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

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TopFlight Satcom SDU & SCM

Installation and Maintenance Manual Ref: TFS062/J-03/003

Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior

written approval. 1

Installation and

Maintenance Manual

TopFlight Satcom

SDU – 82155A Series

SCM – 82158A Series

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Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior

written approval. 2

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RECORD OF REVISIONS

REV.

NO. REVISION

DATE DATE

INSERTED BY REV.

NO. REVISION

DATE DATE

INSTERTED BY

2 October 2007

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written approval. 4

CONTENTS

1.

INTRODUCTION

....................................................................................6

1.1. Purpose of Manual............................................................................6

1.2. Scope.................................................................................................7

1.3. References ........................................................................................7

1.4. Compliance to Regulations .............................................................7

1.5. List of Abbreviations........................................................................8

2.

DESCRIPTION

.....................................................................................10

2.1. TFS Satellite Communication System Domain ...........................10

2.2. TFS System Overview ....................................................................10

2.3. SDU General Description...............................................................11

2.4. Interfaces.........................................................................................20

2.5. Configuration Straps......................................................................21

2.6. SDU Interconnections ....................................................................22

2.7. SCM General Description...............................................................30

3.

INSTALLATION GUIDELINES

..........................................................36

3.1. Introduction.....................................................................................36

3.2. Interchangeability...........................................................................36

3.3. SDU / SCM Location and Accessibility Guidelines......................36

3.4. Mounting Tray.................................................................................37

3.5. Cooling ............................................................................................37

3.6. Power Requirements......................................................................37

3.7. SDU RF Connections......................................................................38

3.8. Bonding Requirements ..................................................................39

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3.9. SDU Fitting Instructions.................................................................39

3.10. SDU Removal Instructions.........................................................40

3.11. SCM Fitting Instructions.............................................................40

3.12. SCM Removal Instructions.........................................................41

4.

INSPECTION AND SYSTEM CHECKOUT

......................................42

4.1. Inspection/Check procedure .........................................................42

4.2. System Checkout............................................................................42

5.

MAINTENANCE

...................................................................................44

5.1. Introduction.....................................................................................44

5.2. Cleaning of Mechanical Parts........................................................44

5.3. Periodic Checks..............................................................................44

5.4. Cabling and Connections ..............................................................44

6.

TESTING AND FAULT ISOLATION

.................................................45

6.1. BITE Function .................................................................................45

6.2. Test Functions................................................................................46

6.3. Fault Isolation .................................................................................48

7.

INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

......................54

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1. INTRODUCTION

1.1. Purpose of Manual

This manual sets forth installation and maintenance guidelines for the THALES

TopFlight Satcom (TFS) Satellite Data Unit (SDU), and SDU Configuration Module

(SCM). The SDU and SCM installation specific and general guidelines contained

within this manual are supported by mechanical and electrical interconnection

drawings. Drawings should be reviewed by the installation organisation, and any

requirements specific to a particular airframe should be assessed before installation is

commenced.

The Manual covers the following topics:

 Title Page

 Record of Revisions

 Table of Content

 Introduction

 Description

 Installation Guidelines

 Inspection and System Checkout

 Maintenance

 Testing and Fault Isolation

 Instructions for Continued Airworthiness

NOTE: This manual does not cover aircraft system commissioning test procedures.

Advisory notes presented within this manual such as: ‘Warnings, Cautions and Notes’

are applicable to the TFS system as follows:

 A WARNING is used to alert the reader to possible hazard which may

cause loss of life or physical injury

 A CAUTION is used to denote the possibility of damage to materiel but not

danger to personnel

 A NOTE is used to convey, or draw attention to, information that is

extraneous to the immediate subject of the text

For any queries related to information contained within this Manual contact the

following THALES TFS Project Manager:

86 Bushey Road

Raynes Park, London

SW20 0JW, UK

Tel. +44 (0)20 8946 8011

Fax. +44 (0)20 8946 7530

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1.2. Scope

The Thales SDU and SCM comply with the design requirements set forward in the

ARINC 781 Characteristic. An ARINC 781 compliant system is intended to support

one or more of the Inmarsat aeronautical services known as ‘Classic-Aero’, ‘Swift 64’,

and ‘SwiftBroadband.

This manual provides information specific for the SDU and SCM capable of providing

SwiftBroadband (SBB) services for Single Aisle (SA) aircraft configuration. The SDU

and SCM covered in this manual support the single channel Inmarsat Class 3A and

Class 7 services only.

1.3. References

1.2.1. THALES SCM Component Maintenance Manual 44-35-33.

1.2.2. THALES SDU Component Maintenance Manual 44-35-32.

1.2.3. EMS AMT-3500 Intermediate Gain Antenna Subsystem Installation Manual

MN-1242-20047.

1.2.4. ARINC 429: Mark 33 Digital Information Transfer System.

1.2.5. ARINC 600 Characteristic: Air Transport Avionics Equipment Interfaces.

1.2.6. ARINC 615 Characteristic: Airborne Computer High speed Data Loader.

1.2.7. ARINC 615A Characteristic: Ethernet Based Data loading.

1.2.8. ARINC 781 Characteristic: Mark III Aviation Satellite Communication

(Satcom) System Avionics.

1.2.9. Transmitter Certification of FCC ID: KV6-TFS-SDU82155A Series TFS SDU

to Federal Communications Commission rule part 87 and Confidentiality:

A111/STE-012/006.

1.2.10. RTCA DO-160E/EUROCAE ED-14E: Environmental Conditions and Test

Procedures for Airborne Equipment.

1.4. Compliance to Regulations

1.4.1. FCC:

 The SDU is designed to be compliant with part 15 and part 87 of the

Federal Communication Commission (FCC) regulations.

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1.4.2. The installation must be compliant to:

 EASA/FAR 25.869 Fire protection: systems

 EASA 25X0899 Electrical bonding and protection against lightning and

static electricity

 EASA/FAR 25.1301 Equipment, general, function and installation

 EASA/FAR 25.1309 Equipment, systems and installations

 EASA 25X1316 System lightning protection

 EASA/FAR 25.1353 Electrical equipment and installations

 EASA/FAR 25.1357 Circuit protective devices

 EASA 25X1360 Precautions against injury

 EASA/FAR 25.1431 Electronic equipment

 EASA 25.561 Emergency Landing

1.5. List of Abbreviations

ac Alternating Current

ACARS Aircraft Communication Addressing and Reporting System

ADL Airborne Data Loader

AES Aeronautical Earth Station

AGS Airborne GSM Server

AIM Antenna Interface Mounting

AMO Approved Maintenance Organization

AOR-E Atlantic Ocean Region-East

AOR-W Atlantic Ocean Region-West

APM Avionics Processor Module

ARINC Aeronautical Radio Inc.

