L3 Technologies AFIRS228S User Manual

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AFIRS 228S Iridium

Global Communications System

Installation Manual

Part Numbers

SDU: 228E5733-00 SCM: 418E5733-00

Publication: 165E5733-00 Rev. 03

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AFIRS 228S Iridium Global Communications System Installation Manual

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 #7E994), 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.

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

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FCC Certification

This device complies with Part 15 of the FCC rules. Operation is subject to the following two conditions: (1) This device may not cause harmful interference, and (2) this device must accept any interference received, including interference that may cause undesired operation. Changes or modifications not expressly approved by the party responsible for compliance could void the user’s authority to operate the equipment.

NOTE: This equipment has been tested and found to comply with the limits for a Class A digital device, pursuant to part 15 of the FCC Rules. These limits are designed to pro-vide reasonable protection against harmful interference when the equipment is operated in a commercial environment. This equipment generates, uses, and can radiate radio frequency energy and, if not installed and used in accordance with the instruction manual, may cause harmful interference to radio communications. Operation of this equipment in a residential area is likely to cause harmful interference in which case the user will be required to correct the interference at his own expense.

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RECORD OF REVISIONS

Rev. Issue Date Description Pages By

00 01 November 2013 Initial issue. All CM

01 15 December 2013

02 21 January 2014

03 16 July 2014 Software PN Change, removed

Corrected SDU & SCM TopLevel Part Numbers.

references to unused features, removed non-configurable, updated wiring diagrams, added MCDU screenshots, added voice and data modem models

All CM/SC

All CP

1, 6, 7, 8, 9, 22, 23, 34, 38, 39, 70-73

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Table of Contents

RECORD OF REVISIONS ............................................................................................................. iv

List of Figures ..................................................................................................................................4

List of Tables....................................................................................................................................5

Appendices ......................................................................................................................................5

Supplemental Documents ...............................................................................................................5

1. Introduction ................................................................................................................................6

1.1 Applicability ........................................................................................................................6

1.2 Model Designation .............................................................................................................6

1.2.1 Iridium SATCOM System .................................................................................................................... 6

1.3 Part Numbers ....................................................................................................................6

1.4 Reference Documents ......................................................................................................6

1.5 Definitions of Acronyms and Terms ..................................................................................8

2. Description and Operation ...................................................................................................... 12

2.1 System Overview ........................................................................................................... 12

2.2 System Architecture ....................................................................................................... 13

2.3 External System Interfaces ............................................................................................ 13

3. Equipment Specifications ....................................................................................................... 16

3.1 Satellite Data Unit (SDU) ............................................................................................... 16

3.1.1 Mechanical Specifications ............................................................................................................... 17

3.1.2 Environmental Specifications –Iridium SATCOM System .............................................................. 18

3.2 SDU Configuration Module (SCM) ................................................................................. 18

3.2.1 Mechanical Specifications ............................................................................................................... 19

3.2.2 Environmental Specifications .......................................................................................................... 20

3.3 Iridium SATCOM System Satellite Antenna .................................................................. 20

3.4 Antenna Coaxial Cable .................................................................................................. 21

3.5 Interface Specifications .................................................................................................. 22

3.5.1 SDU Rear Connector (J1) .................................................................................................................. 22

3.5.2 Power Input ...................................................................................................................................... 24

3.5.3 Chassis Ground ................................................................................................................................. 24

3.5.4 ARINC 429 Digital Serial Bus Input .................................................................................................. 25

3.5.5 ARINC 429 Digital Serial Bus Output ............................................................................................... 25

3.5.6 Rear Ethernet Ports .......................................................................................................................... 25

3.5.7 Discrete Inputs .................................................................................................................................. 25

3.5.8 Discrete Outputs............................................................................................................................... 26

3.5.9 Microphone Input ............................................................................................................................ 27

3.5.10 Iridium / GPS Antenna ..................................................................................................................... 27

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3.6 Maintenance Front Panel Ethernet Port (J2) ................................................................. 27

3.7 SDU Configuration Module (SCM) ................................................................................. 27

3.8 ARINC 429 Receiver Protocols ...................................................................................... 28

3.9 ARINC 429 Receiver Activity Status .............................................................................. 29

3.10 ARINC 429 Transmitter Protocols.................................................................................. 29

3.10.1 From SDU to ATSU / FWC ................................................................................................................ 29

3.10.2 From SDU to MCDU .......................................................................................................................... 30

4. Installation Considerations ..................................................................................................... 32

4.1 Satellite Data Unit (SDU) ............................................................................................... 32

4.2 SDU Configuration Module (SCM) ................................................................................. 32

4.3 Iridium Antenna System ................................................................................................. 33

4.3.1 Antenna Specifications .................................................................................................................... 33

4.3.2 Antenna Mounting ........................................................................................................................... 35

4.3.3 Coaxial Antenna Cable ..................................................................................................................... 36

5. SATCOM Installation Materials .............................................................................................. 38

5.1 Required Materials ......................................................................................................... 38

6. System Interface Wiring ......................................................................................................... 40

6.1 General ........................................................................................................................... 40

6.2 Primary Power, Antenna, and SCM ............................................................................... 40

6.3 ARINC 429 Interfaces .................................................................................................... 41

6.3.1 Receiver Protocols ............................................................................................................................ 41

6.3.2 Transmitter Protocols ...................................................................................................................... 41

6.4 MCDU ............................................................................................................................. 42

6.5 ACARS ATSU ................................................................................................................ 43

6.6 CFDIU Interface ............................................................................................................. 44

6.7 Date, Time, and Position ................................................................................................ 44

6.8 Rear Ethernet Ports........................................................................................................ 44

6.9 Discrete Inputs ............................................................................................................... 45

6.9.1 Landing Gear Control Interface Unit (LGCIU) Input ....................................................................... 45

6.9.2 Function Assignment ........................................................................................................................ 45

6.10 Discrete Outputs ............................................................................................................. 47

6.11 SATCOM ........................................................................................................................ 47

6.11.1 Audio Integrating System ................................................................................................................ 47

7. SATCOM System Configuration ............................................................................................. 50

7.1 Access the Maintenance User Interface (MUI) .............................................................. 51

7.1.1 Home Page Tab Descriptions ........................................................................................................... 52

7.1.2 Faults Page ........................................................................................................................................ 54

7.1.3 Part Numbers Page........................................................................................................................... 55

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7.2 Maintenance Mode ......................................................................................................... 56

7.2.1 Maintenance Mode Upgrades Page................................................................................................ 57

7.3 Configure the Iridium SATCOM System ........................................................................ 64

7.3.1 Address Book .................................................................................................................................... 64

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 Upgrade Iridium SATCOM System Software ................................................................ 69

7.4.1 Upgrade Materials ............................................................................................................................ 69

