EMS Technologies Canada FMPA Licensed Non-Broadcast Station Transmitter User Manual MN 1394 10078

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ARINC 781 SDU, SCM, and FMPA

System Description, Installation, and Maintenance Manual

MN-1394-10078, Revision 001

This document provides procedures for the equipment listed below.

Model Part Number

ARINC 781 Satellite Data Unit 1394-A-1100

ARINC 781 Flange Mounted High Power Amplifier 1394-A-1200

ARINC 781 SDU Configuration Module 1394-A-1300

PRODUCTION - Released - 21 Oct 2014 11:29:40 UTC

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PROPRIETARY STATEMENT

This document contains information which is proprietary and confidential to EMS Aviation (EMS Technologies

Canada, Ltd., Formation Inc., Sky Connect LLC). Neither this document nor the information contained within

may be used for any purpose other than the purpose for which it was prepared. Neither this document nor the

information contained within may be disclosed or copied without the prior written permission of EMS Aviation.

ARINC 781 SDU, SCM, and FMPA System Description, Installation, and Maintenance Manual

Document Number: MN-1394-10078, Revision 001

Revision Table

Revision ECR Description

001 N/A First release.

Windows® is a registered trademark of Microsoft Corporation in the United States and other countries. Other

product, brand, service, and company names herein are the trademarks of their respective owners.

Our products are under continuous research and development. Any information may therefore be changed

without prior notice. EMS Aviation reserves the right to make improvements or changes in the product described

in this manual at any time without notice. While reasonable efforts have been made in the preparation of this

document to assure its accuracy, EMS Aviation assumes no liability resulting from any errors or omissions in

this document, or from the use of the information contained herein.

Printed in Canada.

EMS Aviation

400 Maple Grove Road, Ottawa, Ontario, K2V 1B8, CANADA

EMS Aviation Reception: (613) 591-9064

EMS Aviation Product Support: (888) 300-7415 (calls are routed to an on-call Product Support specialist

after regular business hours)

+44 1684 290 020 (UK)

(613) 591-3086 (outside North America)

EMS Aviation E-mail Help: support@emsaviation.com

EMS Aviation Web site: www.emsaviation.com

EMS Aviation Sales and Marketing: 800-600-9759

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CUSTOMER RESPONSE FORM

To help us improve the quality of our product documentation, EMS Aviation would appreciate your

comments and suggestions on this publication. Please complete the following customer survey and

send to EMS Aviation at:

EMS Aviation

400 Maple Grove Road

Ottawa, ON K2C 0P9

E-mail: techdocs@emsaviation.com

Publication information:

Publication number: MN-1394-10078

Publication title: ARINC 781 SDU, SCM, and FMPA System Description, Installation, and

Maintenance Manual

Latest issue date: 16 APR 10

Document revision: 001

Customer information:

Name:

Company:

Tel:

Fax:

Email:

Comments and suggestions:

Date:

Comments:

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RECORD OF REVISIONS

When revisions are received, insert revised pages, record the date, and initial.

Revision

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Date Date

Inserted Inserted

by (initial) Revision

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SERVICE BULLETIN LIST

Service Bulletin

Number Subject Manual Rev.

Number Manual Rev.

Date

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LIST OF EFFECTIVE PAGES

* An asterisk indicates pages changed, added, or deleted by the current revision.

F indicates a right foldout page with a blank back.

Section Page Date

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TABLE OF CONTENTS

INTRODUCTION

1. Illustration of Equipment .............................................................................INTRO-1

2. Acronyms and Abbreviations......................................................................INTRO-2

3. Safety Advisories .........................................................................................INTRO-4

SYSTEM DESCRIPTION

1. Inmarsat System Overview...................................................................................1-1

2. Equipment Overview.............................................................................................1-2

A. SDU .................................................................................................................................1-3

B. SCM .................................................................................................................................1-3

C. FMPA ...............................................................................................................................1-4

3. Equipment Specifications.....................................................................................1-4

4. System Interfaces..................................................................................................1-7

A. SDU .................................................................................................................................1-8

B. SCM .................................................................................................................................1-9

C. FMPA ...............................................................................................................................1-9

5. User Interfaces.....................................................................................................1-10

A. MCDU ............................................................................................................................1-10

B. 4-Wire Audio ..................................................................................................................1-10

C. Ethernet .........................................................................................................................1-10

D. POTS .............................................................................................................................1-10

E. CEPT-E1 ........................................................................................................................ 1-11

F. ISDN ............................................................................................................................... 1-11

G. Maintenance Port ........................................................................................................... 1-11

H. LEDs .............................................................................................................................. 1-11

I. Self-Test Button ............................................................................................................... 1-11

6. Software Description...........................................................................................1-12

SYSTEM OPERATION

1. Using the ARINC 781 Avionics System...............................................................2-1

A. Operating the MCDU .......................................................................................................2-1

(1) Output Ports.................................................................................................................2-1

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(2) Input Ports.................................................................................................................... 2-1

(3) Screen.......................................................................................................................... 2-1

(4) Keyboard......................................................................................................................2-2

(5) Special Symbols........................................................................................................... 2-2

(6) Navigating the MCDU .................................................................................................. 2-3

B. Logging On and Off ..........................................................................................................2-4

(1) Logging On Automatically ............................................................................................2-4

(2) Logging On Manually ...................................................................................................2-5

(3) Logging Off...................................................................................................................2-5

(4) Viewing Log Status.......................................................................................................2-5

C. Making Cockpit Calls .......................................................................................................2-6

(1) Making Calls from the Telephone Directory ................................................................. 2-6

(2) Ending Calls.................................................................................................................2-8

D. Viewing BITE Information ................................................................................................ 2-8

INSTALLATION

1. Advisories..............................................................................................................3-1

2. Pre-Installation Inspection ...................................................................................3-1

A. Unpacking and Inspecting Equipment ............................................................................. 3-1

B. Cabling Notes ..................................................................................................................3-1

3. Installation Procedure...........................................................................................3-2

4. Connection Details................................................................................................3-2

A. SDU .................................................................................................................................3-2

B. SCM ................................................................................................................................. 3-4

C. FMPA ...............................................................................................................................3-4

5. Installation and Engineering Drawings...............................................................3-6

A. Outline and Installation Drawings .................................................................................... 3-6

B. System Interconnect Drawings ........................................................................................3-6

TEST AND FAULT ISOLATION

1. Operational and Diagnostic Testing....................................................................4-1

A. General ............................................................................................................................4-1

B. Test and Fault Isolation Equipment Requirements .......................................................... 4-1

C. SDU MPU ........................................................................................................................ 4-2

(1) Connecting to the MPU................................................................................................ 4-2

(2) Using the SDU MPU .................................................................................................... 4-3

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(3) Menu Item Descriptions ............................................................................................... 4-4

D. Operational and Diagnostic Test Procedures ..................................................................4-6

(1) Test Setup Procedure...................................................................................................4-7

(2) Post Test ......................................................................................................................4-7

(3) Installation and Operational Verification Tests ............................................................. 4-7

2. Troubleshooting and Fault Isolation ...................................................................4-8

A. Subsystem Health ............................................................................................................4-8

B. SATCOM System Bus ....................................................................................................4-10

C. Thermal Status ............................................................................................................... 4-11

D. SCM Health ...................................................................................................................4-12

E. Subsystem Bus Status ...................................................................................................4-14

F. RF Path Status ............................................................................................................... 4-14

G. USIM and Data Bus Status ............................................................................................ 4-15

H. ORT ............................................................................................................................... 4-16

(1) ORT Use and Storage................................................................................................ 4-16

(2) Checking the ORT...................................................................................................... 4-17

I. Contact Product Support .................................................................................................4-17

3. Adjustment/Alignment Procedures ...................................................................4-18

4. Modification History............................................................................................4-18

MAINTENANCE AND REPAIR

1. Maintenance...........................................................................................................5-1

2. Repair .....................................................................................................................5-1

3. Instructions for Continued Airworthiness ..........................................................5-1

A. Airworthiness Limitations .................................................................................................5-2

B. Electrical and Mechanical Inspection and Check .............................................................5-2

C. Instructions for Continued Airworthiness .........................................................................5-2

4. Visual Inspection and Check................................................................................5-3

APPENDIX A: RETURN MATERIAL AUTHORIZATION .......................................................... A-1

1. Warranty Returns ................................................................................................. A-1

2. Non-Warranty Returns......................................................................................... A-1

3. Repackaging Requirements................................................................................ A-1

4. RMA Procedure .................................................................................................... A-1

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LIST OF FIGURES

Figure INTRO-1 Satellite Data Unit.....................................................................................INTRO-1

Figure INTRO-2 SDU Configuration Module.......................................................................INTRO-2

Figure INTRO-3 Flange Mounted Power Amplifier .............................................................INTRO-2

Figure 1-1 Simplified Aeronautical Satellite Communications System ........................................1-2

Figure 1-2 ARINC 781 Avionics System ......................................................................................1-3

Figure 1-3 ARINC 781 Avionics System Block Diagram..............................................................1-8

Figure 1-4 FMPA Block Diagram ...............................................................................................1-10

Figure 2-1 MCDU Screen ............................................................................................................2-2

Figure 2-2 MCDU Menus.............................................................................................................2-3

Figure 3-1 ARINC 781 SDU Outline and Installation Drawing, 1394-E-1100

Rev B00 (Sheet 1 of 2).....................................................................................................3-7

Figure 3-2 ARINC 781 SDU Outline and Installation Drawing, 1394-E-1100

Rev B00 (Sheet 2 of 2).....................................................................................................3-9

Figure 3-3 ARINC 781 FMPA Outline and Installation Drawing, 1394-E-1200

Rev D00 (Sheet 1 of 2)...................................................................................................3-11

Figure 3-4 ARINC 781 FMPA Outline and Installation Drawing, 1394-E-1200

Rev D00 (Sheet 2 of 2)...................................................................................................3-13

Figure 3-5 ARINC 781 SCM Outline and Installation Drawing, 1394-E-1300

Rev B00 (Sheet 1 of 2)...................................................................................................3-15

Figure 3-6 ARINC 781 SCM Outline and Installation Drawing, 1394-E-1300

Rev B00 (Sheet 2 of 2)...................................................................................................3-17

Figure 3-7 ARINC 781 System Interconnect Drawing, 1394-B-1001

Rev A00 (Sheet 1 of 3)...................................................................................................3-19