ATE Automatic Test Equipment

BGAN Broadband Global Area Network

BITE Built In Test Equipment

BSU Beam Steering Unit

CCM Channel Card Module

CDU Control Display Unit

CMM Component Maintenance Manual

CPM Communication Processor Module

dc Direct Current

DLNA Diplexer and Low Noise Amplifier

EASA European Aviation Safety Agency

ECM External Configuration Memory

ECS Environmental Control System

EMC Electromagnetic Compatibility

ESD Electro Static Discharge

ESDS Electro Static Discharge Sensitive

FPL Front Panel LED

GES Ground Earth Station

GNSS Global Navigation Satellite System

GPS Global Positioning System

HPA High Power Amplifier

IGA Intermediate Gain Antenna

IMEI International Mobile Equipment Identity

IMM Installation and Maintenance Manual

IMSI International Mobile Subscriber Identity

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INMARSAT International Maritime Satellite Organization

IOR Indian Ocean Region

IP Internet Protocol

IPC Illustrated Parts List

IRS Inertial Reference System

I/O Input/Output

ISDN Integrated Service Digital Network

LED Light Emitting Diode

LES Land Earth Station

LRU Line Replaceable Unit

mA MilliAmpere

MCDU Multi-function Control and Display Unit

MCU Modular Concept Unit

MEL Minimum Equipment Level

MES Mobile Earth Station

MIB Management Information Base

NVM Non Volatile Memory

OMS Onboard Monitoring System

ORT Owner Requirements Table

OCXO Oven Controlled Crystal Oscillator

PAST Person Activated Self Test

PC Personal Computer

PLMN Public Land Mobile Network

P/N Part Number

POR Pacific Ocean Region

POST Power On Self-Test

PPPoE Point To Point Protocol over Ethernet

PSM Power Supply Module

PSTN Public Switched Telephone Network

RF Radio Frequency

SA Single Aisle

SATCOM Satellite Communication

SBB SwiftBroadband

SCDU Satellite Control Display Unit

SCM SDU Configuration Module

SDU Satellite Data Unit

SIM Subscriber Identity Module

SIS Standalone Interface System

SNMP Simple Network Management Protocol

SRU Shop Replaceable Unit

STC Supplemental Type Certificate

SW Software

TCP/IP Transmission Control Protocol/Internet Protocol

TFS TopFlight Satcom

UMTS Universal Mobile Telecommunication System

USIM Universal Subscriber Identity Module

Wi Fi Wireless Fidelity

WLAN Wireless Local Area Network

WOW Weight On Wheels

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2. DESCRIPTION

2.1. TFS Satellite Communication System Domain

SATCOM (Satellite Communications) systems provide users with long-range voice

and data communication by accessing global satellite and ground communications

networks. The introduction of Pico-Cells on aircrafts, and the new I4 INMARSAT

constellation of geostationary satellites have been the enabling technologies for the

development of significantly smaller, more capable terminals such as the Thales

TopFlight Satcom system.

SwiftBroadband is the aeronautical service, which operates on the INMARSAT BGAN

(Broadband Global Area Network) infrastructure. SwifBroadband supports Circuit

Switched and always-on TCP/IP data (packet switched) services. Thales SBB

TopFlight Satcom system supports the Inmarsat Classes of service 3A and 7.

Figure 2-1 below depicts the TFS communication system.

Inmarsat domain

TFS System

I4 Satellite

Backbone Networks

IP, PLMN, PSTN

User Terminals

Aeronautical Segment

Satellite

Access

Station

Space Segment

Ground Segment

Figure 2-1: Example of TFS communications system overview.

2.2. TFS System Overview

The TFS system conforms to the ARINC-781 Characteristic, and interfaces with

onboard avionics and communication equipment to provide the aircraft with a range of

communication services by transmitting and receiving L Band signals to and from the

fourth generation of INMARSAT satellites. For this purpose the INMARSAT satellite

constellation is connected to the ground backbone telecommunication network

through Satellite Access Stations (SAS) operated by service providers.

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The TFS system consists of the following LRUs (Line Replaceable Unit):

 One SDU (Satellite Data Unit)

 One SCM (SDU Configuration Module)

 One DLNA (Diplexer Low Noise Amplifier)

 One IGA (Intermediate Gain Antenna)

Figure 2-2 below depicts TFS system interfacing for the Single Aisle configuration.

Figure 2-2: Example of Single Aisle TFS system interfacing.

2.3. SDU General Description

2.3.1. Hardware

The SDU hardware meets RTCA/DO-254 level D requirements, and it is composed

(see Fig 2-3) of the following internal sub-assemblies:

 High Power Amplifier (HPA)

 Channel Card Module (CCM) x 1

 Communication Processor Module (CPM)

 Power Supply Module (PSM)

 Oven Controlled Crystal Oscillator (OCXO)

 Avionics Processor Module (APM)

 Backplane

 Front Panel

IGA

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The SDU enclosure is constructed of machined lightweight aluminium alloy and it is

packaged in an ARINC 600 6 MCU (Modular Concept Unit) housing suitable for

mounting in the equipment bay of an aircraft.

Two hold-down clamps are used to secure the SDU, permitting it to be firmly held in

position in the mounting rack. A handle fitted on the front panel of the SDU permits

removal, installation and carrying of the SDU.

Figure 2-3: Example of SDU sub-system modules exploded.

2.3.2. Software

The software in the SDU can be considered as being supplied in two elements, one

contained within the CCM the other operating on the SDU processors (CPM & APM).

The SDU’s application software primarily functions as the system controller providing

system level tasks such as CCM control, BITE reporting, Avionics interfacing via

ARINC-429 (including IRS (Inertial Reference System)) and providing external

interfaces (such as Ethernet) as well as routing functions between the external

interfaces and the CCM as necessary.

The SDU’s APM and CPM application software meets RTCA/DO-178B level D

requirements, and the CCM application software meets RTCA/DO-178 level E

requirements.

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2.3.3. ORT Parameters

The SCM ORT (Owner Requirement Table) is also stored inside the SDU. The ORT

database contains configuration data that is used to customize the operation of the

TFS system. It allows various preferences to be set to enable the efficient use of the

equipment in normal operation. The SDU is delivered to customers with a default

ORT.

2.3.4. General Operation

The SDU controls and processes all essential data in order to manage the reception

and transmission of data through the satellite link. The SDU controls the set-up of the

required channel types, providing modulation/demodulation, error correction, coding,

and data rates associated with the satellite communication channel(s).

The SDU is of modular design and can be configured for use on a wide variety of

aircraft. It meets requirements for cabin only, cockpit only and cabin and cockpit

services. This manual however covers the SA cabin only configuration.

The SDU converts digital/audio inputs to Radio Frequency (RF), and contains a High

Power Amplifier (HPA) function providing the necessary output power to support

communication between the aircraft and the satellite. It also controls the associated

antenna sub-system and uses the SCM for its own configuration data purposes.