7.4.2 Upgrade the Iridium SATCOM System Software ............................................................................ 70

7.5 Exit Maintenance Mode .................................................................................................. 72

8. Maintenance and Checkout .................................................................................................... 74

8.1 Post-Installation Checkout ............................................................................................. 74

8.1.1 Before Power-On Tests .................................................................................................................... 74

8.1.2 Aircraft Systems Interface Tests ...................................................................................................... 74

8.1.3 Operational System Tests ................................................................................................................ 78

8.1.4 EMI Tests ........................................................................................................................................... 79

8.2 Instructions for Continued Airworthiness ....................................................................... 79

List of Figures

FIGURE 2-1 –IRIDIUM SATCOM SYSTEM OPERATIONAL CONCEPT ............................................................................................. 12

FIGURE 2-2 –IRIDIUM SATCOM SYSTEM BLOCK DIAGRAM ......................................................................................................... 13

FIGURE 2-3 –IRIDIUM SATCOM SYSTEM EXTERNAL INTERFACES ............................................................................................... 14

FIGURE 3-1 –IRIDIUM SATCOM SYSTEM SATELLITE DATA UNIT (SDU) ....................................................................................... 16

FIGURE 3-2 – SDU OUTLINE DRAWING (DIMENSIONS IN [MILLIMETERS] AND INCHES) .......................................................... 17

FIGURE 3-3 –IRIDIUM SATCOM SYSTEM SDU CONFIGURATION MODULE (SCM) ..................................................................... 18

FIGURE 3-4 – SCM OBLIQUE VIEW ................................................................................................................................................ 19

FIGURE 3-5 – SCM CONNECTOR VIEW SHOWING LOCATION OF PIN 1 ...................................................................................... 19

FIGURE 3-6 – SCM OUTLINE DRAWING (DIMENSIONS IN [MILLIMETERS] AND INCHES) .......................................................... 20

FIGURE 3-7 –IRIDIUM SATCOM SYSTEM ANTENNA ..................................................................................................................... 20

FIGURE 3-8 – IRIDIUM ANTENNA COAXIAL CABLE AND CONNECTORS ...................................................................................... 21

FIGURE 3-9 – SDU CONNECTOR MAP ............................................................................................................................................ 24

FIGURE 4-1 – TYPICAL 2MCU MOUNTING TRAY FOR THE SDU ................................................................................................... 32

FIGURE 4-2 - IRIDIUM ANTENNA, OUTLINE AND DIMENSIONS .................................................................................................. 34

FIGURE 4-3 - IRIDIUM ANTENNA, GASKET .................................................................................................................................... 35

FIGURE 4-4 – IRIDIUM ANTENNA COAXIAL CABLE ....................................................................................................................... 36

FIGURE 6-1 – PRIMARY POWER, ANTENNA, AND SCM INTERFACE ............................................................................................ 40

FIGURE 6-2 – MCDU INTERFACE .................................................................................................................................................... 42

FIGURE 6-3 – ACARS ATSU INTERFACE .......................................................................................................................................... 43

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FIGURE 6-4 – CFDIU INTERFACE..................................................................................................................................................... 44

FIGURE 6-5 – REAR ETHERNET PORTS ........................................................................................................................................... 45

FIGURE 6-6 – DISCRETE INPUT INTERFACES ................................................................................................................................. 46

FIGURE 6-7 – LATCHED ACP AUDIO INTERFACE ........................................................................................................................... 48

FIGURE 7-1 – MAINTENANCE PORT LOCATION ............................................................................................................................ 50

FIGURE 7-2 – HOME PAGE – GENERAL TAB .................................................................................................................................. 52

FIGURE 7-3 – FAULTS PAGE (FAULT TAB) ...................................................................................................................................... 54

FIGURE 7-4 – FAULTS PAGE (HISTORY TAB) .................................................................................................................................. 54

FIGURE 7-5 – PART NUMBERS PAGE (SOFTWARE TAB) ............................................................................................................... 55

FIGURE 7-6 – PART NUMBERS PAGE (HARDWARE TAB) .............................................................................................................. 55

FIGURE 7-7 – MAINTENANCE MODE INITIAL DISPLAY SCREEN ................................................................................................... 56

List of Tables

TABLE 1-1 – PART NUMBERS ........................................................................................................................................................... 6

TABLE 1-2 – REFERENCES ................................................................................................................................................................. 6

TABLE 1-3 – ACRONYMS AND TERMS ............................................................................................................................................. 8

TABLE 3-1 – J1A TOP PLUG (TP) INSERT ........................................................................................................................................ 22

TABLE 3-2 – J1B MIDDLE PLUG (MP) INSERT ................................................................................................................................ 23

TABLE 3-3 – J1C BOTTOM PLUG (BP) INSERT ................................................................................................................................ 24

TABLE 3-4 – ARINC 429 RECEIVER PROTOCOLS – ATSU/FWC...................................................................................................... 28

TABLE 3-5 – ARINC 429 RECEIVER PROTOCOLS – MCDU ............................................................................................................. 28

TABLE 3-6 – ARINC 429 RECEIVER PORT MONITORING ............................................................................................................... 29

TABLE 3-7 – ARINC 429 TRANSMITTER PROTOCOLS SDU – ATSU/FWC ..................................................................................... 29

TABLE 3-8 – ARINC 429 TRANSMITTER PROTOCOLS SDU – MCDU ............................................................................................. 30

TABLE 7-1 - READ PRIVILEGES BY ROLE ......................................................................................................................................... 60

TABLE 7-2 - DOWNLOAD PRIVILEGES BY ROLE ............................................................................................................................. 61

TABLE 7-3 – MODIFY PRIVILEGES BY ROLE .................................................................................................................................... 62

Appendices

Appendix A – Wiring Diagram ................................................................................................................................. 1

Appendix B – ORT Worksheet ................................................................................................................................ 4

Appendix C – System Faults ................................................................................................................................... 6

Supplemental Documents

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1. INTRODUCTION

This section provides a general introduction to the Iridium SATCOM System and its applicable standards and references.

1.1 Applicability

This Installation Manual provides the information necessary to plan the 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 Iridium SATCOM System. This manual is applicable to the following software version(s):

Software Part Number: 840E5733-09

1.2 Model Designation

This manual covers model designation Iridium SATCOM System.

1.2.1 Iridium SATCOM System

The Iridium SATCOM System 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 Iridium SATCOM System.