Figure 3-8 ARINC 781 System Interconnect Drawing, 1394-B-1001

Rev A00 (Sheet 2 of 3)...................................................................................................3-21

Figure 3-9 ARINC 781 System Interconnect Drawing, 1394-B-1001

Rev A00 (Sheet 3 of 3)...................................................................................................3-23

Figure 4-1 Maintenance Cable.....................................................................................................4-2

Figure 4-2 Menu 1 Screen Display ..............................................................................................4-4

Figure 4-3 Menu 2 Screen Display ..............................................................................................4-5

Figure 4-4 Menu 3 Screen Display ..............................................................................................4-5

Figure 4-5 SATCOM Subsystem Health Menu ............................................................................4-9

Figure 4-6 SATCOM System Bus Menu ....................................................................................4-10

Figure 4-7 SATCOM Overtemp Menu .......................................................................................4-12

Figure 4-8 SATCOM SCM Menu ...............................................................................................4-13

Figure 4-9 SATCOM Subsystem Bus Menu ..............................................................................4-14

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Figure 4-10 SATCOM RF Path Menu, System with FMPA........................................................ 4-15

Figure 4-11 SATCOM USIM/DATA Menu ................................................................................. 4-16

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LIST OF TABLES

Table 1-1 SDU Physical Characteristics and Specifications.......................................................1-4

Table 1-2 SCM Physical Characteristics and Specifications ......................................................1-5

Table 1-3 External FMPA Physical Characteristics and Specifications ......................................1-6

Table 1-4 ARINC 781 System RTCA/DO-160E Environmental Characteristics.........................1-7

Table 1-5 SDU System Interfaces ..............................................................................................1-9

Table 1-6 SDU LED Status .......................................................................................................1-11

Table 2-1 ARINC 781 System Log Status ..................................................................................2-5

Table 3-1 SDU Rear Connector Pin Deviations..........................................................................3-3

Table 3-2 SDU Front Connector DSUB and RJ45 Pin Assignment............................................3-3

Table 3-3 SCM D-Type Connector Pin Assignment ...................................................................3-4

Table 3-4 FMPA J1 Connector Pin Assignments........................................................................3-5

Table 4-1 List of Required Test Equipment ................................................................................4-2

Table 4-2 Maintenance Port Connection Settings ......................................................................4-3

Table 4-3 Menu 1 Item Descriptions...........................................................................................4-4

Table 4-4 Menu 2 Item Descriptions...........................................................................................4-5

Table 4-5 Menu 3 Item Descriptions...........................................................................................4-6

Table 4-6 Test Setup Procedure.................................................................................................4-7

Table 4-7 Post Test Procedure ...................................................................................................4-7

Table 4-8 Power-On Test Procedure..........................................................................................4-8

Table 4-9 SATCOM Subsystem Health Menu ............................................................................4-9

Table 4-10 Bus Status Indicators..............................................................................................4-10

Table 4-11 SATCOM OVERTEMP Menu .................................................................................4-12

Table 4-12 SATCOM SCM Menu .............................................................................................4-13

Table 4-13 SATCOM SUBSY BUS Menu.................................................................................4-14

Table 4-14 SATCOM RF PATH Menu ......................................................................................4-15

Table 4-15 SATCOM USIM/DATA Menu..................................................................................4-16

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INTRODUCTION

This manual provides the specifications, principles of operation, and information necessary to install

the ARINC 781 SATCOM Avionics System, including the Satellite Data Unit (SDU), SDU

Configuration Module (SCM), and Flange Mounted High Power Amplifier (FMPA).

This document is divided into the following sections:

• System Description

• System Operation

• Installation

• Test and Fault Isolation

• Maintenance and Repair

NOTE: An Illustrated Parts List is not included with this manual.

Only qualified avionics personnel who are knowledgeable in the technical and safety issues related

to the installation of aircraft communications equipment should perform the installation procedures

provided in this manual.

This manual includes general installation guidelines only; it is not intended to provide specific

procedures for every type of installation.

If necessary, the information in this manual will be revised. Before attempting the installation

procedures presented in this manual, verify that you have a complete and up-to-date release of this

document.

1. Illustration of Equipment

Figure INTRO-1 shows the SDU.

Figure INTRO-1 Satellite Data Unit

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Figure INTRO-2 shows the SCM.

Figure INTRO-2 SDU Configuration Module

Figure INTRO-3 shows the FMPA.

Figure INTRO-3 Flange Mounted Power Amplifier

2. Acronyms and Abbreviations

AES Aircraft Earth Station

AMSS Aeronautical Mobile Satellite Services

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AORE Atlantic Ocean Region-East

AORW Atlantic Ocean Region-West

APAC Asia-Pacific

BIT Built-In-Test

BITE Built-In-Test Equipment

BSU Beam Steering Unit

CEPT-E1 Comite Europeen des Postes et Telecommunications

CTU Cabin Telecommunications Unit

DLNA Diplexer/Low-Noise Amplifier

DITS Digital Information Transfer System

EASA European Aviation Safety Agency

EMEA Europe, Middle East, and Africa

ESD Electrostatic Discharge

FAA Federal Aviation Administration

FAR Federal Aviation Regulation

FMPA Flange Mounted High Power Amplifier

FMS Flight Management System

GES Ground Earth Station

GND Ground

HGA High Gain Antenna

HPA High Power Amplifier

ICA Instructions for Continued Airworthiness

ICAO lnternational Civil Aviation Organization

I/O Input/Output

IOR Indian Ocean Region

IRS Inertial Reference System

ISDN Integrated Services Digital Network

LES Land Earth Station

LRU Line Replaceable Unit

MCDU Multi-purpose Control Display Unit

MCU Modular Concept Unit

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3. Safety Advisories

Warnings, cautions, and notes in this manual provide the reader with the following information:

• A WARNING describes an operation, procedure, or condition that, if not obeyed, could

cause injury or death.

• A CAUTION describes an operation, procedure, or condition that, if not obeyed, could cause

damage to the equipment.

• A NOTE provides supplementary information or explanatory text that makes it easier to

MES Mobile Earth Station

MHz Megahertz

MOPS Minimum Operational Performance Standards

MPU Maintenance Port Utility

ORT Owner Requirement Table

POR Pacific Ocean Region

POTS Plain Old Telephone System

RF Radio Frequency

RMA Return Material Authorization

RTN Return

Rx Receive

SATCOM Satellite Communications

SBB SwiftBroadband (Inmarsat)

SCM SDU Configuration Module

SDU Satellite Data Unit

SLU Software Logical Unit

STC Supplemental Type Certificate

Tx Transmit

USIM Universal Subscriber Identity Module

UUT Unit Under Test

VSWR Voltage Standing Wave Ratio

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understand and perform procedures.

All personnel who install, operate, and maintain the ARINC 781 SDU, SCM, FMPA, and

associated test equipment must know and obey the safety precautions listed below. The

procedures provided in this manual assume that the person performing installation or

maintenance tasks is familiar with and obeys standard aviation shop and safety practices.

The general safety advisories include the following:

WARNING: THE ARINC 781 AVIONICS SYSTEM INCLUDES COMPONENTS THAT

RADIATE RF AND MICROWAVE EMISSIONS IN THE BANDWIDTH OF 1626.5

TO 1660.5 MHZ.

WARNING: BEFORE HANDLING ANY UNIT OR COMPONENT, GROUND THE REPAIR

OPERATOR THROUGH A CONDUCTIVE WRIST STRAP OR OTHER DEVICE

THAT USES A 470 KILOHM OR 1 MEGAOHM SERIES RESISTOR TO

PREVENT INJURY.

CAUTION: TURN OFF POWER BEFORE DISCONNECTING ANY EQUIPMENT FROM

WIRING. DISCONNECTING THE EQUIPMENT WITHOUT TURNING POWER

OFF MAY CAUSE VOLTAGE TRANSIENTS THAT CAN DAMAGE THE

EQUIPMENT.

CAUTION: THIS EQUIPMENT INCLUDES ITEMS THAT ARE ELECTROSTATIC

DISCHARGE SENSITIVE (ESDS) DEVICES. ESDS DEVICES ARE SUBJECT

TO DAMAGE BY EXCESSIVE LEVELS OF VOLTAGE AND/OR CURRENT.

THE LOW-ENERGY SOURCE THAT MOST COMMONLY DESTROYS ESDS

DEVICES IS THE HUMAN BODY, WHICH, IN CONJUNCTION WITH

NONCONDUCTIVE GARMENTS AND FLOOR COVERINGS, GENERATES

AND RETAINS STATIC ELECTRICITY. TO ADEQUATELY PROTECT ESDS

DEVICES, THE DEVICE AND EVERYTHING THAT CONTACTS IT MUST BE

BROUGHT TO GROUND POTENTIAL BY PROVIDING A CONDUCTIVE

SURFACE AND DISCHARGE PATHS. USE STANDARD INDUSTRY

PRECAUTIONS TO KEEP RISK OF DAMAGE TO A MINIMUM WHEN

TOUCHING, REMOVING, OR SERVICING THE EQUIPMENT.

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SYSTEM DESCRIPTION

This section includes basic information about the ARINC 781 avionics system, including the

following sections:

• Inmarsat System Overview

• Equipment Overview

• Equipment Specifications

• System Interfaces

• User Interfaces

• Software Description

1. Inmarsat System Overview

This section provides an overview of the Inmarsat satellite communications system and

networks.

Satellite communication systems provide users with long-range voice and data communication

by accessing global satellite and ground communications networks. Satellite communication

systems include global satellite networks, Land Earth Stations (LESs), Ground Earth Stations

(GESs), Aircraft Earth Stations (AESs), and Mobile Earth Stations (MESs).

The LES/GES is the part of the satellite communication system that is on the ground. These

numerous, international stations are responsible for routing voice and data calls from the

MES/AES to their destinations around the world. The MES/AES is the part of the satellite

communication system that is on the aircraft. GES and AES are the terms associated with

Aero-H+ services. LES and MES are terms associated with other satellite communication

services.

Inmarsat is an international organization that operates and maintains multiple geostationary

satellites and satellite networks (I-3 and I-4). For more information about I-3 and I-4 satellite

beam coverage, refer to the Inmarsat website—www.inmarsat.com.