The SDU operates within set frequency bandwidths:

 RX range is between 1525 to 1559 MHz

 TX is tuned over the range 1626.5 to 1660.5 MHz

 TX operational range is between 1631.5 to 1660.5 MHz

2.3.5. Sub-modules Basic Detailed Operation

 The Front Panel assembly gives visual indications for system status,

external maintenance interface connections and the SDU Person Activated

Self Test (PAST) push button

 The Backplane assembly makes interconnections between external

interfaces and the SDU internal sub-assemblies

 The APM provides interfacing to external avionics. It receives aircraft

position, speed and heading information from external avionics via ARINC

429 (Aeronautical Radio Incorporated), and updates the CCM with position

information every second. The APM manages satellite selection based on

aircraft position, and maintains antenna pointing to the wanted satellite

beam steering via ARINC 429. The APM manages RF (Radio Frequency)

resources and set CCM transmit power levels, taking into consideration

antenna gain and cable losses stored within the ORT

 The CPM handles and controls all communications interfaces (Ethernet,

RS232 and RS422)

 The CCM converts user’s input/output data to signals suitable for

transmitting and receiving L-Band signals using the satellite link

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 The High Power Amplifier (HPA) module amplifies the low level RF

signals from the CCM to produce high power output prior to connection to

the antenna

 The PSM operates from 115 Vac and supplies low level dc power supplies

to SRUs within the SDU and 12 Vdc to the SCM

 The OCXO provides 10 MHz clock reference signal for the CCM circuit

2.3.6. Operating Environment

 Operating temperature: between -15o C (5o F) and +55o C (131o F)

 Cooling: Forced air type in accordance with ARINC 600, requiring airflow

rate of 50 kg/hr, blowing from top to bottom. Maximum inlet temperature

+40o C

 Heat dissipation: 220 W (assuming 100% duty cycles with HPA operating

at 30 W output

2.3.7. Environmental Conditions

The SDU complies with the RTCA/DO-160-E (ED-14E). The environmental

qualifications categories complied with, are as per listed in Figure 2-4.

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RTCA DO-160E (ED-14E) Environmental Categories

1 Temperature/Altitude A2

2 Loss of Cooling V

3 Temp Var. B

4 Humidity B

5 Shock/Crash E

Vibration R

6 Vibration Curve BC

7 Explosion E

8 Waterproof X

9 Fluids X

10 Sand/Dust X

11 Fungus F

12 Salt Fog X

13 Magnetic Effect A

Power Input A(WF)

14 Harmonics H

15 Voltage Spike A

16 Conducted Audio R(WF)

17 Induced ZW

18 RF Susceptibility TR

19 RF Emissions M

20 Lightning Induced A3G33

21 Lightning Direct X

22 Icing X

23 ESD A

24 Fire C

Figure 2-4: Environmental test categories for SDU & SCM.

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2.3.8. Identification Label

Figure 2-5 represent the SDU Front Panel Identification Label for detailed description

of the numbered field refer to the legend in Figure 2-6.

HW PNR

Minor Rev.

SW PNR

TEST SDU

SCM

A

ntenna

HW PNR 82155X30

SW PNR

A

TEST PORT DLNA

Ext. HPA

Ext. BSU

Ext. Data Bus

ORT/Config.

Sat. Link #1

Sat. Link #2

LED INDICATIONS MAY RELATE TO

OTHER EQUIPMENT OR AIRCRAFT WIRING

CAUTION

THIS EQUIPMENT

REQUIRES FIELD

LOADABLE SOFTWARE

ENSURE CORRECT

SOFTWARE IS LOADED

REFER TO AMM

Supply 115VAC

CSD cm

Wt. 9.5kg (max)

FAA TC

FCC id

HW DO-254 Level C

SW DO-178B Level D

DO-160E Env. Cat

[(A2)Z]BAE[SC]EXXXFXA[

A(WF)]A[R(WF)][ZW][RR

]M[A3G33]XXAC

SATELLITE DATA UNIT (SDU)

MFR

SER

DMF

MFR K0385

SER NO

DMF

INSPECT

AMDT A B C D E F

G H I J K L

S

I

2 12

3

4

5

6

7

13 11

9

10

11

1

8

CAUTION CAUTION

SURFACE

HOT

16

15

14

Figure 2-5: Example of SDU Front Panel.

17

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SDU Front Panel legend

1 Manufacturer’s Name

2 Hardware Part Number

3 Hardware Minor Revision

4 Software Part Number

5 Manufacturer’s Code

6 Equipment Serial Number

7 Date of Final Factory Inspection (month and year)

8 Amendment Label

9 Inspection Stamp

10 Standalone Identification System

11 Field Loadable Software Warning

12 Voltage Supply, Compass Safe Distance, Weight of Equipment, FCC

(Federal Communication Commission) ID, Hardware and Software

Compliance references

13 Carrying Handle

14 Hold Down Lugs

15 Ethernet RJ45 Maintenance Connector

16 Status Light Emitting Diodes (LEDs)

17 Push To Test Switch

Figure 2-6: SDU Front Panel legend.

2.3.9. Weight and Dimensions

 For overall dimensions refer to Figure 2-7

 Form Factor: ARINC 600, 6 MCU

 Mass: 9.5 kg (21 lb) maximum

2.3.10. SDU Electrical Characteristics

 Supply voltage: 100 to 122 Vrms, ac, Frequency Range 360 to 800 Hz

 Power consumption: 255 W maximum

 RF Power Rating: variable up to 30W for continuous operation

 Max Power Rating, Watts: 120W peak RF power 4 channels @ 7.5W each

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Fi

g

ure 2-7: SDU Overall Dimensions. NOTE: all measurements

g

iven are in mm.

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2.4. Interfaces

The SDU interfaces with various aircraft systems.

2.4.1. Aircraft Power Utility Service

The TFS interfaces with the aircraft primary power generator as per depicted in

Figure 2-8 below.

SDU

IGA

DLNA

Aircraft Power

Supply

BP01

BP05

BP03

115 Vac Cold

115 Vac Hot

Chassis Ground

115V AC - 5 AMP Type A Circuit Breaker, as

per ARINC 781 recommendation.

19

18

E

F

115 Vac Cold

115 Vac Hot

SCM

SCM Power Return

Power Source 12 VDC MP01D

MP02D

A

7

22

Figure 2-8: TFS example of aircraft power distribution diagram.

2.4.2. Avionics interfaces

The following avionics interfaces are supported:

 Specific to type Cabin Network domain

 ADL (Aircraft Data Loader), PDL (Portable Data Loader)

 IRS, GPS (Global Positioning System)

In order to comply with transmit burst time, INMARSAT requires the SDU to be

provided with the aircraft present position within 1500m in three dimensions,

referenced to WGS-84 (GPS). In order to comply with this requirement the TFS SDU

requires ARINC 429 Nav Data labels as referenced in Figure 2-9. The values apply

to aircraft configurations where only on Nav Data bus is connected.