Table 1-1 – Part Numbers

Part Number Description

228E5733-00 Iridium SATCOM System Satellite Data Unit (SDU)

418E5733-00 Iridium SATCOM System SDU Configuration Module (SCM)

Formatted: No underline, Font color: Auto, Not Highlight

1.4 Reference Documents

Table 1-2 – References

Ref. Document Number Description

ANSI/TIA/EIA-232F-1997

ARINC 429-19 Mark 33 Digital Information Transfer System (DITS)

ARINC 573-7 Mark 2 Aircraft Integrated Data System (AIDS Mark 2)

ARINC 600-16 Air Transport Avionics Equipment Interfaces

ARINC 619-3 ACARS Protocols For Avionic End Systems

ARINC 664-2 Aircraft Data Networks

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Interface Between Data Terminal Equipment and Data CircuitTerminating Equipment Employing Serial Binary Data Interchange

AFIRS 228S Iridium Global Communications System Installation Manual

Ref. Document Number Description

ARINC 702-6 Flight Management Computer System

ARINC 702A-3 Advanced Flight Management Computer System

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

16.

FAA TSO C-159a

17.

GAMA Publication No. 11, Ver. 5.1

18.

IEEE 802.3-2008

19.

RTCA/DO-160G

20.

RTCA/DO-214

21.

RTCA/DO-262A Minimum Operational Performance Standards for Avionics

22.

TIA/EIA-422-B

Second Generation Aviation Satellite Communication System, Aircraft Installation Provisions

Technical Standard Order, Avionics Supporting Next Generation Satellite Systems (NGSS)

ARINC 429, General Aviation Subset

IEEE Standard for Information Technology-Specific Requirements

- Part 3: Carrier Sense Multiple Access with Collision Detection (CMSA/CD) Access Method and Physical Layer Specifications

Environmental Conditions and Test Procedures for Airborne Equipment

Audio Systems Characteristics and Minimum Operational Performance Standards for Aircraft Audio Systems and Equipment

Supporting Next Generation Satellite Systems (NGSS)

Electrical Characteristics of Balanced Voltage Digital Interface Circuits

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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

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

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

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Acronym Definition

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

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

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Acronym Definition

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

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 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.

Figure 2-1 –Iridium SATCOM System Operational Concept

The 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.

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2.2 System Architecture

The 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).

Figure 2-2 –Iridium SATCOM System Block Diagram

2.3 External System Interfaces

• Audio System Interface (1)

• ARINC 429 Transmitters (6) and Receivers (16)

• Discrete Outputs (8) and Inputs (16)

• Iridium Antenna (1)

• User Media Interfaces – SIM (1), CF (1)

• Maintenance Interfaces – Ethernet (1)

• Ethernet Ports (4)

• Voice Modem – Iridium 9523

• Data Modem – Iridium 9602

Figure 2-3 illustrates the interfaces that the Iridium SATCOM System provides to external aircraft systems or to the user.

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Figure 2-3 –Iridium SATCOM System External Interfaces NEED EFB GRAPHIC

• 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.

• 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 Iridium SATCOM System. Typical interfaced systems include MCDUs, ACARS ATSUs, etc.

• Maintenance Front Panel Ethernet Port J2 (1)

An RJ45 jack on the front panel provides Maintenance Port access using an Ethernet connection.

• Rear Ethernet Ports (4)

These interfaces can be used to connect to several different systems. Typical interfaced

systems include EFB, etc.One of these ports can also be used to provide a remote maintenance

port interface (e.g. in the flight compartment).

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•

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 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) that must be installed to be used for system fault testing.

•

Voice Modem – Iridium 9523

Connects the Iridium System in the aircraft to the Iridium satellite for voice communication.

•

Data Modem – Iridium 9602

Connects the Iridium System in the aircraft to the Iridium satellite for ACARS data communication.

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3. EQUIPMENT SPECIFICATIONS

This section describes the mechanical and environmental specifications of the components of the Iridium SATCOM System.

3.1 Satellite Data Unit (SDU)

The SDU is housed in an ARINC 600 2MCU enclosure designed to be mounted in a standard ARINC 600 mounting tray.

Figure 3-1 –Iridium SATCOM System Satellite Data Unit (SDU)

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3.1.1 Mechanical Specifications

Dimensions 7.81” x 2.27” x 15.02” (198.3mm x 57.7mm x 381.5mm)

Weight 7.7 lbs. (3.49 kg) Max

Material/Finish Aluminum Alloy with Black Polyurethane Finish

Mounting ARINC 600 2MCU Mounting Tray

Rear Mating Connector Size 2 ARINC 600 Receptacle

Maintenance Connector RJ45 (8P8C) Modular Connector Jack

Flash Card CompactFlash® (Type I or Type II)

Radiall P/N: NSXN2P201S0004

Figure 3-2 – SDU Outline Drawing (dimensions in [millimeters] and inches)

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3.1.2 Environmental Specifications –Iridium SATCOM System

Refer to Supplemental Documents for environmental testing conditions, categories and descriptions of the SDU tests conducted.

Note:

DO-160G categories for the Iridium SATCOM System are as specified by the design.

3.2 SDU Configuration Module (SCM)

The SCM is housed in a small enclosure designed to be mounted within 24” of the SDU rear connector. Typically, the SCM will be mounted on or near the ARINC 600 mounting tray used for the SDU. See Figure 3-6 for an outline of this component.

Figure 3-3 –Iridium SATCOM System SDU Configuration Module (SCM)

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3.2.1 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

Note:

Resistance not to exceed 20 milli-ohms

- Between mounting plate and module

- Between mounting plate and aircraft structure

Figure 3-4 – SCM Oblique View

Figure 3-5 – SCM Connector View Showing Location of Pin 1

Note:

Connector is a 9-pin D-Sub, P/N ABS1145A09P03B

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Figure 3-6 – SCM Outline Drawing (dimensions in [millimeters] and inches)

3.2.2 Environmental Specifications

Refer to Supplemental Documents for environmental testing conditions, categories, and descriptions of the SCM tests conducted.

3.3 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. It provides satellite connectivity for both the GPS and Iridium satellite systems.

Figure 3-7 –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 4.3.3 which provides recommended coaxial cable types to be used which meet the Iridium SATCOM System requirements.