I-3 satellites provide Inmarsat services for aviation (Aero H+ and Swift 64), shipping, and

land-mobile users. The satellites connect to ground telecommunication systems through a

network of GESs. Each I-3 satellite is located over an Ocean Region (OR)—the current OR

names are:

• Atlantic Ocean Region-East (AOR-E)

• Atlantic Ocean Region-West (AOR-W)

• Indian Ocean Region (IOR)

• Pacific Ocean Region (POR)

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In addition to the services offered by I-3 satellites, the I-4 satellites provide worldwide

SwiftBroadband (SBB service). Each I-4 satellite has 19 wide spot beams, 228 narrow spot

beams, and is capable of accommodating many separate, simultaneous SBB sessions. The

SBB service and I-4 satellites support broadband applications such as video conferencing. The

current I-4 satellites are:

• AMERICAS

• EMEA (Europe, Middle East, and Africa)

• APAC (Asia-Pacific)

The satellite communication avionics (ARINC 781 systems), typically in conjunction with an

antenna subsystem, act as an AES/MES. The combined system provides users with a data and

voice communications link to the satellite network and global telecommunications system.

Figure 1-1 illustrates a simplified satellite communications system.

Figure 1-1 Simplified Aeronautical Satellite Communications System

2. Equipment Overview

The ARINC 781 SATCOM Avionics System, in combination with the antenna sub-system,

provides Aeronautical Mobile Satellite Services (AMSS) by facilitating airborne satellite

communications over the Inmarsat network, including the following services:

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• Classic Aero-H+—Provides packet data services at 600 bps, 1200 bps, or 10500 bps

over the PRT channel combination and half-rate circuit switched voice or data service

over the C channel.

• Swift 64—Provides packet switched Mobile Packet Data Service (MPDS).

• SwiftBroadband—Provides AMBE+2 voice (circuit-switched) and broadband packet

switched services. The equipment can achieve aggregate rates of 432 kbps, but data

rates may vary with network load.

The ARINC 781 SATCOM Avionics System consists of the Satellite Data Unit (SDU), the

Satellite Data Unit Configuration Module (SCM), and optionally, the Flange Mount Power

Amplifier (FMPA).

Figure 1-2 illustrates the ARINC 781 avionics system.

Figure 1-2 ARINC 781 Avionics System

A. SDU

The SDU is the central communications processing and control unit and largely

determines the functionality of the complete SATCOM system. It manages interfaces,

routing and priorities, and call channel establishment and tear down. When configured

without an FMPA, the SDU provides RF power amplification using an internal high power

amplifier (HPA).

The SDU is divided into several Shop Replaceable Units (SRUs) that are electrically

connected via the backplane. Various SRUs are also connected using RF cables.

B. SCM

The SCM is an external peripheral of the SDU and provides a dedicated interface to the

SDU. It stores Secure and User ORTs (Owner Requirement Tables) and a Swift 64

Forward ID. The SCM can accommodate up to four Universal Subscriber Identity Modules

(USIM) that store subscriber information for the SBB network.

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By storing configuration information independent of the SDU, the SCM facilitates efficient

SDU replacement. A new SDU that replaces a faulty SDU does not require any

configuration. All configuration information is obtained from the SCM.

C. FMPA

The FMPA is an optional component that provides amplification for configurations

requiring an external HPA. It is managed by the SDU and provides the final radio

frequency amplification in the AES system. The FMPA is divided into three SRUs—power

supply, control processor, and power amplifier. An overall packaging system encloses

the SRUs and the physical connections between them.

3. Equipment Specifications

This section includes the physical and environmental characteristics of the ARINC 781 SDU,

SCM, and FMPA.

Table 1-1 provides a summary of the physical characteristics and equipment specifications of

the SDU component.

Table 1-1 SDU Physical Characteristics and Specifications

CHARACTERISTIC SPECIFICATION

RELATED DOCUMENTS

ARINC characteristics ARINC 781 Mark 3 Aviation Satellite Communications System

RTCA documents DO-178B, Software Considerations in Airborne Systems and

Equipment Certification

DO-160E, Environmental Conditions and Test Procedures for

Airborne Equipment

FMPA SPECIFICATIONS

Physical Size

Length 32.46 cm (12.78 in)

Width 18.34 cm (7.22 in)

Height 13.72 cm (5.40 in)

Weight 6.81 kg (15.0 lbs)

Mounting Information 4 x 0.266” holes on 11.19” x 6.4” spacing

Electrical Interfaces

Power/Control

interface ARINC 781

Power Requirements 115 Vrms ac, 300 Hz to 900 Hz

Power Consumption < 250 VA

Table 1-4 lists the RTCA/DO-160E environmental characteristics of the SDU, SCM, and FMPA.

Mounting Information 4 x 0.125" holes on 3.3" x 3.5" spacing, per

attachment 1-6 of ARINC 781

Electrical Interfaces

Power/Control interface as per ARINC 781

Power Requirements + 12 V ± 5% (derived from SDU)

Table 1-2 SCM Physical Characteristics and Specifications (Continued)

CHARACTERISTIC SPECIFICATION

Table 1-4 ARINC 781 System RTCA/DO-160E Environmental Characteristics

Section Environmental Condition Category

SDU/SCM FMPA

4.0 Temperature and Altitude F2/A2 F2/A2

4.5.1 Ground Survival Low F2 F2

4.5.1 Short Term Operating Low Ambient F2 F2

4.5.2 Operating Low Ambient F2 F2

4.5.3 Ground Survival High F2 F2

4.5.3 Short Time Operating High F2 F2

4.5.4 Operating High Ambient F2 F2

4.5.5 In Flight Loss of Cooling PF2

4.6.1 Altitude F2 F2

4.6.2 Decompression A2 A2

4.6.3 Overpressure A2 (modified to

-20,000 ft) A2 (modified to

-20,000 ft)

5Temperature Variation B B

6Humidity A A

7Operational Shock and Crash Safety B B

8.5 Vibration Standard – Sine S, Curves L, M, Y S, Curves L, M, Y

8.5.2 Vibration Standard – Random S, Curve B S, Curve C

8.7.2 Vibration Robust – Random R, Curves B, B1 R, Curves C, C1

9.0 Explosive Atmosphere E E

15 Magnetic Effect Z Z

16.5 Power Input (ac) A(WF)H A(WF) (modified

extended

frequency 300

Hz to 900 Hz)

17 Voltage Spike A A

18 Audio Frequency Conducted Susceptibility (ac) K(WF) K(WF)

19 Induced Signal Susceptibility CW CW

20 Radio Frequency Susceptibility R R

21 Emission of RF Energy M M

22 Lightning Induced Transient Susceptibility A3J33 A3J33

25 Electrostatic Discharge (ESD) A A

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4. System Interfaces

This section describes the ARINC 781 system interfaces.

Figure 1-3 illustrates the block diagram of the ARINC 781 avionics system.

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Figure 1-3 ARINC 781 Avionics System Block Diagram

A. SDU

The SDU is divided into the following SRUs:

• Channel Cards (2)

• Control and Data Processor Card

• Voice and Router Processor Card

• Power Amplifier

• ARINC Backplane

• DIN Backplane

• 10 MHz Oven Controlled Crystal Oscillator

• Power Supply

The major interfaces of the SDU are listed in Table 1-5.

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B. SCM

The SCM does not provide any interfaces other than a dedicated interface to the SDU.

The SCM is powered by the SDU.

C. FMPA

The FMPA provides RF multi-carrier amplification capabilities permitting up to 32 W total

average RF power. The SDU manages the FMPA, providing the necessary command

control. The FMPA has four operational interfaces:

• ARINC 429 Control (x1)/BITE (x1) – FMPA to SDU control and reporting

• RF Input Signal (x1) – RF low power input from the SDU

• RF Output Signal (x1) – RF high power output to the antenna subsystem (DLNA)

• Power Supply (x1) – 115 Vac, 300 Hz to 900 Hz

Figure 1-4 illustrates a block diagram of the FMPA.

Table 1-5 SDU System Interfaces

System Interface Description

ACU/BSU (x1) Antenna Control Unit/Beam Steering Unit

FMPA (x1) Flange Mount Power Amplifier

MCDU (x3) Multi-Purpose Control and Display Unit

ACARS CMU (x2) Aircraft Communication Addressing and Reporting System

Communication Management Unit

IRS (x2)/GPS (x1) Inertial Reference System/Global Positioning System

SCM (x1) SDU Configuration Module

CMC (x1) Central Maintenance Computer

AES ID (x1) Aircraft Earth Station Identification

Servicing Front Panel Accessible Service Port for data log retrieval

Button Initiated Self-Test

RF Transmit to the FMPA, Receive from the DLNA

Antenna subsystem ARINC 781 Antenna Subsystem

Miscellaneous ARINC discrete input, outputs, and configuration straps

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Figure 1-4 FMPA Block Diagram

5. User Interfaces

This section describes the ARINC 781 SDU interfaces that enable users to access Inmarsat

services and monitor the operation of the ARINC 781 avionics system.

NOTE: There are no user interface associated with the SCM and FMPA.

A. MCDU

The MCDU is a device that uses an ARINC 429 interface per ARINC 739, which lets you

communicate with individual instruments on an aircraft, including the Flight Management

System (FMS), very high frequency (VHF) radio, and the SDU.

The SDU supports three MCDUs.

B. 4-Wire Audio

The SDU supports two 4-wire audio interfaces.

C. Ethernet

The SDU supports five Ethernet data interfaces.

D. POTS

The SDU supports two POTS interfaces.

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E. CEPT-E1

The SDU supports one CEPT-E1 interface.

F. ISDN

Two ISDN interfaces are currently not supported.

G. Maintenance Port

The SDU is equipped with a maintenance port, located on its front panel. The

maintenance port provides the physical connection to a password-protected

Maintenance Port Utility (MPU) that provides a system interface for users or service

personnel who need to monitor or troubleshoot the system.

For more information on configuring the maintenance port, refer to "Connecting to the

MPU" on page 4-2.

H. LEDs

The front panel of the SDU has two LEDs to indicate unit status:

• One green LED labelled Power

• One red LED labelled Fault

Table 1-6 provides information about the LED signals.