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PARAMETER ARINC 429 LABEL

Latitude GNSS – Hybrid 254

Longitude GNSS – Hybrid 255

Ground Speed GNSS – Hybrid 175

Track Angle True GNSS – Hybrid 137

True Heading – Hybrid 132

Pitch Angle 324

Roll Angle 325

GNSS Height (HAE) or Hybrid Altitude MSL 370 or 261

GNSS UTC (Binary) 150

GNSS Date 260

GNSS Sensor Status 273

GNSS HDOP 101

Figure 2-9: ARINC 429 Nav Data Labels – Hybrid.

2.4.3. Maintenance Interfaces

The SDU supports the following maintenance interfaces:

 Aircraft Data Loader (ADL), ARINC 615/615A

 Portable Data Loader (PDL), ARINC 615A

 Thales Maintenance Terminal

NOTE: For more information concerning data loading tools contact the Thales TFS

product support representative at the following address:

86 Bushey Road

Raynes Park, London

SW20 0JW, UK

Tel. +44 (0)20 8946 8011 (Switchboard)

Tel. +44 (0)20 8946 5169 (Hot desk).

2.5. Configuration Straps

In the case of using the mandatory configuration straps the SDU is configurable via

the SDU ARINC 600 configuration straps as defined in ARINC 781.

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The straps input values will be read only at unit power-up to determine the system

configuration. The SDU configuration will be selectable by multiplexing the

Configuration Straps inputs with the service availability discrete outputs as per

ARINC 781 Attachment 1-4 Note 17.

2.5.1. Mandatory Configuration Pins

Pins TP (Top plug) 3D and TP3E must be used on all aircraft installations as they

may be used as hardware implemented safety override to force the internal HPA

function into low power mode when connected to an external HPA.

Pin TP3G must be used on all aircraft installations since one of its functions is to

indicate whether all other configuration pins (excluding TP3D, TP3E, TP3F, TP3G,

and TP4D) should be used by the SDU. Pin TP4D should be used on all aircraft

installations since it indicates the SDU number (1 or 2).

Pin TP3F must be used on all aircraft installations since it indicates that the number

of all configuration pins (excluding TP3D) including the parity pin itself connected to

service availability discrete (or TP3D) is odd.

2.6. SDU Interconnections

2.6.1. ARINC 600 Standard Interwiring Connector

The SDU ARINC 600 connector provides:

 Input/Output connections

 DO160E EMC filtering to input and output interfaces

 ESD (Electrostatic Discharge) protection for ATE connections

The SDU is provided with a low insertion force, size 2-shell receptacle in accordance

with ARINC 600 Attachment 19. This connector accommodates coaxial and signal

interconnections in the top plug (TP) insert, Quadrax and signal interconnections in

the middle plug (MP) insert, and coaxial, fibre and power interconnections in the

bottom plug (BP) insert. The contact arrangements are as follows:

 Insert arrangement 08 receptacle in accordance with ARINC Specification

600, Attachment 11 for the top insert (Size 1 Coax cavity and Size 22

Signal sockets)

 Insert arrangement 120Q2 receptacle in accordance with ARINC

Specification 600, Attachment 20, Figure 20-6.5.5 for the middle insert

(Size 8 Quadrax cavities for pin components and Size 22 Signal sockets)

 Insert arrangement 12F5C2 receptacle in accordance with ARINC

Specification 600, Attachment 19, and Figure 19-49.19 for the bottom

insert (Size 12 Electrical pins, Size 16 Electrical pin, Size 5 Coax cavities,

and Size 16 Optical cavities).

 Index pin code 081 in accordance with ARINC Specification 600,

Attachment 18 should be used on both the SDU and the aircraft rack

connectors

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written approval. 23

2.6.1.1. ARINC 600 Pin Assignment

The layout of the rear panel ARINC 600 connector and the Pin assignment are

shown in the figures 2-10, 2-11, 2-12, and 2-13. For further Information regarding the

ARINC 600 connector refer to Figure 2-15.

Figure 2-10: ARINC 600 Connector Layout.

Top Plug

Middle Plug

Bottom Plug

Index code 81 (5,2,2)

Note: The index code pins dark

colour represents the post.

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written approval. 24

ATE ATE

A

TE

A

TE

Empty Config Config Config SPARE

ATE

Pin 1

A

ATE

Pin 2

B

Pin 3 Pin 4

A

TE

Pin 5

A

TE

Pin 6

A

TE

Pin 7

A

TE

Pin 8

A

TE

Pin 9

A

TE

Pin 10

ATE

Pin 11

ATE

Pin 12

ATE

Pin 13

ATE

Pin 14 Pin 15 Pin 16

A

TE

Pin 17

A

TE

Pin 18

A

TE

Pin 19

A

TE

Pin 20

Ethernet 1

TX

A

Ethernet 1

RX

A

Empty

Cavity

Config

Pin 1

Config

Pin 2

Config

Pin 3

Config

Pin 4

SPARE ISDN 1

TX

A

ISDN 1

RX

B

Ethernet 1

RX

B

Ethernet 1

TX

B

Cavity Pin 5

Config

Pin 6 Pin 7 Pin 8

ISDN 1

RX

A

ISDN 1

TX

B

Empty

Cavity

Empty

Cavity

Empty

Cavity

Config

Pin 9

Config

Pin 10

Config

Pin 11

Config

Pin 12

(Spare)

SPARE SPARE SPARE

1

2

3

4

5

A B C D G H J K

6

7

Empty Config Config Config SPAREEthernet 2

TX

MCDU 3

A

Ethernet 2

RX

MCDU 3

A

Cavity Pin 13

(Spare)

Config

Pin 14

(Spare)

Pin 15

(Spare)

Pin 16

(Spare)

ISDN 2

TX

A

ISDN 2

RX

B

Ethernet 2

RX

B

Ethernet 2

TX

B

Empty

Cavity

Config

Pin 17

(Spare)

Config

Pin 18

(Spare)

Config

Pin 19

(Spare)

Config

Pin 20

(Spare)

SPARE ISDN 2

RX

A

ISDN 2

TX

B

RF TX

To HPA or DLNA

E F

Figure 2-11: ARINC 600 Connect Arrangement For Top Plug (TP) Insert

Figure 2-12: ARINC 600 Connections Arrangement For Bottom Plug (BP) Insert.

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written approval. 25

Figure 2-13: ARINC 600 Connect Arrangement For Middle Plug (MP) Insert.

2.6.2. Electric Interconnection Diagram

The SDU interconnection diagram is given in Figure 2-14. It illustrates all the

necessary connection between the SDU and all the other interfaced equipment.