Figure 3-8 – Iridium Antenna Coaxial Cable and Connectors

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A B C D E F G H J K

Ethernet

AFIRS 228S Iridium Global Communications System Installation Manual

3.5 Interface Specifications

3.5.1 SDU Rear Connector (J1)

Table 3-1 – J1A Top Plug (TP) Insert

Tx+

Ethernet

Rx-

3 O O O O O O O O O O

O O O O O O O O O O

Tx+

Ethernet

Rx-

7 O O O O O O O O O O

O O O O O O O O O O

Rx+

Ethernet

1A Tx-

Rx+

Ethernet

4B Tx-

O O

O O O O O O O O

Tx+

Ethernet

Rx-

Rx+

Ethernet

Tx-

O O

Tx+

Ethernet

Rx-

Rx+

Ethernet

Tx-

O O O O O O O O O O

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AFIRS 228S Iridium Global Communications System Installation Manual

A B C D E F G H J K

No. 1

No. 2

No. 3

No. 4

No. 2

No. 5

No. 6

No. 7

No. 8

No. 9

No. 2

No. 3

No. 5

No. 1

No. 2

No. 11

No. 12

No. 13

No. 14

No. 15

No. 5

No. 6

No. 7

No. 8

Phone

Table 3-2 – J1B Middle Plug (MP) Insert

O O O O O O

Ext. 1

Mic Audio

Ext. 1

Mic Audio

Ext. 1

Audio Out

Ext. 1

Audio Out

A429Rx

O O O O O O

A429Rx

A429Tx

3 O O

No. 1

Discrete

Output

A429Rx

No. 10

A429Rx

No. 8

Discrete

Input

RS232

Com

No. 2

RS422Rx+

RS232RXD

Discrete

Input

No. 14

A429Rx

Fault

Output

14 O

N/C

LGCIU 1

Discrete

A429Rx

No. 10

A429Rx

No. 2

Discrete

Output

RS232

No. 2

RS422Rx-

RS232CTS

Discrete

No. 14

A429Rx

Output

Chime Output

A429Rx

O O O O O O O

No. 2

Discrete

Input

A429Rx

No. 3

A429Tx

No. 12

A429Rx

A429Tx

No. 3

RS422Tx-

RS232TXD

Discrete

Input

No. 6

A429Tx

Input

Com

Input

Fault

N/O

A429Rx

No. 3

Discrete

Input

A429Rx

No. 3

A429Tx

No. 12

A429Rx

A429Tx

No. 3

RS422Tx+

RS232RTS

Discrete

Input

No. 6

A429Tx

O O O O O O O O

A429Rx

Discrete

A429Rx

A429Tx

Discrete

RS422Tx-

RS232TXD

RS422Rx+ RS232RXD

Discrete

A717Rx A A717Rx

No. 4

Input

No. 4

No. 3

Output

No. 3

Input

A429Rx

No. 5

Discrete

Input

A429Rx

No. 4

A429Tx

No. 9

Discrete

Input

RS422Tx+

RS232RTS

No. 3

RS422Rx-

RS232CTS

LGCIU

HPP

A429Rx

No. 6

Discrete

Input

A429Rx

No. 11

A429Rx

No. 4

Discrete

Output

RS422Rx+

RS232RXD

No. 4

RS422Tx-

RS232TXD

Discrete

Output

No. 15

A429Rx

RS422Rx-

RS232CTS

RS422Tx+

RS232RTS

A429Rx

No. 7

Discrete

Input

A429Rx

No. 11

A429Rx

No. 10

Discrete

Input

No. 4

Discrete

Output

No. 15

A429Rx

A429Tx

SCM

Power

SCM

Data

A429Rx

No. 1

RS232

Com

No. 13

A429Rx

RS422Tx-

RS232TXD

No. 4 RS422Rx+ RS232RXD

Discrete

Output

No. 16

A429Rx

A429Tx

SCM

Ground

SCM Clock

A429Rx

No. 4

RS232

Com

No. 13

A429Rx

RS422Tx+

RS232RTS

No. 4

RS422Rx-

RS232CTS

Discrete

Output

No. 16

A429Rx

15 O O O O O O

Ext. 2

Tip

Ext. 2

Ring

Ext. 3

Tip

Ext. 3

Ring

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Table 3-3 – J1C Bottom Plug (BP) Insert

Pin Size Description

1 20 Not Used

2 12 Primary 28 VDC Power Input

3 12 Power Ground

4 20 Not Used

5 20 Not Used

6 20 Not Used

7 12 Not Used

8 16 Chassis Ground

9 16 Not Used

10 16 Not Used

11 16 Not Used

12 5 Not Used

13 5 Iridium/GPS Antenna

Figure 3-9 – SDU Connector Map

3.5.2 Power Input

The Iridium SATCOM System is powered by +28 VDC.

3.5.3 Chassis Ground

Quantity 1

Format DC Chassis Ground

For redundant chassis ground connection only.

Not to be used as a normal current carrying conductor.

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3.5.4 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

3.5.5 ARINC 429 Digital Serial Bus Output

Quantity 6

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

3.5.6 Rear Ethernet Ports

Quantity 4

Format 802.3 10BASE-T/100BASE-TX, half- and full-duplex modes

(auto-negotiated) ARINC 664P2 Physical Layer

3.5.7 Discrete Inputs

Quantity 16 Configurable

Input Impedance >10 k

Fault Current <15 mA

DIN+ Voltage Range Logic High: 7.0 – 36.0 VDC

Pulse Width (Min) 100 ms

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Ω

Logic Low: 0 – 3.5 VDC

AFIRS 228S Iridium Global Communications System Installation Manual

3.5.7.1 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 Section 6.9 for additional information on use of configurable inputs.

3.5.8 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

3.5.8.1 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 Section 6.10 for additional information on use of configurable outputs.

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3.5.9 Microphone Input

Quantity 1

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

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 Maintenance Front Panel Ethernet Port (J2)

The 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.

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3.8 ARINC 429 Receiver Protocols

Table 3-4 – ARINC 429 Receiver Protocols – ATSU/FWC

Source: ATSU / FWC

Label Parameter Format Transmit Rate

172 ATSU Identifier Word BCD 1 s

270 ATSU Status Word and Monitoring

307 SDU SAL HYB

377 ATSU Equipment Identifier BCD 1 s

ARINC 618

Block Uplink

ARINC 618

Block Downlink

Source: ARINC 739A MCDU

Label Parameter Format Transmit Rate

377 MCDU Identifier BCD 1 s

270 Discrete Word #1

350 Maintenance Word #1

307 SDU SAL HYB

Boolean

word

BOP (GFI=Eh) ISO 5 N/A

Table 3-5 – ARINC 429 Receiver Protocols – MCDU

Discrete

word

Discrete

word

Speed: High

(Configurable)

600 ms

Speed: Low (Configurable)

1 s

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Receiver

Activity Label

Min

imum

Update Rate

AFIRS 228S Iridium Global Communications System Installation Manual

3.9 ARINC 429 Receiver Activity Status

Defines the criteria the Iridium SATCOM System uses to determine if a receiver port is active. A bus is generally declared active when four consecutive words at the specified rate are received, and declared inactive when four consecutive samples fail.