Table 1-6 SDU LED Status

Power LED Status Fault LED Status Description of SDU Status

On for 60 seconds, then off

during normal operation Off No fault detected

Off On while the fault exists LRU fault detected

Off Flashing at 1 Hz with a 50%

duty cycle while the fault

exists

System fault detected but not isolated

to the LRU

Alternating flashing of Power and Fault LEDs Self-test in progress

I. Self-Test Button

The front panel of the SDU has a recessed button labelled Test:

• To reset the unit, press and hold the Test button for at least 5 seconds

• To initiate self-test (when no LEDs are flashing), momentarily press the Test button

• To disable the existing LED condition (when LEDs are flashing), momentarily press

the Test button

NOTE: During initial power-up or self-test execution, a momentary press of the

self-test button is ignored.

The LEDs indicate the results of the self-test. Table 1-6 provides information about the

meaning of LED signals.

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6. Software Description

All operating software meets RTCA/DO-178B Level D requirements.

The SCM does not contain any software. Only configurable parameters are stored in the SCM.

All FMPA software is stored in the Control Processor SRU. It manages BITE, data loading,

maintenance, and ARINC 429 label transmission and reception.

The SDU software is not partitioned. The software is modular and modules run on individual

Software Logical Units (SLUs) within the SDU:

• Each channel card has a single SLU

• Control and Data Processor card has a Control SLU and a Data SLU

• Voice and Router card has a Voice SLU and a Router SLU

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SYSTEM OPERATION

The SDU is an integral component in an AES. Together with the SCM, DLNA, Antenna, and HGA

subsystem, it provides AMSS by facilitating airborne satellite communication services over the

Inmarsat network. These services comprise Classic Aero-H+, Swift 64, and SwiftBroadband (SBB).

The SCM is a dedicated peripheral of the SDU and stores aircraft specific installation configuration

critical to the operation of the AES.

The FMPA provides RF multi-carrier amplification capabilities permitting up to 32 W total average

RF power. The SDU manages the FMPA, providing the necessary command control.

This section provides basic information on using the ARINC 781 avionics system.

1. Using the ARINC 781 Avionics System

This section describes how to perform the following tasks:

• Operating the MCDU

• Logging On and Off

• Making Cockpit Calls

• Viewing BITE Information

A. Operating the MCDU

This section provides information about the MCDU and its interfaces—output and input

ports, the screen, and the keyboard.

(1) Output Ports

The MCDU transfers its identification and commands to the SDU using 32 bit words

on a 12-14.5 kbps output port, as defined in ARINC Specification 429, Digital

Information Transfer System (DITS).

(2) Input Ports

The MCDU receives identification information and displays data from individual

subsystems using seven input ports, as defined by ARINC Specification 429. Ports

1 and 2 are reserved for FMSs, and they operate at 100 kbps. Ports 3–7 are available

for the MCDU to communicate with the SDU, and they operate at 12-14.5 kbps.

(3) Screen

The MCDU displays all data on the screen, as shown in Figure 2-1.

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Figure 2-1 MCDU Screen

The top of the screen displays the title of the menu on the screen. The bottom of the

screen (Line 14) is the scratchpad that displays information that you enter on the

keyboard.

The MCDU has six buttons on each side of the screen that activate MCDU functions.

Figure 2-1 displays these buttons on the left and right sides of the screen. When the

functions corresponding to a button are available, the function is displayed beside

the button.

Other lines on the MCDU screen display information relevant to the function or status

of the ARINC 781 system.

(4) Keyboard

The MCDU’s keyboard includes a set of numeric keys and a set of alphabetic keys,

both of which you can use to enter data into the MCDU.

The keyboard may include preset keys, such as the following:

• The IDX or MAIN MENU key: this key returns you to the MCDU’s main menu.

• The CLR key: this key clears any text you type into the scratchpad.

• The NEXT PAGE key: this key brings up the next page of a menu if one is

available.

• The PREV PAGE key: this key brings up the previous page of a menu if one is

available.

(5) Special Symbols

Because of space constraints on the screen, the MCDU uses a number of special

symbols to indicate actions:

• < and > appear at the far left or right to indicate that another menu page is

available in that direction or that a function is available for that label.

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• NUMBER/NUMBER appears to tell you which page out of how many pages you

are viewing. For example, 1/3 would appear when you are on page 1 of 3 pages

in total.

(6) Navigating the MCDU

The MCDU includes a number of menus, as shown in Figure 2-2.

Figure 2-2 MCDU Menus

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B. Logging On and Off

Using the MCDU, you can log on to the satellite network manually or automatically:

• Manual Logon—constrains the logon to use a satellite that you select

• Automatic Logon—logs on using the best available satellite as defined by the ORT

If specified in the ORT, the initial system logon happens immediately after the

ARINC 781 system powers up, with no MCDU input required. If the ORT is not configured

as such, you must initiate the logon from the MCDU (MANUAL LOG-ON or AUTO

LOG-ON command).

You can watch the progress of the logon on the SATCOM LOG 1/2 page, or simply wait

until the prompt on the SAT-PHONE 1/2 page indicates the service is available for use.

(1) Logging On Automatically

When you initiate an automatic logon, the system selects a satellite and GES based

on the preferences specified in the ORT.

To log on automatically:

1. On the SAT-PHONE 1/2 page, press the key next to LOG.

The SATCOM LOG page appears.

2. On the SATCOM LOG page, press the key next to AUTO LOG-ON.

The MCDU returns to the SAT-PHONE 1/2 page and the SAT-L and SAT-R

channels are updated with READY status after the logon completes.

NOTE: The MCDU does not display the AUTO LOG-ON and MANUAL LOG-ON

functions when the ARINC 781 system is already logged on.

NOTE: On the SAT-PHONE 1/2 page, SAT-L shows the Classic Aero channel

status and SAT-R shows the SBB channel status. The ARINC 781

system logs on the Classic Aero channels first, and then logs on the SBB

channels.

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(2) Logging On Manually

To log on manually, you must select a satellite and GES.

To log on manually:

1. On the SAT-PHONE 1/2 page, press the key next to LOG.

The SATCOM LOG page appears.

2. Press the key next to SATELLITE ID until the MCDU screen shows the satellite

ID to which you want the ARINC 781 system to log on.

3. Press the key next to GES ID until the MCDU screen shows the GES to which

you want the ARINC 781 system to log on.

4. On the SATCOM LOG page, press the key next to MANUAL LOG-ON.

The MCDU returns to the SAT-PHONE 1/2 page and updates the SAT-L and

SAT-R channels with READY status after the log on completes.

NOTE: SAT-L shows the Classic Aero channel status and SAT-R shows the SBB

channel status. The ARINC 781 system logs on the Classic Aero

channels first, and then searches for SBB or Swift 64 services on the

satellite determined by the Classic Aero log-on.

(3) Logging Off

To log off:

1. On the SAT-PHONE 1/2 page, press the key next to LOG.

The SATCOM LOG page appears.

2. On the SATCOM LOG page, press the key next to LOG-OFF.

The ARINC 781 system logs off the satellite network.

(4) Viewing Log Status

The log status defines whether the ARINC 781 system is logged on or logged off.

Valid values are shown in Table 2-1.

Table 2-1 ARINC 781 System Log Status

Log Status Description

CALIBRATION If in FMPA mode, and cable calibration not yet completed

SAFE MODE Configuration error detected

HSR NOT READY High stability oscillator is in a warming condition

ANT NOT READY Antenna is reporting test state

AES ID NOT READY Displayed until a non-zero ICAO address is present

NAV DATA UNAVAIL Insufficient navigation data available

CC NOT READY Channel card has not fully booted

LOGGED OFF ARINC 781 system not logged on to the satellite network.

Awaiting input from the user

TUNING TO SAT Tuning and scanning for reception from the selected

satellite

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To view log status:

1. On the SAT-PHONE 1/2 page, press the key next to LOG.

The SATCOM LOG page appears.

2. The log status appears on the line below STATUS.

C. Making Cockpit Calls

You can make air-to-ground and air-to-air calls using the ARINC 781 system, the MCDU,

and one or two 4-wire headsets. You can manually dial calls or dial previously saved

telephone numbers from the MCDU’s telephone directory.

(1) Making Calls from the Telephone Directory

You can make voice calls from the numbers you have saved in the MCDU’s telephone

directory. Numbers can be saved in the telephone directory using the MCDU or the

ORT.

To make a call from the telephone directory:

1. On the SAT-PHONE 1/2 page, press the key next to DIRECTORY.

The SAT DIRECTORY INDEX page appears.

DET SYS TABLE Updating the Satellite table

SPOT BEAM SEARCH Selecting the optimal spot beam

WAIT LOGON CONF Awaiting the logon confirmation from the satellite

WAIT LOGON ACK Awaiting for logon acknowledge from the GES

LOGGED ON Successfully logged on to GES

REJECT-TEMPORARY Logon rejected by the GES, but the condition is temporary

REJECT-PERMANENT Logon rejected by the GES, and the condition is

permanent

REJECT-INV PARAM Logon rejected by the GES due to invalid parameters, and

the condition is permanent

REJECT-AES INVAL ICAO address was not accepted by the GES, the

condition is permanent

LOGGING OFF Starting the logoff process

Table 2-1 ARINC 781 System Log Status (Continued)

Log Status Description

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2. To access phone numbers in a directory, press the key next to a directory name.

The SAT DIRECTORY page appears.

NOTE: If an entry has the < symbol in the SAT-L column, that entry can be dialed

on Classic Aero channels. If an entry has the > symbol in the SAT-R

column, that entry can be dialed on SBB channels. If there is no symbol,

the entry cannot be dialed on that channel. For example, in the SAT

DIRECTORY shown below, NANDI CTR cannot be dialed on the SBB

channel because it’s priority is higher than PUB (public).

3. Press the key to the left or right of the number you wish to dial. Pressing the left

key loads the number on SAT-L and pressing the right key loads the number on

SAT-R.

The MCDU returns to the SAT-PHONE 1/2 page and the number is displayed

under the selected channel (SAT-L or SAT-R).

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4. Optionally, to change the priority of the call, press the key next to PRI. Valid

values are PUB (public), LOW (low), HGH (high), and EMG (emergency).

NOTE: You cannot change the priority of calls on SAT-R (SBB) channels. SBB

calls are always public priority.

5. Press the key next to MAKE CALL.

The call status is shown on the SAT-PHONE 1/2 page.

(2) Ending Calls

To end a call:

• On the SAT-PHONE 1/2 page, press the key next to END CALL.

When a call is ended, the MCDU briefly shows the status of why the call ended.

To clear the status, press the key next to CLR STATUS.