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SDU

(Notes 1,7,10)

Antenna

D/LNA

TP3D

TP3E

Service Availability Discrete 2

MP11F

Config Pin 1

Config Pin 2

Primary Nav Data (A)

Primary Nav Data (B)

Navigation Data

MP02A

MP02B

Aircraft

Power

Supply

BP01

BP05

BP03

115 Vac Cold

115 Vac Hot

Chassis Ground

115V AC - 5 AMP

Type A Circuit

Breaker, as per

ARINC 781

recommendation.

19

18

E

F

115 Vac Cold

115 Vac Hot

J10

D/LNA BITE Return

Client

Ethernet Port

Connector

Ethernet 3 RX (A) Q1

Ethernet 3 TX (B) Q1

Ethernet 3 TX (A) Q1

Ethernet 3 RX (B) Q1

1T-1

1T-3

1T-2

1T-4

SCM

Data to SCM (B)

Data to SCM (A)

Data from SCM (B)

Data from SCM (A)

SCM Power Return

SCM Power Source MP01D

MP02D

MP03D

MP04D

MP05D

MP06D 2

1

3

4

8

15

3

5

6

8

MP08C

MP08D

BITE Input Top/Port BSU/Ant (B)

BITE Input Top/Port BSU/Ant (A)

Multi-Control Output (B)

Multi-Control Output (A) MP01E

MP01F

7

4

(Note 5)

(Note 4)

(Note 3)

22

A

(Note 6)

7

NOTE: See Figure 2 -15 for list of Explanatory Notes

7

Front Panel RJ-45

Maintenance

Terminal

Connector

TX+

TX-

RX-

RX+

TX-

RX-

TX+ 2

1

6

3

(Note 8)

External HPA

not fitted

MP8F TX Mute Input

System

Failed

Indication

TX Mute

ARINC 615A

Data Loader

Connector

TP01A

TP01C

TP01B

TP01D Rear Ethernet RX (A)

Rear Ethernet TX (B)

Rear Ethernet TX (A)

Rear Ethernet RX (B)

(Note 11)

TX +

TX -

RX +

RX -

RX +

TX +

TX -

RX -

(Note 12)

See Note 1

for Signal

Details

MP1G SPARE

External

Reset

See Note 13

for Signal

Details

Secondary Nav Data (A)

Secondary Nav Data (B)

Navigation Data

(Note 14)

MP01J

MP01K

RX Port

TX Port

Antenna Port (Note 2)

D/LNA BITE H9

B

D/LNA Control 11

TP71

SDU RF Output to D/LNA

SDU RF Input from D/LNA BP07

(Note 2)

Figure 2-14: TFS System Interconnection Block Diagram – Single Aisle Configuration.

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ARINC 600 - Shell Size #2 Connector

View above is looking at the SDU mount connector, Radiall Part Number: 620-600-703.

Tray-mount mating half is supplied with all necessary inserts, except 1 x Size 5 Socket Coax

insert (male centre contact) (Radiall P/No: 620-021), which should be ordered separately. See

Radiall specification for 620-600-700 for further details on supplied inserts.

Fibre inserts are not required and will not be populated on the SDU mount connector, filler plugs

will be used to fill cavities. Size 5 Coax insert BP-6 is not required on the SDU mount connector

and will not be populated, a filler plug will be used to fill cavity.

Index Code: 81 (5,2,2)

(Top Insert: 08 / Middle Insert: 120Q2 / Bottom Insert: 12F5C2)

For the index code pins above, the dark colour represents the post.

ARINC 600

SDU Connector

defined in ARINC 781 - see Note 1

ABCDEFGHJ

1

5

7

1

5

7

ABCDEFGHJ

1

4

9

1

3

2

3

5

6

7

8

1

0

1

2

1

4

1

5

1

3

67

5

4

298

11 10

12

Index code

81 (5,2,2)

71

Note 1: System interconnections are as per ARINC781 - refer to ARINC 781 for clarification / further detail.

Note 6: Uses “Star-Quad” cable as defined in ARINC 664 Part 2. Cross-over to be provided in cable.

Note 7: Pins not required are not listed and should be left ‘Not-Connected’.

Note 8: Cross-over to be provided in cable, when using standard RJ-45 Ethernet connections.

Note 9: Radiall P/No: 620-600-700 does not include all necessary contacts; 1 x Size 5 Crimp Socket Coaxial Contact must also be ordered: Radiall P/No: 620-021.

Note 10: Pigtails for wiring shields/screens are to be made as short as possible to reduce susceptibility to interference.

Note 11: Uses “Shielded, Twisted Pair” cable as defined in ARINC 664 Part 2.

Note 12: The Maintenance Terminal interface will only be connected during maintenance activities.

Note 13: For the External Reset discrete input signal, ground state defined as input voltage less than 3.5V and resistance to airframe dc ground less than 20 mohms. Open

state defined as input voltage higher than 14V and resistance to airframe dc ground higher than 100000 ohms.

Note 14: A second Nav Data bus might be required for some aircraft installations.

PIN No SIGNAL DESCRIPTION

1 +28 Vdc Connection Not Required

2 28 Vdc RTN Connection Not Required

3 Antenna BITE A ARINC 429 from antenna

4 Antenna BITE SCRN Screen for ARINC 429

5 Antenna BITE B ARINC 429 from antenna

6 Antenna Control A ARINC 429 to antenna

7 Antenna Control

SCRN Screen for ARINC429

8 Antenna Control B ARINC 429 to antenna

9 D/LNA BITE BITE from D/LNA

10 D/LNA SCRN Screen/RTN for D/LNA

11 D/LNA CTL D/LNA on/off control from antenna

12 Serial SCRN1 Connection Not Required

13 RS422 RXD A1 Connection Not Required

14 RS422 RXD B1 Connection Not Required

15 RS422 TXD A1 Connection Not Required

16 RS422 TXD B1 Connection Not Required

17 ATE Pin Connection Not Required

18 115 Vac Hot Aircraft ac power

19 115 Vac Return Aircraft ac power

20 -- Connection Not Required

21 -- Connection Not Required

22 Chassis Ground Chassis Ground

The IGA/HGA Connector is a receptacle -

13-35 insert of the MIL-C-38999 Series III

family: D38999/24FC35PN which mates

with D38999/26FC35S on the cable

1

2

3

21

20

19

18

17

16

15

7

6

5

4

8

9

10

11

12

13

14

22

IGA/HGA Power and Control Connector

Note 4

RF Cable Losses

Note 2

Pin Signal Description

1 Data to SDU A (RS422) Data to SDU A

2 Data to SDU B (RS422) Data to SDU B

3 Data from SDU A (RS422 Data from SDU A

4 Data from SDU B (RS422) Data from SDU B

5 Reserved – RS232 GND 1Connection Not required

6 Spare Connection Not required

7 Chassis Ground Chassis Ground

8 Power Input +8 to +15V SCM Power Input

9 Reserved - Enable RS232 1Connection Not required

10 Reserved – 0V strap output 1Connection Not required

11 Spare Connection Not required

12 Reserved – RS232 Tx 1Connection Not required

13 Reserved – RS232 Rx 1Connection Not required

14 Spare Connection Not required

15 Power Return 0V SCM Power Return

SCM Connector

Note 3

The SCM connector is a DB15 male connector, mating with a DB-15 female

connector on the cable, in accordance with MIL-DTL-24308 (15 pins - gauge 20).