Table 3-6 – ARINC 429 Receiver Port Monitoring

ATSU / FWC 270 1 Hz

ARINC 739A MCDU 270 / 377 1 Hz

3.10 ARINC 429 Transmitter Protocols

3.10.1 From SDU to ATSU / FWC

Table 3-7 – ARINC 429 Transmitter Protocols SDU – ATSU/FWC

Destination: ATSU / FWC Speed:

Label Parameter Format Transmit

172 SDU Identifier BCD 1 s –

270

304 ATSU SAL HYB

ARINC 618

Block Uplink

ARINC 618

Block Downlink

SDU Status Word and Monitoring

BOP (GFI=Eh) ISO 5 N/A -

Boolean

word

High (Configurable)

Update Rate

Rate

1 s -

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3.10.2 From SDU to MCDU

Table 3-8 – ARINC 429 Transmitter Protocols SDU – MCDU

Destination:

ARINC 739A MCDU

Label Parameter Format

172 Subsystem Identifier BCD 1 s –

377 Equipment Identifier BCD 1 s –

220

MCDU Address Label for MCDU#1

221

MCDU Address Label for MCDU#2

222

MCDU Address Label for MCDU#3

Speed:

Transmit Rate

Low (Configurable)

Update

Rate

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4. INSTALLATION CONSIDERATIONS

4.1 Satellite Data Unit (SDU)

The SDU is housed in an ARINC 600 2MCU enclosure designed to be mounted in a standard ARINC 600 mounting tray. Although the SDU does not require forced-air cooling, every attempt should be made to install it in a well-ventilated area, preferably on a mounting tray that provides cooling air to the SDU.

Figure 4-1 – Typical 2MCU Mounting Tray for the SDU

The SDU tray should be electrically bonded to the airframe (<20 milli-ohms), and installed so that there is easy access to the front panel to facilitate replacing the flash card or connecting to the Maintenance Port.

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 milli-ohms). Ensure that the installation location allows easy access to the cover should the SIM card require replacement. Refer to Figure 3-6 for the SCM mounting footprint.

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AFIRS 228S Iridium Global Communications System Installation Manual

4.3 Iridium Antenna System

The 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.

4.3.1 Antenna Specifications

The antenna is a low-profile, circular device that can be mounted directly to the aircraft fuselage, and connects to the Iridium SDU through a coaxial cable – see Figure 3-8.

Weight (Typical) 0.170 kg (6 oz.)

Height (Typical) 16.8 mm (0.66 inches)

Diameter (Typical) 89 mm (3.5 inches)

Manufacturer’s Reference Documentation

The Iridium SATCOM System antenna meets the environmental requirements of RTCA DO-262A, where applicable, as referenced in Doc. No. 905-E5809-42, Revision C.

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 Gs (DO-160D/E F2-AB)

Drawing 009E5733-00, Revision B

Iridium Antenna – Passive, 1565 – 1626.5 MHz

RHCP – see Figure 4-2.

Iridium SATCOM System Supplier Equipment Specification: Doc. No. 905-E5750-07, Revision N

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AFIRS 228S Iridium Global Communications System Installation Manual

Frequency 1616.0 – 1626.5 MHz

VSWR

Impedance 50-Ohms

Polarization RHCP

Axial Ratio

Power Handling 60 Watts CW

≤

1.5:1

≤

3.0 db @ zenith

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 four screws (MS24693-C274) for mounting the Iridium Antenna.

Figure 4-3 - Iridium Antenna, Gasket

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AFIRS 228S Iridium Global Communications System Installation Manual

4.3.3 Coaxial Antenna Cable

The Iridium SATCOM System uses 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. One end of the coaxial cable has an ARINC Size 5 coaxial contact installed and the other end has a TNC male connector.

Specifications

Weight (Typical)

Length (Typical)

Diameter (Typical) 8.1 mm (0.32 inches)

Manufacturer’s Reference Documentation

•

024E5733-01 - 1.64 kg (57.85 oz)

•

024E5733-02 – 1.50 kg (52.91 oz)

•

024E5733-03 – 1.47 kg (51.85 oz)

•

024E5733-04 – 1.68 kg (59.26 oz)

•

024E5733-01 – 11.30 m (445.0 inches)

•

024E5733-02 – 10.20 m (402.0 inches)

•

024E5733-03 – 9.95 m (392.0 inches)

•

024E5733-04 – 11.56 m (455.1 inches)

Drawing 024E5733-00, Revision D

Iridium Antenna Coax Cable – see Figure 4-4.

Iridium SATCOM System Supplier Equipment Specification: Doc. No. 905-E5750-07, Revision N

Formatted: No underline, Font color: Auto

The Iridium SATCOM System coaxial cable meets the environmental requirements of RTCA DO-262A, where applicable, as described in Doc. No. 905E5836-42 Revision B.

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 Iridium SATCOM System LRUs (SDU and SCM), the materials described in this section are generally required as part of a typical 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

• Antenna coaxial cable(s)

• System interface wiring

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6. SYSTEM INTERFACE WIRING

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 in Figure 6-1 are required for all 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

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6.3 ARINC 429 Interfaces

The 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.

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. Once a protocol (except “None”) is selected for any given receive port, it is no longer available for assignment to any other port. 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.

•

None

•

ACARS 1

•

ACARS 2

•

A739 MCDU 1

•

A739 MCDU 2

•

A739 MCDU 3

See Section 0 for the label specifications for each receiver protocol.

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. Once a protocol (except “None”) is selected for any given port, it is no longer available for assignment to any other port.

•

None

•

ACARS

•

A739 MCDU

See Section 3.10 for the label specifications for each transmitter protocol.

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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

• MCDU 2 and 3 can be connected to any ARINC 429 Rx port from 2-16

(Ports 2 and 3 are used in Figure 6-2)

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 Iridium SATCOM System. It is recommended that if the ACARS ATSU ARINC 429 Rx connection will not be used, that the wires be capped and stowed near the connectors as shown. Any Rx port from 2 to 16 may be used (ARINC 429 Rx port 4 is used in Figure 6-3).

Figure 6-3 – ACARS ATSU Interface

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6.6 CFDIU Interface

The SDU communicates with the 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 Iridium SATCOM System’s internal GPS provides date, time, and position information to be used in various ways; for example, attaching information tags to various reports and events.

6.8 Rear Ethernet Ports

The Iridium SATCOM System has four rear Ethernet ports (see Figure 6-5) that should be set to “none”. Each port can auto-negotiate the best speed (10/100) and mode (full/half duplex).

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. Examples: PIC P/N E51424 and ECS P/N 422404

• For twisted-pair construction, the conductor twists should be maintained right up to the rear connector. Examples: PIC P/N E40424 and ECS P/N 922404

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.

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

• 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

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AFIRS 228S Iridium Global Communications System Installation Manual

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. REPLACE WITH UPDATED DIAGRAM FROM AIRBUS – This was NOT updated when the NonEFB document was because only the non-EFB drawing was created at that time.

Figure 6-5 – Rear Ethernet Ports

6.9 Discrete Inputs

The Iridium SATCOM System has 16 Discrete Inputs, of which 14 are software-configurable for OpenGround or Open-28V signaling levels, Active High or Active Low logic, and the assigned function.

6.9.1 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 Section 6.9.2) 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 Section 6.9.2), 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.”