D. Viewing BITE Information

From the SATCOM BITE menu, you can view BITE information to determine subsystem

health.

To view BITE information:

1. On the MCDU main menu, press the key next to SAT-PHONE.

2. On the MCDU keyboard, press the NEXT PAGE key to advance to the second

page of the SAT-PHONE menu, and then press the key next to SATCOM BITE.

The SATCOM BITE page appears.

You can view the following information from this screen:

• SDU status on the line below SDU

• Overall health of all subsystem components (SCM, DLNA, HGA, and FMPA) on

the line below SUBSY HLTH

• Thermal status of the SDU, HGA, and FMPA on the line below OVERTEMP

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• SCM health on the line below SCM

• Peripheral LRU bus status on the line below SYS BUS

• Subsystem bus status on the line below SUBSY BUS

• The number of functional channels followed by the number of installed channels

on the line below CHANNELS

• RF path status on the line below RF PATH

• USIM and data bus status on the line below USIM/DATA

NOTE: Valid values for status are OK and FAIL. If the status of a subsystem is

FAIL, press the key next to the subsystem to view the details.

To view more information about the health of a particular subsystem, press the key next

to the name of the subsystem. For more information about the various MCDU menu

screens, see "Troubleshooting and Fault Isolation" on page 4-8.

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INSTALLATION

This section describes the procedures required to install the ARINC 781 system (SDU, SCM, and

optionally, FMPA) on an aircraft, including the following sections:

• Advisories

• Pre-Installation Inspection

• Installation Procedure

• Connection Details

• Installation and Engineering Drawings

1. Advisories

Before performing any installation procedures, read the safety advisories listed in the

Introduction on page INTRO–4 of this manual.

2. Pre-Installation Inspection

Before installing any ARINC 781 system, conduct a pre-installation inspection of all parts to

make sure that no damage occurred during shipping.

A. Unpacking and Inspecting Equipment

• Unpack the ARINC 781 equipment from the shipping containers.

• Verify that the part number displayed on the shipping box and equipment component

matches the model and part number ordered. If components are missing from the

shipment, contact the supplier immediately and report the problem.

• Visually inspect the ARINC 781 equipment for any shipping damage. If any shipping

damage has occurred, contact the shipping carrier immediately and report the

problem.

• Check the ARINC 781 equipment connectors for corrosion and damage. If damage

is noted, do not apply power to the equipment. Contact the supplier immediately to

report the problem.

B. Cabling Notes

Before proceeding with the installation of the ARINC 781 system, read all cabling notes

provided on the Interconnection and Contact Assignment drawings on page 3–19.

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3. Installation Procedure

Only authorized technical personnel, trained in general aviation workmanship, that have a basic

understanding of SATCOM systems should proceed with the following procedure.

Before performing any installation procedures, read the safety advisories listed in “Advisories”

on page 8 of this manual.

1. Install the SDU in a 6 MCU tray as per ARINC 600. The minimum clearance between

the SDU and any other equipment installed above it shall be no less than 0.5 inches.

2. Install the SCM in any orientation. Refer to Table 1-2 on page 1-5 for the SCM

mounting specification.

• There are no clearance requirements for the SCM.

• The SCM must be thermally insulated from the structure on which the SCM is

mounted. The SCM includes heaters to maintain the SIM cards at an appropriate

temperature. A large structure can act as a heat sink and reduce the effectivity

of the SCM heaters.

3. If using an external FMPA, install the FMPA in any orientation. Refer to Table 1-3 on

page 1-6 for the FMPA mounting specification. Refer to Figure 3-3 on page 3–11 for

required clearances.

4. Connect the SCM to the SDU. The SDU supports one RS-422 interface for

interconnect to the SCM.

5. Connect the SDU to the antenna subsystem. The SDU supports ARINC 429

communication to and from the antenna subsystem.

6. Connect the SDU to the MCDU(s). The SDU supports three ARINC 429 receive

interfaces and one ARINC 429 transmit interface for interconnect to the flight deck

MCDU(s).

7. If using an external FMPA, connect the SDU to the FMPA. The SDU supports one

ARINC 429 interface for communication to and from the FMPA.

4. Connection Details

A. SDU

The SDU uses two external interface connectors:

• Rear Connector—a low insertion force, size 2 shell receptacle accommodating

coaxial and signal interconnections in the top plug insert, Quadrax and signal

connections in the middle plug insert, and coaxial and power interconnections in the

bottom plug insert. Pin assignments are compliant with ARINC Characteristic 781

with top plug and middle plug deviations as shown in Table 3-1.

• Front Connector—an RJ45 and 9S DSUB connector providing 10BT Ethernet

interfaces and an RS-232 maintenance interface. Pin assignments are shown in

Table 3-2. The front connector is behind a maintenance cover. This connector

provides access to maintenance and troubleshooting information when the SDU is

not in normal operation.

Table 3-1 SDU Rear Connector Pin Deviations

Description Pin Deviation

Top Plug Insert Pin Deviations

Router Processor Maintenance TXD TP01A ATE pin 1

Router Processor Maintenance RXD TP01B ATE pin 2

Router Processor & Data I/O Processor

Maintenance GND TP01C ATE pin 3

Data I/O Processor Maintenance TXD TP01D ATE pin 4

Data I/O Processor Maintenance RXD TP01E ATE pin 5

CC1 Processors #1 & #2 Maintenance

GND TP01F ATE pin 6

CC1 Processor #1 Maintenance TXD TP01G ATE pin 7

CC1 Processor #1 Maintenance RXD TP01H ATE pin 8

CC1 Processor #2 Maintenance TXD TP01J ATE pin 9

CC1 Processor #2 Maintenance RXD TP01K ATE pin 10

Download Security TP02A ATE pin 11

Voice Processor Maintenance GND TP02C ATE pin 13

Voice Processor Maintenance TXD TP02D ATE pin 14

Voice Processor Maintenance RXD TP02E ATE pin 15

CC2 Processors #1 & #2 Maintenance

GND TP02F ATE pin 16

CC2 Processor #1 Maintenance TXD TP02G ATE pin 17

CC2 Processor #1 Maintenance RXD TP02H ATE pin 18

CC2 Processor #2 Maintenance TXD TP02J ATE pin 19

CC2 Processor #2 Maintenance RXD TP02K ATE pin 20

Middle Plug Insert Pin Deviations

GPS ARINC 429 Receiver MP06J/MP06K Spare

Data Loader Link Enable MP08E For Ethernet also

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Table 3-2 SDU Front Connector DSUB and RJ45 Pin Assignment

9S DSUB Pin

Number Description RJ45 Pin Number Description

1NC 1RX+

2TX 2RX-

3RX 3TX+

4NC 4NC

5GND 5NC

6NC 6TX-

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B. SCM

The SCM uses a 15 pin D-type male connector and locking screws. Pin assignments are

compliant with ARINC Characteristic 781 and shown in Table 3-3.

Table 3-3 SCM D-Type Connector Pin Assignment

Pin Number Description

1Data to SDU A (RS422)

2Data to SDU B (RS422)

3Data from SDU A (RS422)

4Data from SDU B (RS422)

5Reserved - RS232 Gnd (used for shop loading)

6Spare

7Chassis Ground

8Power Input +8 V to +15 V

9Reserved - Enable RS232 (used for shop loading)

10 Reserved - 0 V strap output (used for shop loading)

11 Spare

12 Reserved - RS232 Tx (used for shop loading)

13 Reserved - RS232 Rx (used for shop loading)

14 Spare

15 Power Return 0 V

C. FMPA

The FMPA provides three external connectors:

• J1 – Power/Control MIL-C-38999 Series III Insert Arrangement 17-26

• J2 – RF input, TNC female

• J3 – RF output, N Type female

7NC 7NC

8NC 8NC

9NC

Table 3-2 SDU Front Connector DSUB and RJ45 Pin Assignment (Continued)

9S DSUB Pin

Number Description RJ45 Pin Number Description

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These connectors and their pin layouts are compliant with ARINC Characteristic 781.

Table 3-4 describes the FMPA connector pin layout.

Table 3-4 FMPA J1 Connector Pin Assignments

Pin Number Signal Description

AHPA BITE A ARINC 429 from HPA

BHPA BITE B ARINC 429 from HPA

CRS422 RXD A Serial data to HPA +

DRS422 RXD B Serial data to HPA -

ERS422 TXD A Serial data from HPA +

FRS422 TXD B Serial data from HPA -

GSPARE SPARE

HSPARE SPARE

JChassis Ground Chassis Ground

KSPARE SPARE

LSPARE SPARE

MDiscrete BITE #1 Discrete BITE #1 from HPA

NDiscrete BITE #2 Discrete BITE #2 from HPA

PAntenna Control A ARINC 429 to HPA

RAntenna Control B ARINC 429 to HPA

SAntenna Control Shield Shield for ARINC 429

THPA BITE Shield Shield for ARINC 429

URS422 Shield RS422 Shield

VSPARE SPARE

WSPARE SPARE

X115VAC Hot Aircraft AC power

Y115VAC Return Aircraft AC power

ZSPARE SPARE

aDiscrete BITE #3 Discrete BITE #3 from HPA

bATE Pin Manufacturer specific

cSPARE SPARE

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5. Installation and Engineering Drawings

This section contains the Outline and Installation diagrams, and Interconnection and Contact

Assignment drawings for the SDU, SCM, and FMPA.

All foldout pages are odd-numbered and not-backed for print production purposes.

A. Outline and Installation Drawings

The Outline and Installation drawings on pages 3–7 to 3–17 show the physical

characteristics of the SDU, SCM, and FMPA, and provide installation data for the system.

B. System Interconnect Drawings

System Interconnect drawings on pages 3–19 to 3–23 show the interconnection details

for the SDU, SCM, and FMPA.