Note 5

Pin Signal Description

Pin A Chassis Ground Chassis Ground

Pin B LNA Control LNA Control

Pin C Future Spare Connection Not required

Pin D Future Spare Connection Not required

Pin E 115 Vac Cold Aircraft AC Power

Pin F 115 Vac Hot Aircraft AC Power

Pin G +28V DC Hot Connection Not required

Pin H LNA BITE LNA Bite

Pin J LNA BITE Return LNA BITE Return

Pin K +28V DC Return Connection Not required

The D/LNA Connector is MS3470L1210P which

mates with MS3476L1210S on the cable

F E D

H A B

K J CG

D/LNA Power and Control Connector

Notes

The IGA mount RF connector (J2), the DLNA mount Antenna connector (J1)

and the DLNA mount RX (SDU input) connector (J2) are all TNC Jack (female)

type connectors.

The DLNA mount TX (SDU output) connector (J3) is a N-Type Jack (female)

type connector.

Size 1 Coax Plug. Radiall

P/N: 620 001 (male center contact)

Size 5 Coax Plug. Radiall P/N:

620 121 (female center contact)

See Note 9.

Quadrax Insert 2T

RF Loss

SDU to D/LNA Loss ≤ 1.4 dB

D/LNA to Antenna Loss ≤ 0.3 dB

D/LNA to SDU 6 dB ≤ Loss ≤ 25 dB

Quadrax Insert 1T

Figure 2-15: TFS Interconnection Block Diagram – Single Aisle Configuration.

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written approval. 29

2.6.3. Interconnection Cables

2.6.3.1. RF Coaxial Cables

The SDU is connected to the DLNA and Antenna (see Figure 2-14), by means of a

RF low loss coaxial cable. The distance between the devices, and the cable selected

for the installation must be such that the cable losses remains within the limits

indicated within Figure 2-15, Note 2. All coaxial cable should be 50 Ohms nominally.

NOTE: Interconnect cables should be routed away from sources of potential

electromagnetic interference. Use shielded wires and cables where necessary.

2.6.3.1.1. RF cable characteristics for the SDU to DLNA Tx port

Maximum Path Loss Nominal Max Power Frequency Range

1.4 dB (see Note) 60 Watts 1626.5 – 1660.5 MHz

2.6.3.1.2. RF cable characteristics for the DLNA to SDU Rx port

Loss Range Nominal Max Power Frequency Range

6 – 25 dB (see Note) 0.5 Watts 1525 – 1559 MHz

2.6.3.1.3. RF cable characteristics for the DLNA to Antenna port

Maximum Path Loss Nominal Max Power Frequency Range

0.3 dB (see Note) 46 Watts 1525 – 1660.5 MHz

NOTE: Applied to the complete RF cable path and not to each component within the

RF path.

2.6.3.2. Power Cables

The SDU mains power cable must be able to handle 115 Vac/5A (see note). The

recommended size is 20 AWG.

NOTE: Switch on surge is approximately 7A for the duration of 200ms.

The SDU to SCM power cable must be able to handle 12Vdc. Cable size is 22 AWG.

2.6.3.3. ARINC 429 connections

ARINC 429 connection cable must be a size 22 single twisted and shielded pair of

wires cable.

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written approval. 30

2.6.3.4. ETHERNET

The recommended Aerospace Grade 100Base-T Ethernet cable is P/N NF 24Q100.

The conductor AWG size (19 strands) is size 24.

Flammability requirements for this cable meet or exceed FAR25.869 requirements.

2.7. SCM General Description

2.7.1. Hardware

The only SCM Part Number available is 82158A Series. This SCM is compatible with

the SA SDU Part Number 82155A Series and all other different SDU configurations.

The SCM hardware meets RTCA/DO-254 level D requirements.

The SCM contains four USIM (Universal Subscriber Identity Module) cards. The SCM

also contains an External Configuration Memory (ECM) storing the Owner

Requirement Table.

2.7.1.1. External Description

The SCM is composed by the following external elements:

 The mounting plate with four attaching holes (1)

 The 15-way D-type (male) socket (2)

 The body of the SCM with one main identification label (3)

3

2

1

Inspect

A

GB

HC

I

D

J

E

K

F

L

PLA

E

1

SDU CONFIGURATION

MODULE (SCM)

MFR

SER

DMF

HW DO-254 Level C

PNR

Minor

REV.

SW PNR

Supply 12V D.C.

CSD 10cm

Wt. 0.25kg MAX

FAA TC x

FCC id xxxxxx-xxxx

Amdt

Figure 2-16: Example of SCM external view.

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written approval. 31

2.7.1.2. Internal Description

The SCM is composed of the following internal parts:

 One gasket between the D-type connector and the Body of the SCM (1)

 One PEC card with a D-type connector attached (2)

 Four USIM cards holders (3)

 A plate attached to the body by four screws and washers (4)

 A body attached to the single PEC card by four screws and washers (5)

1

2

3

5

4

C

SDU CONFIGURATION

Inspect

AG

BHI

DJ

EK

FL

PLA

E1

MODULE (SCM)

MFR

SER

DMF

HW DO-254 Level C

PNR

Minor

REV.

SW PNR

Supply 12V D.C.

CSD 10cm

Wt. 0.25kg MAX

FAA TC x

FCC id xxxxxx-xxxx

A

Figure 2-17: SCM exploded view.

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written approval. 32

2.7.2. ORT Parameters

The ORT is represented by a database containing a set of configuration data for the

exclusive use of the SDU. The ORT is partitioned for two types of parameters in

accordance with ARINC 781:

 User parameters, for operator use

 Secure parameters, for aircraft specific configurations

The ORT parameters are stored within the SCM and SDU, and are used to customise

the operation of the TFS system, allowing various preferences to be set to enable the

efficient use of the equipment within different platform configurations. The SDU and

SCM are delivered with a default ORT.

2.7.3. ORT Synchronisation

At each power up the SDU reads the ORT from the SCM, and compares it with its

locally stored copy. In normal condition the SDU and SCM ORTs should be the same,

but if different the SDU overwrites its local copy with the ORT read from the SCM.