• When any of the LGCIU discrete inputs are in the inactive state, the aircraft is considered as “in the air.”

6.9.2 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 6-6.

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The Mic On and Call Light functions are used in conjunction with the Extension 1 audio interface and are discussed in Section 6.11.1.1 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), configure the input 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 Section 6.9.1 for the logic used when a LGCIU2 input is provided.

Figure 6-6 – Discrete Input Interfaces

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6.10 Discrete Outputs

The 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.

6.11 SATCOM

This section describes the interface and integration requirements for the Iridium SATCOM System with an Audio Integrating System.

6.11.1 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.

6.11.1.1 Audio Discrete Signals

There is one discrete input and one discrete output that can be used to support the integrated audio interface.

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 List Output is Software configurable for either steady or flashing lights.

• Incoming Call is Ringing = Call Light output will transition to the active state, either in a steady state or flashing at approximately a 1 Hz rate.

• Call is Answered = Call Light output remains active in the steady state as long as the call is in progress.

• Call is Terminated = Call Light output will go inactive.

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6.11.1.2 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.

Figure 6-7 – Latched ACP Audio Interface

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7. SATCOM SYSTEM CONFIGURATION

The Iridium SATCOM System Satellite Data Unit (SDU) is configured via the Maintenance Port Ethernet connection, 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), as well as general information on the steps required to configure and update the Iridium SATCOM System.

An RJ-45 Maintenance Port jack is located behind the access door on the front panel of the SDU.

Figure 7-1 – Maintenance Port Location

Note:

Upon initial configuration of an installed system, perform and complete the Before Power-On Tests in Section 8.1, before applying power to the Iridium SATCOM System.

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7.1 Access the Maintenance User Interface (MUI)

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.

1. On the laptop computer set the IP address to one of the following:

a. Set the Internet Protocol to: Obtain an IP Address Automatically

Formatted: No underline, Font color: Auto

b. Use the following IP address:

IP address: 196.168.128.10

Subnet mask: 255.255.255.0

2. Connect an Ethernet cable to the Maintenance Port via the front panel access door of the SDU

- system power may be on or off.

3. Connect the other end of the Ethernet cable to a laptop with a web browser.

Note:

Mozilla Firefox ® is the recommended Internet browser with the SDU.

4. If not already powered, apply power to the SDU.

5. Confirm that there is either a steady, or flashing, green link light (adjacent to Maintenance Port RJ45 connector). A flashing light indicates that data is being transmitted.

6. Open a web browser on the laptop. In the Address bar, type the following IP address:

192.168.128.1

Note:

Before opening the web page, clear the web browser’s cache, or Ctrl+F5 and re-open the web page.

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The Iridium SATCOM System home page appears with the General tab information displayed.

Figure 7-2 – Home Page – General Tab

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

No user name or password is required to open the MUI home page.

General Tab

• UTC Date and Time: This is correlated to a GPS clock if the 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).

*Important: The phone number displayed may not be correct - check the SIM card.

• ISVM IMEI: Iridium Satellite Voice Modem International Mobile Equipment Identity (15 digits).

• ISDM IMEI: Iridium Satellite Data Modem International Mobile Equipment Identity (15 digits).

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System

ISVM and ISDM LINK

GPS LINK

AFIRS 228S Iridium Global Communications System Installation Manual

• Iridium SATCOM System Status Indicators

Yellow = (INIT) initializing Green = OK

Yellow = FAULT Yellow (blank) = system is in Maintenance Mode

Red = SDU Configuration Module (SCM) or Satellite Data Unit (SDU) Hardware failure or other critical error.

Yellow = NO LINK, no Iridium link if CSQ (Channel Signal Quality) is 0-1

Green = OK, if CSQ is 2-5

Yellow = NO FIX

Green = OK

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.

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).

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7.1.2 Faults Page

The Faults page provides access to the system fault log and fault history.

• FAULT tab displays only currently-raised faults

• HISTORY tab displays all raised and cleared faults since the last system reboot

Figure 7-3 – Faults Page (Fault Tab)

Figure 7-4 – Faults Page (History Tab)

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7.1.3 Part Numbers Page

The Part Numbers page provides the software and hardware configuration status of the Iridium SATCOM System.

Figure 7-5 – Part Numbers Page (Software Tab)

Figure 7-6 – Part Numbers Page (Hardware Tab)

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7.2 Maintenance Mode

To enter Maintenance Mode, the aircraft must be deemed “On-Ground.” If the aircraft is deemed “InAir”, 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.

The following users can enter Maintenance Mode after log in:

Maintenance User (View Upgrades page, modify 5 parameters on the ORT page)

Administrator User (View Upgrades page, modify parameters on the UAT page)

Role-based MUI permissions are provided in Table 7-1 through Table 7-3 at the end of this section.

Enter Maintenance Mode

1. Once connected to the Iridium SATCOM System MUI, on the Home page, enter your user name and password and 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.

3. Click Enter Maintenance Mode. The following message displays, prompting for confirmation to enter Maintenance Mode.

4. Click OK. The Home screen displays. The SYSTEM status indicates Yellow (blank).

Note:

Entering Maintenance Mode disables all MCDU functions.

Figure 7-7 – Maintenance Mode Initial Display Screen

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Exit Maintenance Mode

1. Upon completion of uploading of data or software files or modifying parameters, click Exit Maintenance Mode for the changes to take effect.

The following dialog box will display, prompting for confirmation to save changes.

2. Click OK, then the system will restart. The following screen will display.

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.

7.2.1 Maintenance Mode Upgrades Page

1. Click Upgrades from the Maintenance menu to upload software or data files. The following page will display.

2. Click Browse to navigate and select the software or data file to be uploaded.

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3. Click Upload. Success

• 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.

Incomplete

4. Click Apply to start the verification process.

5. Click Reset in to upload another file.

6. Click Exit Maintenance Mode. The system must re-boot for changes to take effect.

7. Maintenance User can modify only 5 ORT parameters:

8. Administrator User can modify any UAT parameter:

9. Click Exit Maintenance Mode. The system reboots and returns to Operational Mode.

• Non-compatible files will be rejected and an error message will display.

Success

• The blue progress bars turn green.

Incomplete

• Non-compatible files will be rejected and an error message will display.

Note:

If the aircraft’s status changes to “In-Air” before uploading is complete, the system will reboot automatically and return to Operational Mode - disregarding incomplete uploads.

a. Click ORT (Owner Requirements Table) to configure customized settings for specific

aircraft and or operator requirements.

a. Click UAT (User Access Table) to configure user access privileges.

Note:

If the aircraft’s status changes to “In-Air” before uploading is complete, the system will reboot automatically and return to Operational Mode - disregarding incomplete uploads.