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Figure 3-1 ARINC 781 SDU Outline and Installation Drawing, 1394-E-1100 Rev B00 (Sheet 1 of 2)

Blank Page

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Figure 3-2 ARINC 781 SDU Outline and Installation Drawing, 1394-E-1100 Rev B00 (Sheet 2 of 2)

Blank Page

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Figure 3-3 ARINC 781 FMPA Outline and Installation Drawing, 1394-E-1200 Rev D00 (Sheet 1 of 2)

Blank Page

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Figure 3-4 ARINC 781 FMPA Outline and Installation Drawing, 1394-E-1200 Rev D00 (Sheet 2 of 2)

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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Blank Page

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Figure 3-5 ARINC 781 SCM Outline and Installation Drawing, 1394-E-1300 Rev B00 (Sheet 1 of 2)

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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Blank Page

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Figure 3-6 ARINC 781 SCM Outline and Installation Drawing, 1394-E-1300 Rev B00 (Sheet 2 of 2)

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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Blank Page

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Figure 3-7 ARINC 781 System Interconnect Drawing, 1394-B-1001 Rev A00 (Sheet 1 of 3)

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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Blank Page

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Figure 3-8 ARINC 781 System Interconnect Drawing, 1394-B-1001 Rev A00 (Sheet 2 of 3)

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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Blank Page

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Figure 3-9 ARINC 781 System Interconnect Drawing, 1394-B-1001 Rev A00 (Sheet 3 of 3)

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TEST AND FAULT ISOLATION

This section provides test procedures to determine the operational readiness of SDU units.

There are no operational test procedures defined for the SCM or FMPA. SCM and FMPA health are

determined by accessing the SDU BITE information.

If the ARINC 781 equipment passes all tests in this section but does not function according to the

installation requirements, the fault may be with equipment or wiring outside the ARINC 781 system.

This section includes:

• Operational and Diagnostic Testing

• Troubleshooting and Fault Isolation

• Adjustment/Alignment Procedures

• Modification History

NOTE: Depending on the version of software installed, the MPU report and menu screens displayed

may differ from those shown as examples in this manual.

1. Operational and Diagnostic Testing

This section includes the following sections:

• General

• Test and Fault Isolation Equipment Requirements

• Operational and Diagnostic Test Procedures

A. General

Usually, the ARINC 781 system requires testing for one of the following reasons:

• To verify the operational readiness of the system during and after installation on an

aircraft

• To verify that a fault exists and produce system reports for troubleshooting purposes

• To verify the operational readiness of repaired LRUs during re-installation on an

aircraft

This section includes test and fault isolation procedures for the ARINC 781 system. All

test and load procedures require the ARINC 781 SDU MPU, which is accessed by

connecting to the maintenance port of the SDU.

B. Test and Fault Isolation Equipment Requirements

Table 4-1 lists the equipment required to access the SDU MPU and perform operational

and diagnostic testing on the SDU.

Table 4-1 List of Required Test Equipment

Item Equipment Specification Quantity

Computer Standard VT-100 386 CPU, 20 MHz or higher 1

VT-100 terminal

emulation program HyperTerminal©,

ProComm Plus©, or

equivalent

Serial communication program using an

RS-232 port 1

Cable RS-232 cable Maximum length 25 feet 1

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C. SDU MPU

This section describes the SDU MPU and provides the connection and cabling details

required to access and use the program.

(1) Connecting to the MPU

The MPU provides a system interface for fault isolation and diagnostic procedures.

To use the SDU MPU, connect an RS-232, VT-100 terminal (computer operating a

terminal emulation program) to the RS-232 maintenance port interface of the SDU.

The maintenance port on the front panel of the SDU provides a direct connection to

the MPU using a DB9 connector.

Figure 4-1 provides cabling details for the SDU maintenance port.

Figure 4-1 Maintenance Cable

(a) Interface Requirements

A standard VT-100 compatible terminal running an emulator program (such as

HyperTerminal, ProComm Plus, or similar) provides the user interface to the SDU

MPU. The RS-232 terminal connection settings for SDU maintenance ports are

listed in Table 4-2.

Table 4-2 Maintenance Port Connection Settings

Parameter Setting

Character Format ASCII

Baud Rate 19200 bps

No. of bits 8

Parity None

Stop bits 1

Flow Control None

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(2) Using the SDU MPU

This section describes the basic procedures for using and navigating the SDU MPU.

NOTE: There are various levels of access to the MPU. Each level is protected by a

different password. This section describes the MPU functions available using

the Level 1 password.

(a) Entering Passwords

You can enter the password any time after the SDU boots.

• To access Level 1 functions, type menu.

NOTE: The password does not appear on the screen when you type it.

(b) Navigating the SDU MPU

• To scroll through the available menus, press CTRL+N.

• To go to the previous menu, press CTRL+O.

• To refresh the menu screen or exit from a Reports Menu, press ESC.

• To enable test or data entry functions, press the letter associated with the

menu items.

(d) Selecting Reports

The reports available through the MPU enable users to view information about

the configuration and status of the SDY. This information is used to troubleshoot

the communication system on the aircraft.

To access reports:

1. In the MPU, press EQUAL SIGN (=).

A list of reports appears. Active reports show as toggled on. Inactive reports

show as toggled off.

2. To activate a report, type the report number, and then press ENTER.

NOTE: Multiple reports can be activated at the same time; type and enter

each report number separately.

3. To turn off individual, active reports, type the report number you want to

toggle off, and then press ENTER.

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4. To turn off all active reports, press EQUAL SIGN (=), and then press X.

(3) Menu Item Descriptions

This section provides a brief description of the Level 1, MPU menu items used for

test and fault isolation procedures.

In active SDUs, menu screens display the firmware version.

NOTE: Depending on the version of software installed and the system configuration,

the menu and reports available to users may differ slightly from the

illustrations shown and described in this document.

(a) Menu 1

Figure 4-2 shows an example Menu 1 screen display. Table 4-3 describes the

items available in Menu 1.

MENU 1 FIRMWARE Vx.x GND

Y explain error status U list event log (hex)

F print equipment stats

<CTRL> N next menu <CTRL> O previous menu = select reports

Figure 4-2 Menu 1 Screen Display

(b) Menu 2

Figure 4-3 shows an example MPU Menu 2 screen display. Table 4-4 describes

the items available in Menu 2.

Table 4-3 Menu 1 Item Descriptions

Menu Item Description

Y: explain error status Reports error status when failure LED is illuminated. Displays OK if no error

exists.

F: print equipment

stats Prints a list of the current equipment statistics, including temperature,

number of power-ups, hours of operation, time since power-up, and

processor usage.

U: list event log Lists the current event log (hex format).

MENU 2 FIRMWARE Vx.x GND

L re-enter logon password V get firmware versions

Z reset A781 SDU C query loss of cooling mode

H query SDU-FMPA cable loss

<CTRL> N next menu <CTRL> O previous menu = select reports

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Figure 4-3 Menu 2 Screen Display

Table 4-4 Menu 2 Item Descriptions

Menu Item Description

L: re-enter logon

password Permits a user to enter a new access level password.

Z: reset A781 SDU Enables a complete, soft reset of the SDU; once reset, the menu access

password must be re-entered.

H: query SDU-FMPA

cable loss Initiates the cable loss determined in auto-calibration.

V: get firmware versions Displays the kernel and application software versions for the Control

Processor, Data I/O Processor, Channel Cards

C: query loss of cooling

mode Indicates if loss of cooling mode is active or inactive.

Figure 4-4 shows the menu 3 screen display. Table 4-5 describes the items

available in Menu 3.

MENU 3 FIRMWARE Vx.x

F list call log G clear call log

O list DIO ORT H list SCM/CP ORT

Y verify CP ORT

<CTRL> N next menu <CTRL> O previous menu = select reports

Figure 4-4 Menu 3 Screen Display

Table 4-5 Menu 3 Item Descriptions

Menu Item Description

F: list call log Lists Classic call logs for the following events:

• Successful Aero Log-on

• Air-to-ground calls accepted by the SDU

• Ground-to-air calls accepted by the SDU

Lists SBB call logs for the following events:

• Attachment or modification of attachment, including change of beam ID

• Creation or deletion of primary or secondary contexts

O: list DIO ORT Lists of ORT items destined for the Data Processor in human readable

form.

Y: verify CP ORT Verifies if file name of the internal copies of the Secure and User ORT

are valid or corrupted.

G: clear call log Clears the call log after a confirmation.

H: list SCM/CP ORT Lists ORT settings and how they were configured (either by default or

through the maintenance port, or via SCM ORT files). “Set by

maintenance port” indicates that the ORT parameter is set by the

maintenance port.

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D. Operational and Diagnostic Test Procedures

You can perform all test procedures presented in this section to test the total operational

status of the ARINC 781 system. You can conduct these operational tests for all equipment

returned to service after repair.

The procedures assume that the technical personnel are familiar with the test equipment

used and can operate the equipment to produce the required inputs and obtain the

required results (indications). Refer to the detailed operating procedures and descriptions

of the SDU MPU included in this section.

CAUTION: ONLY AUTHORIZED TECHNICAL PERSONNEL WHO ARE TRAINED IN

GENERAL AVIATION WORKMANSHIP AND HAVE A BASIC

UNDERSTANDING OF SATCOM SYSTEMS SHOULD PERFORM THE

OPERATIONAL AND DIAGNOSTIC TEST PROCEDURES IN THIS

MANUAL.

CAUTION: CHANGES TO DEFAULT VALUES FOR SOME MENU FUNCTIONS MAY

SERIOUSLY DEGRADE SYSTEM OPERATION.

NOTE: This manual describes the basic MPU functions, menus, and reports required for

the testing and fault isolation procedures presented in this section. Please consult

Product Support before entering any unfamiliar menu selections not described in

this manual.

NOTE: Using a terminal emulation program, open a log file and save all test results for

future reference and test records.

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Refer to the Outline and Installation diagrams (Figure 3-1 to Figure 3-6) and the

Interconnection and Contact Assignment drawings (Figure 3-7 to Figure 3-9) for

additional information.

(1) Test Setup Procedure

The test setup procedure is presented in Table 4-6.

Table 4-6 Test Setup Procedure

Step Action

1.0 Make sure that the SDU is powered down and disconnected from the power source.

2.0 Remove the maintenance-port connector cover.

3.0 Connect a maintenance cable to the SDU front-panel maintenance port connector.

4.0 Connect the other end of the cable to the serial port of the computer.

5.0 Open a log file to capture all test data.

(2) Post Test

When testing is completed, follow the steps in Table 4-7.

Table 4-7 Post Test Procedure

Step Action

1.0 Save the log file of the test results (or data) for future reference.

2.0 Remove power from the SDU that was tested and from all other test equipment.

3.0 Disconnect test equipment from the SDU.

4.0 Replace the maintenance-port connector cover (if it was removed during the test

setup).

If the Unit Under Test (UUT) PASSED the test, re-install the unit on the aircraft.