The SDU uses that ORT until the SDU is powered down.

The SDU stores the local copy of the SCM Secure and User ORTs over a power

down in case one of the ORTs from the SCM is not valid when the SDU next powers

up.

NOTE: For more information concerning the operation of the SDU when it determines

that an ORT is not valid refer to the ARINC 781 specification section 3.4.2

‘Configuration & Identification Data’.

NOTE: For more information concerning changes or updates regarding ORT contact

the Thales TFS product support representative.

2.7.4. Basic Operation

When operating, the SCM interfaces with the SDU CCM via the SDU CPM. The SCM

operation will not commence until an input voltage from the SDU is detected.

Alternatively, when removed form the aircraft the SCM will also acknowledge an input

voltage from a personal computer (PC), and will operate as if it were connected to an

SDU.

A single USIM card is required for each Swift Broadband channel operated by the

SDU.

The SCM contains an External Configuration Memory (ECM). The ECM is a non-

volatile memory, which stores the ORT database.

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written approval. 33

2.7.5. Environmental Condition

Refer to Table 2-4.

2.7.6. Identification Label

The main manufacturer label gives the following information (Figure 2-18):

 HW PNR: Equipment part number in alphanumeric form and bar code form

 Minor rev: Minor revisions

 SW PNR: For Owner Requirement Table (ORT)

 MFR: Manufacturer code in alphanumeric and bar code form

 SER: Basic part number and serial numbering alphanumeric and barcode

from.

 DMF: Date of final factory inspection (month and year)

 Amdt: Amendments

 CSD: Compass Safe Distance

 Wt: Weight

 FAA TC: Federal Aviation Administration Type Certificate

 FCC id: Federal Communications Commission identification

PNR

Minor

REV.

SW PNR

Supply 12V D.C. HW DO-254 Level D

CSD 10 cm

Wt. 0.25 kg MAX

FAA TC x

FCC id xxxxxx-xxxx

SDU CONFIGURATION

MODULE (SCM)

MFR

SER

DMF

INSPECT

ABCDEF

LKJIHG

PLA

E1

Amdt

Figure 2-18: Example of SCM Identification Label.

2.7.7. SCM Electrical Characteristics

 Power input: 8 to 15 Vdc. SDU typical supplied voltage 12 Vdc

 Power consumption: 3.6 W or less

 Max current: 300 mA at 12 Vdc

2.7.8. Weight and Dimensions

 For overall dimensions refer to Figure 2-19

 Mass = 0.25kg (0.44Lbs)

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written approval. 34

83.813.1

110

6.1 88.9

101

1. 5

22.5

Inspect

A

G

B

HC

ID

J

E

K

F

L

PLA

E1

SDU CONFIGURATION

MODULE (SCM)

MFR

SER

DMF

HW DO-254 Level C

PNR

Minor

REV.

SW PNR

Supply 12V D.C.

CSD 10cm

Wt. 0.25kg MAX

FAA TC x

FCC id xxxxxx-xxxx

Amdt

Figure 2-19: SCM Overall Dimensions.

NOTE: All measurements given in Figure 2-19 are in mm.

2.7.9. SCM Connector

The SCM connector is a DB15 (15 pins – gauge 20) male connector (see Figure 2-20

below), mating with a DB-15 female connector on the cable. For complete description

of Pin Assignment refer to Figure 2-15, Note 3.

Figure 2-20: Front View of the 15 Pin D-Type Connector.

Chassis Stud

(GND Bonding)

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written approval. 35

2.7.10. Equipment Electric Interconnection Diagram

The SDU interconnection diagram is given in Figure 2- 21 below. The diagram

illustrates all the necessary connection between the SCM and the SDU. For

description of detailed pin-to-pin connection refer to Figure 2-14 and 2-15.

SCM

15 way D-type connector (PL1)

SDU

RS422_Tx_A

0V

+12V

RS422_Rx_A

RS422_Rx_B

RS422_Tx_B

Figure 2-21: SDU/ SCM Interconnection Diagram.

_

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written approval. 36

3. INSTALLATION GUIDELINES

3.1. Introduction

The SDU and SCM should be installed in the aircraft in a manner consistent with

acceptable workmanship and engineering practices, and in accordance with the

instructions set forth in this manual.

To ensure that the system has been properly and safely installed in the aircraft the

installer should make a through visual inspection and conduct an overall operational

check of the system on the ground prior to commissioning to the Customer and or a

flight.

NOTE: Before installing any components or cabling, read all notes contained within

drawings.

3.2. Interchangeability

The SDU and SCM will operate in any installation that complies with ARINC 781.

Therefore, the SDU and SCM are interchangeable only with identical system

components as covered in this manual.

3.3. SDU / SCM Location and Accessibility Guidelines

Where possible the SDU should be installed in a pressurized zone that is also

partially temperature controlled, and mounted on an appropriate ARINC 600

compliant mounting rack. The SDU requires external forced air-cooling.

The SCM should be installed as close to the SDU as possible in order to keep the

cable runs to a minimum.

To determine the best location, the installer must select equipment locations to allow

easy access to these components and their connectors. Equipment location will vary

with aircraft type and design/installation specifications.

The electronic bay, and the cabin hat rack are suitable places to install this unit.

The SDU must be installed in a location that allows the following facilities to be

accessible:

 Front Panel LEDs

 Front Panel TFS system Test Push Button

 Software loading RJ45 connector

CAUTION

BEFORE EQUIPMENT INSTALLATION ENSURE THAT THE AIRCRAFT POWER

SUPPLY CIRCUIT BREAKER IS POSITIONED IN THE OFF CONDITION.

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written approval. 37

3.4. Mounting Tray

The mounting tray used for the installation of the SDU must comply with the design

specifications for the 6 MCU (Modular Concept Unit) form factor. Refer to the ARINC

600 Specification for detailed information regarding the design of compatible

equipment and airframe installations.

Figure 3-1: Example of an ARINC 600, 6 MCU Mounting Tray.

3.5. Cooling

The SDU is designed to accept an installation configuration able to provide forced air-

cooling as defined in Section 3.5 of the ARINC Specification 600.

In normal operation the SDU will be cooled by forced convection with air supplied

from the platform services at a maximum flow rate of 50 kg/hr and a temperature of

up to 400 C. The cooling air will enter the equipment chassis at the bottom via a

plenum chamber and exhaust at the top.

3.6. Power Requirements

It is the responsibility of the installer to select the appropriate gauge of wire for power

connections, and to ensure that the required safety and voltage drop requirements

are complied with.

For SDU power supply specifications refer to:

 2.3.10: ‘SDU Electrical Characteristics’

 Figure 2.8: ‘ Aircraft Power Distribution’

 Figure 2-14: ‘TFS System Interconnection Diagram’

For SCM power supply specifications refer to:

 2.7.8: ‘SCM Electrical Characteristics’

 Figure 2-14: ‘TFS System Interconnection Diagram’

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written approval. 38

3.7. SDU RF Connections

The SDU is connected to the DLNA through a RF coaxial cable. Installation designer

must be aware that the shorter the cable is, the better system performance.