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Table 7-1 - Read Privileges by Role

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Table 7-2 - Download Privileges by Role

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Table 7-3 – Modify Privileges by Role

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7.3 Configure the Iridium SATCOM System

The following sections are intended to provide 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

Reminder:

To enter Maintenance Mode, the aircraft must be deemed “On-Ground”.

The following users can enter Maintenance Mode after log in:

Maintenance User – 5 ORT parameters

Administrator User – UAT parameters

7.3.1 Address Book

• Can be uploaded as a comma-separated-values file (adb.csv).

• Can contain up to 300 Address Book entries.

• Can be viewed by Maintenance and Administrator users after login in Operational mode.

• Entries can be modified, if unprotected, via the MCDU in Operational mode.

• 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 upper-case alpha-numeric characters; A-Z, 0-9, +, -, /, space

• Priority – 4 (Public), 3 (Non-Safety), 2 (Safety), 1 (Emergency)

• Protected – 0 (No) = Entry can be modified or deleted via the MCDU in Operational Mode.,

1 (Yes) = Entry cannot be modified via the MCDU in Operation Mode.

• Directory - 4 (Public), 3 (Non-Safety), 2 (Safety), 1 (Emergency)

• Speed Dial 1 – 1 (address book appears in the cockpit for pilot’s use)

• Speed Dial 2 – 0 (currently not used)

• Speed Dial 3 – 0 (currently not used)

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View the Address Book in the MUI

1. In Operational Mode, log in as Maintenance User or Administrator User.

2. Click Address Book. The Address Book will display.

3. Address Book entry fields:

• 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 upper-case alpha-numeric characters

• Default Call Priority and Directory: Options displayed are Emergency, Safety, Non-

Safety, and Public.

• Protected:

YES = Entry cannot be modified via the MCDU in Operational Mode NO = Entry can be modified or deleted via the MCDU in Operational Mode

• Extension 2 and 3 Speed Dial: Currently not used.

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7.3.2 Owner Requirements Table (ORT) Parameters

The Owner Requirements Table (ORT) contains the parameters that may be customized by the individual aircraft operator.

Formatted: No underline, Font color: Auto

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.

Modification of the ORT will cause the MOD label to display on the MCDU under the ORT P/N.

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. If the ORT has been modified, the text “MOD” will be displayed on the MCDU, under the ORT Part Number.

The default file name of a downloaded ORT file is “ort.bin”.

Note:

An ORT Configuration Worksheet is provided in Appendix B to assist the operator in selecting and documenting the correct ORT configuration settings.

Formatted: No underline, Font color: Auto

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ORT Group

ORT Parameter Name

Value

Air

to Ground Calls

Call Progress Tones

 NORTH AMERICAN

Other Call Parameters

Allow Low Priority Calls in Cockpit

 YES

Additional ACARS Header Parameter

 NONE

AFIRS 228S Iridium Global Communications System Installation Manual

Access and Modify ORT Parameters

 EUROPEAN

Allow Manual Dialing Extension 1  YES

Safety Services (Iridium SATCOM System)

ATS Enabled  YES

1. Log in with user name and password as Maintenance User while aircraft is “On-Ground”.

2. Click Enter Maintenance Mode.

3. Click the ORT link on the left 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 (default) or European.

5. ALLOW MANUAL DIALING - EXTENSION 1:

YES = Manually-dialed phone calls can be placed from the cockpit, and via the directory. 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.

 NO

 ARINC

 NO

Formatted: No underline

IMPORTANT! For 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.

6. OTHER CALL PARAMETERS – ALLOW LOW PRIORITY CALLS IN COCKPIT:

Low-priority calls are considered PUBLIC or Priority 4. YES = Low-priority calls can be received in the cockpit, and low-priority calls can be placed from the cockpit. 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.

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7. SAFETY SERVICES (Iridium SATCOM System) – ADDITIONAL ACARS HEADER PARAMETER: The default configuration of NONE corresponds to SITA; alternatively, select ARINC.

8. ATS ENABLED: YES = Safety / ATS (Air Traffic Service) SIM card installed in the SCM. NO = Non-Safety / NON-ATS (Air Traffic Service) SIM card installed in the SCM.

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 User Access Table (UAT) is used by an Administrator User to set up user access privileges for up to 20 users. These settings may be changed as required to meet operational requirements.

Access and Modify UAT Parameters

1. Log in with user name and password as Administrator User while the aircraft is “On-Ground”.

2. Click Enter Maintenance Mode.

3. Click the UAT (Security) link on the left side of the screen to open the UAT page.

4. USER NAME: From 4 to 20 upper-case alphanumeric characters

5. PASSWORD: From 4 to 20 upper-case alphanumeric characters

6. SECURITY LEVEL: Select either DATA COLLECTOR (default) or MAINTENANCE or ADMINISTRATOR.

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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.

7.4 Upgrade Iridium SATCOM System Software

The Iridium SATCOM System software may be upgraded in the field using the Upgrade function of the MUI in Maintenance Mode.

Maintenance and Administrator Users have privileges to login and upload software and data files while aircraft status is “On-Ground”.

7.4.1 Upgrade Materials

Make sure to 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 Mozilla Firefox ® (see Section 7.1 Access the Maintenance User Interface).

• 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.

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7.4.2 Upgrade the Iridium SATCOM System Software

1. From the left menu, click Upgrades. The Upgrades screen will display.

2. Click Browse to locate the software file to upload (upgrade.tgz).

3. Select the software file and click Upload.

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.

Note:

Incompatible files will be rejected. The progress bars will turn red, and an error message will display 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 has successfully completed, the progress bars turn green, and a message displays that the system must be restarted for the changes to take effect.

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 incomplete upgrades.

To activate the newly installed software, you must Exit Maintenance Mode and restart the SDU.

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5. 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.

6. Click OK.

The SDU automatically restarts and applies the newly-installed software. A message displays indicating that the AFIRS system is rebooting.

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 verify any faults that might be 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.

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7.5 Exit Maintenance Mode

1. To save changes and uploaded configuration data, exit maintenance mode for the changes to take effect

1. In the top-right corner of the screen, click Exit Maintenance Mode.

2. A Message displays prompting for confirmation to exit Maintenance Mode

Note:

If you click Cancel, changes are still active but not saved.

3. Click OK to exit Maintenance Mode, save your changes, and reboot the system. The following message displays.

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4. Once the system reboots to Operational Mode, verify your changes and confirm that the correct software and data files have been installed.

5. Click the Part Numbers page and review the Software tab for the correct Part Numbers. The Part Numbers screen displays.

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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 502-1180-x flash cards should be used in the 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 yellow, indicating that the system is initializing.

Note:

The first time an SDU is installed in an aircraft, the SYSTEM LED indicator will typically remain yellow 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.

8.1.2 Aircraft Systems Interface Tests

Note:

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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 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 <SAT prompt should be available at one of the Line Select Keys (LSKs). Press the LSK to display the SATCOM MAIN MENU page.