If the UUT FAILED the test, return the UUT along with a hardcopy printout of the recorded

(captured) log file of the test results to the manufacturer for service and repair. Indicate

the date of the test and the serial number of the UUT on the test documentation.

(3) Installation and Operational Verification Tests

To verify that the ARINC 781 system is ready for operation, use the following

procedures:

• Power-On Test

• BITE

(a) Power-On Test

To complete the power-on test, follow the steps in Table 4-7.

Table 4-8 Power-On Test Procedure

Step Action

1.0 Follow the test setup procedure in Table 4-6 on page 4-7.

2.0 Power-on the SDU.

3.0 Power-on the FMPA (if applicable).

4.0 Check the status of the front panel LEDs. Verify that the green LED flashes for 60

seconds and then turns off. Verify that the red LED is not illuminated. For more

information about the LED signals, refer to "LEDs" on page 1-11.

5.0 Review the BITE status of all system components using the MCDU. Verify that all

subsystems show OK status. For more information about using the MCDU, refer to

"Viewing BITE Information" on page 2-8.

6.0 Follow the post test procedure in Table 4-7 on page 4-7.

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(b) BITE

If equipment connected to the ARINC 781 avionics system provides wrong

information or does not provide a signal to the ARINC 781 SDU, the SDU cannot

function properly. You can check the status of connected equipment with the

MCDU BITE screens. To check the status of connected equipment, follow the

procedure described in "Viewing BITE Information" on page 2-8.

The SATCOM BITE page provides information about the results from BITE for

various parts of the ARINC 781 system.

• If BITE fails a component, remove the component from service and return it

to the equipment supplier—see "Maintenance and Repair" on page 5-1.

• If BITE fails a component other than the ARINC 781 SDU, FMPA, or SCM,

verify the operation of that component and test the satellite communication

system again.

2. Troubleshooting and Fault Isolation

This section provides troubleshooting procedures for ARINC 781 systems.

Troubleshooting procedures require data obtained using the MCDU. For specific instructions

on how to access and use the MCDU, refer to "Operating the MCDU" on page 2-1.

NOTE: All of the MCDU pages discussed in this section are accessed from the SATCOM

BITE page.

A. Subsystem Health

The SATCOM SUBSY HLTH page provides the BITE status of subsystem components.

To check the subsystem health, on the SATCOM BITE page, press the key next to SUBSY

HLTH.

Figure 4-5 illustrates the SATCOM SUBSY HLTH page.

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Figure 4-5 SATCOM Subsystem Health Menu

Table 4-9 describes the information available on the SATCOM SUBSY HLTH menu.

Table 4-9 SATCOM Subsystem Health Menu

Label Description Action

LNA Reports the status of the LNA as OK, NO DATA (if

golden label 350 from the antenna is missing or

HGA is disconnected), TEST, or FAULT. The LNA

status matches the HDA status.

If the status is NO DATA, check

the bus connections from the

Antenna and check the speed of

bus.

If the status is FAULT, test or

troubleshoot the LNA equipment.

ANT Reports the status of the HGA as OK, FAULT,

TEST, or NO DATA. If the status is FAULT, test or

troubleshoot the HGA equipment.

If the status is NO DATA check the

ARINC 429 bus from the Antenna.

FMPA Reports the status of the FMPA as OK, FAULT, NO

DATA, or NONE. If there is no FMPA configured,

the reported status is NONE.

If the status is FAULT, return the

FMPA to the equipment supplier.

If the status is NO DATA check the

cable to the FMPA.

CONFIG

PARITY Reports the status of the rear connector

configuration parity as OK (parity is odd) or FAULT

(parity is not odd). This status can be different from

the setting of Bit 25 in Label 350 to the CMC, which

is also set if the secure ORT is missing or invalid.

If the status is FAULT, check

strapping—a non-supported

configuration may be strapped.

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B. SATCOM System Bus

The SATCOM SYSTEM BUS page provides information about the bus status of

equipment outside the ARINC 781 system. SATCOM services are not available if the

equipment does not operate or communicate properly.

To check the bus status, on the SATCOM BITE page, press the key next to SYS BUS.

Figure 4-6 illustrates the SATCOM System Bus page.

Figure 4-6 SATCOM System Bus Menu

Table 4-10 describes the information available on the SATCOM SYS BUS menu.

Table 4-10 Bus Status Indicators

Bus Status

INACTIVE NO DATA NONE OK

CFDS No labels of correct

speed on bus. The expected Golden

label (227) is not

present.

The bus is not

installed. The expected Golden

label is present and the

bus is active at the

correct speed.

MCDU No labels of correct

speed on bus. The expected Golden

label (377) is not

present.

The bus is not

installed. The expected Golden

label is present and the

bus is active at the

correct speed.

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C. Thermal Status

As shown in Figure 4-7, the SATCOM OVERTEMP menu reports the thermal status of

system components.

To check the thermal status, on the SATCOM BITE page, press the key next to

OVERTEMP.

IRS - PRI No labels of correct

speed on bus. The expected Golden

label (310) is not

present.

N/A The expected Golden

label is present and the

bus is active at the

correct speed.

IRS - SEC No labels of correct

speed on bus. The expected Golden

label (310) is not

present.

The IRS2Type secure

ORT parameter

specifies whether it is

connected or not

connected.

The expected Golden

label is present and the

bus is active at the

correct speed.

GNSS No labels of correct

speed on bus. The expected Golden

label (110) is not

present.

The bus is not

installed. The expected Golden

label is present and the

bus is active at the

correct speed.

AES ID No labels of correct

speed on bus. The expected Golden

label (275) is not

present.

The bus is not

installed. The expected Golden

label is present and the

bus is active at the

correct speed.

CMU No labels of correct

speed on bus. The expected Golden

label (270) is not

present.

The bus is not

installed. The expected Golden

label is present and the

bus is active at the

correct speed.

CTU Label 351 bit 27 is set

to inactive. N/A The bus is not

installed. Label 351 bit 27 is set

to OK.

Table 4-10 Bus Status Indicators

Bus Status

INACTIVE NO DATA NONE OK

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Figure 4-7 SATCOM Overtemp Menu

Table 4-11 describes the information available on the SATCOM OVERTEMP menu.

D. SCM Health

As shown in Figure 4-8, the SATCOM SCM menu reports the status of the communication

buses to the SCM and the status of the secure and user configuration tables.

Table 4-11 SATCOM OVERTEMP Menu

Label Description Action

SDU Reports the SDU thermal status

as OK or FAIL. If the status is FAIL, check the fan operation and

temperature at the location of the equipment.

HGA Reports the HGA thermal status

as OK, NO DATA, or FAIL. If the status is FAIL, check the fan operation and

temperature at the location of the equipment.

FMPA Reports the FMPA thermal status

as OK, NO DATA, or FAIL. If the status is FAIL, check the fan operation and

temperature at the location of the equipment.

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Figure 4-8 SATCOM SCM Menu

Table 4-12 describes the information available on the SATCOM SCM menu.

Table 4-12 SATCOM SCM Menu

Label Description Action

STATUS Reports the SCM status as OK or FAIL. If the status is FAIL, return the SCM to

the equipment supplier.

BUS

TO/FROM Reports the status of the bus to the SCM as

OK or FAIL. If the status is FAIL, check the

connections to the SCM.

SECURE ORT Reports the status of the Secure ORT as

one of the following:

NOT LOADED – No ORT in SCM memory.

OK – Secure ORT is valid.

INVALID – The Secure ORT is corrupted or

otherwise invalid and must be reloaded.

If the status is INVALID or NOT

LOADED, load a SECURE ORT file.

USER ORT Reports the status of the User ORT as one

of the following:

NOT LOADED – No ORT in SCM memory.

OK – User ORT is valid.

INVALID – The User ORT is corrupted or

otherwise invalid and must be reloaded.

If the status is INVALID or NOT

LOADED, load a USER ORT file.

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E. Subsystem Bus Status

As shown in Figure 4-9, the SATCOM SUBSY BUS menu reports the status of all

subsystem buses that provide communication between the components of the system.

Figure 4-9 SATCOM Subsystem Bus Menu

Table 4-13 describes the information available on the SATCOM SUBSY BUS menu.

Fields are left blank if the equipment is not included in the installation.

NOTE: Input and output are with respect to the SDU.

F. RF Path Status

As shown in Figure 4-10, the SATCOM RF PATH menu reports the status the RF paths

of a system with an FMPA installed.

Table 4-13 SATCOM SUBSY BUS Menu

Label Description Action

ANT Reports the status of the input and

output buses for the antenna as OK,

NO DATA, or FAIL.

If status is NO DATA, label 350 is missing—

check the bus connections.

HPA Reports the status of the input and

output buses for the HPA as OK, NO

DATA, NONE, or FAIL.

If status is NO DATA, label 350 is missing—

check the bus connections.

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Figure 4-10 SATCOM RF Path Menu, System with FMPA

Table 4-14 describes the information available on the SATCOM RF PATH menu.

G. USIM and Data Bus Status

As shown in Figure 4-11, the SATCOM USIM/DATA menu reports the status of the USIMs

and data buses of the system.

Table 4-14 SATCOM RF PATH Menu

Label Description

RX:SDU-DLNA Reports the status of the RF path from the DLNA to the SDU as OK or FAULT.

TX:SDU-FMPA Reports the status of the RF path from the SDU to the FMPA as OK or FAULT.

For systems not configured for FMPA, the status is N/A.

TX:FMPA-ANT Reports the status of the RF path from the FMPA to the antenna as OK or

FAULT. For systems not configured for FMPA, the status is N/A.

VSWR Reports the status of the VSWR between the FMPA and the antenna as OK

or FAULT. For systems not configured for FMPA, the status is N/A.

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

ARINC 781 SDU, SCM, and FMPA

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Figure 4-11 SATCOM USIM/DATA Menu

Table 4-15 describes the information available on the USIM/Data menu.

H. ORT

The ARINC 781 system may not function properly if the ORT parameters do not match

the installed system.

(1) ORT Use and Storage

The ARINC 781 system includes a secure and user ORT. Secure ORT files must be

certified for the aircraft type on which the equipment is installed. Items in user ORT

files can be modified by individual customers and may be customized to an individual

aircraft.

You can change secure ORT parameters only by uploading an ORT file. To obtain

an ORT file, contact Product Support.

