1. On the MCDU MENU page, the
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