2. On the SATCOM MAIN MENU, press the LSK for the SATCOM STATUS page.

The SATCOM STATUS page should be displayed with log-on state as well as voice and datalink status information.

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3. On the SATCOM STATUS page, press the LSK of the CONFIG prompt. The SATCOM CONFIG page 1 of 7 should be displayed.

If the ORT has been modified, the text “MOD” will be displayed on the MCDU, under the ORT Part Number.

4. Press Arrow Down or Arrow Up to view current configurations to page 7.

5. On the SATCOM STATUS page, press the LSK of the BITE prompt to display the SATCOM BITE STATUS page to display the status of the SDU, SIM CARDS, and SCM.

Formatted: No underline, Font color: Auto

Formatted: Not Highlight

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6. On the SATCOM BITE STATUS page, press the LSK of the SYS BUS prompt. The SATCOM SYS BUS page should display with status information of the MCDU#1, MCDU#2, MCDU#3, ATSU#1, and ATSU#2 and EFB.

7. Press the <RETURN LSK several times to return to the SATCOM MAIN MENU page.

8.1.2.4 Ethernet Port Tests

1. Confirm connectivity to each Ethernet device as follows:

2. Confirm that the SDU front panel ETHERNET LEDs for the connected ports are green. Flashing green indicates data is being transferred.

3. Perform any tests specific to the connected system to confirm that it is communicating with the SDU over the Ethernet port.

8.1.2.5 Discrete Input Tests

For each discrete input connected (1-16), confirm the correct aircraft system interface as follows:

1. Using the Maintenance User Interface (MUI), click on the Discrete In tab on the Home page.

2. Select the discrete input to its inactive state. Confirm proper operation of the interfaced aircraft system.

3. Select the discrete input to its active state. Confirm proper operation of the interfaced aircraft system.

8.1.2.6 Discrete Output Tests

For each discrete output configured and connected (1-8), confirm the correct state is detected as follows:

1. Manipulate the system providing the discrete output as required to indicate the output active state

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8.1.3 Operational System Tests

Note:

The tests in this section require the aircraft to be powered and outside the hangar in a location that has a clear view of the Iridium and GPS satellites. Aircraft systems that interface with the Iridium SATCOM System must be installed and operational.

These tests also require the AFIRS system to be activated on the Iridium network by SIM card provider, and a valid SIM card installed in the SCM. Ensure that the ORT configuration ATS Enabled (Yes/No) matches the SIM card type installed.

8.1.3.1 Date, Time, and Position Tests

1. Open the MUI to display the AFIRS Home page.

2. Confirm that the correct date, time, and position (UTC) information is displayed.

3. If the Internal GPS is configured as Active, the MUI display is showing AFIRS GPS and the GPS Link is displayed green.

8.1.3.2 Datalink Tests

1. Confirm on the MUI that the ISVM and ISDM Links are green, and the MCDU SATCOM STATUS page displays LOGGED-ON.

8.1.3.3 SATCOM Voice Tests

1. Confirm that the MCDU SATCOM MAIN MENU page displays Ready to Connect.

2. Place an air-to-ground call by using the MCDU. Confirm proper MCDU indications for a call in progress.

3. Terminate the call from the cockpit. Confirm proper cockpit indications and return to Ready to Connect state.

4. Place a ground-to-air call. Confirm proper cockpit indications for an incoming call. Answer the call and confirm proper cockpit indications for a call in progress.

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5. Place a ground-to-air call and reject the incoming call. Confirm proper cockpit indications.

6. Place a ground-to-air call. Allow call to go unanswered. Confirm proper ring sequencing, eventual call termination, and proper cockpit indications.

7. If SIM card installed is ATS-enabled, place a ground-to-air call. While the call is in progress, place a higher priority ground-to-air call. Confirm that the existing call is terminated and preempted by a call of higher priority.

8. Terminate call from the ground. Confirm proper cockpit indications.

8.1.4 EMI Tests

Each Iridium SATCOM System aircraft installation should be tested for electromagnetic interference in accordance with procedures developed by the aircraft systems integrator. The tests should be developed to ensure that there is no objectionable interference between the Iridium SATCOM System and other aircraft systems. This can include ground tests with engine running and flight tests as required.

8.2 Instructions for Continued Airworthiness

The aircraft systems integrator is responsible to provide Instructions for Continued Airworthiness (ICA) for the Iridium SATCOM System specific to the aircraft installation. The general content in this Installation Manual may be referenced by the aircraft systems integrator when developing the ICA.

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Appendix A – Wiring Diagram

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ORT Group

ORT Parameter Name

Value

Air to Ground Calls

Call Progress Tones

 NORTH AMERICAN

Allow Manual Dialing

Ext

ension

 YES

Additional ACARS Header Parameter

 NONE

ATS Enabled

 YES

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Appendix B – ORT Configuration Worksheet

 EUROPEAN

 NO

Other Call Parameters Allow Low Priority Calls in Cockpit  YES

Safety Services (Iridium SATCOM System)

 NO

 ARINC

 NO

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Appendix C – System Faults

AFIRS 228S Iridium

Iridium SATCOM Built-In-Tests (BIT)

Most of the checks are run as part of the Power-On Self-Test (POST) functionality or the Continuous Built-In Test (C-BIT) functionality.

- POST checks are run when the system is in Initialization Mode

- C-BIT checks are run at regular intervals during Operational Mode and Maintenance Mode

As BIT Checks are performed, the system will identify any "Raise Fault/Failure" conditions (system errors) that will affect functionality. Sometimes an error can cleared immediately, and there will be no record of it in the fault log. If a system error cannot be resolved immediately, a Failure, Fault, or Status Message will be recorded and tagged with the specific Date, Time, Position (DTP), and the value will be stored as the ORT Aircraft ICAO Address parameter.

During the next periodic Continuous tests the system will determine if a recorded system error is still affecting functionality. If it is not, the Failure, Fault, or Status Message may be cleared. In the event that a condition is cleared, the system will record it as cleared, and tag it with the specific Date, Time, Position and the value of the associated ORT Aircraft ICAO Address parameter.

Data Area Checks: Ensures that the various data areas utilized by the Iridium SATCOM system are accessible

Power Checks: Monitors voltage inputs to the Iridium SATCOM system and internal voltage rails of the power supply

Temperature Checks: Responds to system critical temperatures reported by the temperature sensors built into the SDU

Internal Interface Checks: Monitors communication with system devices, including the Internal GPS, ISVM, ISDM, the SCM

External Interface Checks: Monitors communication between the Iridium SATCOM system and external systems

Satellite Link Checks: Monitors the availability of the GPS and Iridium satellite links

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L3 Technologies AFIRS228S User Manual

Specifications and Main Features

Frequently Asked Questions

User Manual