Table 4-15 SATCOM USIM/DATA Menu

Label Description

USIM#1 Reports the status of USIM#1 bus as OK, WARMING, SBB LOG, FAULT, or N/A

if channel card 1 is not in SBB mode.

ETH#1 Reports the status of ETH#1 bus as DISABLED, LINK, or NO LINK.

ETH#2 Reports the status of ETH#2 bus as DISABLED, LINK, or NO LINK.

QUAD ETH#3 Reports the status of QUAD ETH#3 bus as DISABLED, LINK, or NO LINK.

QUAD ETH#4 Reports the status of QUAD ETH#4 bus as DISABLED, LINK, or NO LINK.

ETH#5 Reports the status of ETH#5 bus as DISABLED, LINK, or NO LINK.

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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The load procedure loads an ORT file to the SCM using an ARINC 615A data loader.

You can only load ORT data when the aircraft is on the ground and the data load

discrete is asserted. When the SDU boots, it compares the ORT file in its memory to

that in the SCM. If the ORT files do not match, the SDU loads the file from the SCM

into its memory.

Some user ORT parameters can be modified in the SDU ORT. You can reset the

SDU ORT to the default values stored in the SCM in the maintenance menus.

(2) Checking the ORT

You can check the content of the ORT file through the maintenance port menus.

"SDU MPU" on page 4-2 provides information about accessing the maintenance port

menus.

NOTE: The ORT includes many parameters that affect internal operations. These

parameters are not meaningful for technicians troubleshooting the satellite

communication system.

To check the ORT:

1. In the maintenance port menus, navigate to menu 3.

2. To list the ORT, press h.

The list of ORT parameters appears. The list is about eight pages long.

Some ORT parameters displayed are system defaults that cannot be modified

through the secure and user ORT files.

3. Compare the ORT parameters to the system installed in the aircraft.

I. Contact Product Support

When the troubleshooting procedures do not find a fault and the ARINC 781 system does

not function properly, contact Product Support.

Product Support may ask you to capture and send them system specific logs and reports.

To access logs:

1. In the maintenance port menus, navigate to Menu 3.

2. Turn on the text capture feature of the terminal emulator on your computer.

In HyperTerminal, click Transfer, and then click Capture Text.

3. To view the call log, in Menu 3, press f.

4. To view the event log, in Menu 3, press s.

NOTE: The event log includes information about internal events that enable Product

Support to monitor the processes of the ARINC 781 system. This log does

not provide information for the end user.

5. Turn off the text capture feature of the terminal emulator and send the captured file

to Product Support.

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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To access reports:

1. Turn on the text capture feature of the terminal emulator on your computer.

In HyperTerminal, click Transfer, and then click Capture Text.

2. In the maintenance port menus, press EQUAL SIGN (=).

A list of reports appears.

3. To activate a report, type the number next to the report description, and then press

ENTER.

NOTE: Product Support will specify the required reports, and may ask you to operate

the ARINC 781 equipment while the reports gather information.

4. To stop a report, press EQUAL SIGN (=), then type the number of the report, and

then press ENTER.

NOTE: To stop all reports, press X.

5. Turn off the text capture feature of the terminal emulator and send the captured file

to Product Support.

3. Adjustment/Alignment Procedures

There are no adjustment/alignment procedures required for the ARINC 781 system.

4. Modification History

The ARINC 781 system currently has no history of modifications.

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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MAINTENANCE AND REPAIR

This section provides maintenance and repair information for the ARINC 781 system, including the

following sections:

• Maintenance

• Repair

• Instructions for Continued Airworthiness

• Visual Inspection and Check

1. Maintenance

The ARINC 781 system does not require routine maintenance.

2. Repair

If functional problems occur, the SDU BITE identifies the faulty LRU.

As per continued airworthiness instructions, if an SDU, SCM, or FMPA is inoperative, use the

Standard Practices Chapter of the Aircraft Maintenance Manual to:

• remove the unit

• secure cables and wiring

• collar applicable switches and circuit breakers, and placard them as “inoperative”

Before flight, revise the equipment list and weight and balance data as applicable, and record

the removal of the unit in the log book [refer to section 91.213 of the FAR or the aircraft’s minimum

equipment list (MEL)].

All repairs must be performed at the equipment supplier factory.

3. Instructions for Continued Airworthiness

Periodic inspections of the mechanical and electrical interfaces of the ARINC 781 system

components to the aircraft should be completed as defined by the governing airworthiness

body’s Instructions for Continued Airworthiness (ICA) for the installation (for example, Transport

Canada, the FAA, the EASA).

Installation of the ARINC 781 SATCOM Avionics System on an aircraft by Supplemental Type

Certificate (STC) obligates the aircraft operator to include the maintenance information supplied

by this manual in the operator’s Aircraft Maintenance manual and the operator’s Aircraft

Scheduled Maintenance Program.

This section provides the special instructions and maintenance requirements for continued

airworthiness of the ARINC 781 system.

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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A. Airworthiness Limitations

When applicable, the Airworthiness Limitations section is FAA-approved, and specifies

maintenance required under Title 14 Code of Federal Regulations (CFR) Part 43.16 and

14 CFR 91.403 of the Federal Aviation Regulations unless an alternative program has

been FAA approved.

This section must be added to the Airplane Maintenance Manuals. The information

contained herein supplements the Airplane Maintenance Manuals only in those areas

covered by the ARINC 781 system installation. For limitations and procedures not

contained in this supplement, consult the basic Airplane Maintenance Manuals.

The inspections and airworthiness limitations specified in this section are FAA approved.

This section specifies the inspections and other maintenance required under sections

433.16 and 91.403 of the Federal Aviation Regulations unless an alternative program

has been FAA approved.

B. Electrical and Mechanical Inspection and Check

Periodic inspections of the mechanical and electrical interfaces of the A781 system

components to the aircraft should be completed as defined by the governing

airworthiness body (for example, Transport Canada, the FAA, the EASA).

C. Instructions for Continued Airworthiness

The following paragraphs describe all maintenance requirements and instructions for

continued airworthiness of the ARINC 781 avionics system:

1. This manual contains maintenance information for the SDU, SCM, and FMPA,

including system description, system operation, installation, test, and fault isolation.

2. Add the following information to the illustrated parts catalog for the aircraft:

• all part numbers referred to in this manual

• all LRUs referred to in this manual

3. Add all wiring diagram information contained in this manual to the aircraft operator’s

appropriate aircraft Wiring Diagram Manuals.

4. No additional or routine maintenance is required for the on-condition SDU, SCM, and

FMPA.

5. If an SDU, SCM, or FMPA is inoperative, follow the instructions listed in "Repair" on

page 5-1.

6. Return all units to the equipment supplier factory for repair. See Appendix A: Return

Material Authorization for detailed removal information and procedures.

7. Install repaired units on the aircraft in accordance with the installation instructions

provided in this manual.

8. Make sure that all repaired units are operating before approving them for return to

service, using the operational verification tests and procedures provided in this

manual.

9. Enter the approval for return to service in the logbook, as required by section 43.9

of the FAR.

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10.Add the following scheduled maintenance tasks to the aircraft operator’s appropriate

aircraft maintenance program:

1. Recommended periodic scheduled servicing tasks: None required.

2. Recommended periodic inspections: as per the aircraft inspection and

maintenance schedule.

3. Recommended periodic scheduled preventative maintenance tests (tests to

determine system condition and/or latent failures): None required.

4. Visual Inspection and Check

Perform the following procedures to inspect the SDU, SCM, and FMPA after installation of the

units onto the aircraft.

Follow all approved safety standards and practices during the inspection.

1. Disconnect all circuit breakers to the SDU, SCM, and FMPA and associated systems.

CAUTION: FAILURE TO DISCONNECT CIRCUIT BREAKERS CAN LEAD TO

INJURY TO THE OPERATOR AND DAMAGE TO THE EQUIPMENT.

2. Examine the connection for loose, damaged, or missing hardware.

3. Examine cables and connections. Contact Product Support to gauge the severity of

the damage if you find:

•corrosion

• chafing

• wear

• damage

4. Tighten any loose connectors to the manufacturer’s recommended value.

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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APPENDIX A: RETURN MATERIAL AUTHORIZATION

To return equipment to the equipment supplier for repair, this RMA procedure must be followed.

Failure to comply with this procedure may result in shipping delays and additional charges.

1. Warranty Returns

Equipment that qualifies for warranty repair can be returned to the equipment supplier for repair

or replacement at their discretion. The customer shall pay the shipping costs to the equipment

supplier and the equipment supplier will pay the shipping costs to return the repaired/replaced

unit to the customer.

2. Non-Warranty Returns

Equipment that fails to work properly because of improper or negligent use, abuse, shipping

damage, or any other condition can still be returned to the equipment supplier for repair or

replacement at their discretion. The customer will be notified of the cost to repair or replace the

unit before invoicing for the repair or replacement. The customer shall pay for the shipping costs

to and from the equipment supplier.

3. Repackaging Requirements

ARINC 781 SDU or SCM components must be returned to the equipment supplier in approved

shipping containers. Failure to do so may invalidate the warranty.

If SDU or SCM shipping containers are unavailable, they can be ordered from the equipment

supplier when requesting the RMA number.

4. RMA Procedure

If it is determined that equipment must be returned to the equipment supplier for repair or

overhaul, follow the RMA procedure below.

1. Have the following information ready before calling Product Support:

• Model (e.g., ARINC 781 SDU)

• Unit part number (e.g., 1394-A-1100)

• Serial number

• Description of failure

• Aircraft tail number, serial number, and aircraft model number

2. Call Product Support.

3. A Product Support specialist will attempt to resolve the problem by telephone. If

equipment must be returned to the equipment supplier, the Product Support

Specialist will authorize the R&O Coordinator to issue an RMA number.

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

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4. Pack the equipment in the original shipping container or a container approved by the

equipment supplier.

5. Write the RMA number on the outside of the shipping container and on all shipping

documents, enclose a copy in the box, and send your prepaid shipment to the

equipment supplier.

6. Fax or email the details of the shipment to the R&O Coordinator, including the

following information: Shipment date, carrier name, and the waybill number.

EMS Technologies Canada FMPA Licensed Non-Broadcast Station Transmitter User Manual MN 1394 10078

EMS Technologies Canada, Ltd. Licensed Non-Broadcast Station Transmitter MN 1394 10078

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