As the SDU/DLNA low loss cable is sometimes almost rigid and it could have a

diameter not compatible with the IGA and DLNA connectors, it is recommended to

install a short portion of a smaller and more flexible cable at each end of this low loss

cable (pig tail type installation).

If necessary, secure the cable by means of evenly spaced collars to prevent the cable

from chafing on aircraft parts and surfaces. These collars must be of a design, which

avoids damaging the cable.

CAUTION

DO NOT EXCEED MINIMUM CABLE RADIUS OF CURVATURE FOR THE

COAXIAL CABLE. USE DUMMY CABLES FOR A FIRST INSTALLATION TO

DETERMINE CABLE RUNS. INSTALL FINAL CABLES ONLY AFTER THIS

MODELING OPERATION.

CAUTION

ONLY PREFORMED RF CABLES SHALL BE CONNECTED TO THE SATCOM

SYSTEM EQUIPMENT. ATTEMPTING TO FORM CABLES OR APPLYING STRESS

TO THE CABLES WHILE THEY ARE CONNECTED TO THE EQUIPMENT

CONNECTORS MAY CAUSE DAMAGE TO THE EQUIPMENT.

NOTE: Interconnect cables should be routed away from sources of potential

electromagnetic interference. Use shielded wires and cables where necessary.

3.7.1. RF Insertion Losses

The SDU RF interface with the Antenna via a DLNA device. The diplexer and LNA are

combined into one unit for installation. The Diplexer function couples transmit signals

from the SDU to the respective antenna. The LNA amplifies the very low level L-band

receive signal from its respective antenna and couples this amplified signal to the

SDU.

For detailed RF insertion losses refer to Figure 2-15 Note 2. To ensure these

requirements are met, some installations need the SDU to be installed in close

proximity to the antenna subsystem components or the use of low loss coaxial cable.

The total loss between the DLNA and the SDU must be in the range 6 to 25 dB. If the

RF cable type being used for a short cable length is less then 6 dB, an attenuator

must be fitted to ensure the required loss is achieved.

3.7.2. VSWR

The Voltage Standing Wave Ratio (VSWR) of all RF cables should be 1.2:1 or better.

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3.8. Bonding Requirements

The bonding of all LRUs to the airframe must not exceed 20 milliohms. However

some aircraft manufacturers or design/installation organisation may require a lower

value than the recommended 20 milliohms.

3.9. SDU Fitting Instructions

Unpack the SDU from the transportation packaging. Perform a visual inspection of the

unit for evidence of damage incurred during transportation. If a claim for damage is to

be made, save the shipping container to substantiate the claim, and contact your

Thales representative. Remove the ESD protection cap on the ARINC 600 connector.

CAUTION

THE SDU IS ELECTROSTATIC DISCHARGE SENSITIVE EQUIPMENT. OBSERVE

STANDARD ESD PROCEDURES WHEN HANDLING THE EQUIPMENT.

Ensure that the electrical supply to the mounting tray back connector is removed.

Carefully place the SDU on its mounting tray and slide it towards the mounting tray

back connector, following the direction of the arrow indicated in figure 3-3.

When the SDU is fully engaged into the connector raise the mounting tray Hold Down

Clamps (see Figure 3-3), over the hooks of the SDU and hand tight in the clockwise

direction.

As the LRU is tightened into position, and in order to prevent electrical pins from

bending, ensure that the SDU is uniformly inserted into the mounting tray back

connector.

Figure 3-3: SDU Installation on to ARINC 600 Mounting Tray.

CAUTION

ENSURE THAT THE THUMBSCREW HOLD DOWN CLAMPS HAVE BEEN

FASTENED, AND THAT THE LRU IS SECURELY HELD INTO PLACE.

SDU

installation direction

Hold Down Clamps

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3.10. SDU Removal Instructions

Ensure that the electrical supply to the mounting tray back connector is removed.

Loose mounting tray Hold Down Clamps (counter clockwise). Ensure that the Hold

Down Clamps are loosened so that the SDU is uniformly extracted out of the

mounting tray back connector. Clear the retaining hooks on the front of the SDU.

Separate the SDU from the mounting tray back connector and extract the SDU by

pulling on the carrying handle at the front of the SDU following the direction of the

arrow indicated in Figure 3-4.

Install an ESD protection cap on the SDU ARINC 600 back connector.

Figure 3-4: SDU Removal from ARINC 600 mounting tray.

3.11. SCM Fitting Instructions

Unpack the SCM from the transportation packaging. Perform a visual inspection of

the unit for evidence of damage incurred during transportation. If a claim for damage

is to be made, save the shipping container to substantiate the claim, and contact your

Thales representative. Remove the ESD protection cap on the D Type connector.

CAUTION

THE SCM IS ELECTROSTATIC DISCHARGE SENSITIVE EQUIPMENT. OBSERVE

STANDARD ESD PROCEDURES WHEN HANDLING THE EQUIPMENT.

Place the SCM to the dedicated mounting fixture and insert the four (1) fixing screws

to finger tightness only. See Figure 3-5. After all four fixing screw have been inserted

tight the screws with an appropriate tool.

Insert the cable from the SDU to the D Type connector (other half from the SDU) and

tighten the aircraft mating connector into the two (2) female screw locks.

SDU

removal direction

Hold Down Clamps

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Figure 3-5: SCM Installation.

CAUTION

ENSURE THAT THE FIXING SCREWS HAVE BEEN FASTENED, AND THAT THE

LRU IS SECURELY HELD INTO POSITION.

3.12. SCM Removal Instructions

Ensure power to the SDU is disconnected.

Loosen the two (2) screw locks that secure the 15-pin D Type connector to the SCM.

See Figure 3-6.

Disconnect the D connector. Bag and stow the cable as required.

Install an ESD protection cap on the SCM D Type connector.

Assuming that the mounting fixture is equipped with anchor nuts, loosen and remove

the four fixings screws that retain the SCM to its mounting fixture while supporting the

SCM. Retain the screws for future installation.

Remove the SCM, and visually inspect it for any signs of damage.

Figure 3-6: SCM Removal.

Fixing Screws (4 off)

D Type Connector (3)

Fixing Screw (1)

Screw locks (2)

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4. INSPECTION AND SYSTEM CHECKOUT

4.1. Inspection/Check procedure

Table 4.1 below provides a visual inspection/check procedure that should be

performed during or after the SDU/SCM installation, or as a periodic maintenance

inspection check of the installation.

EQUIPMENT INSPECTION/CHECK PROCEDURE

Wiring and RF

cables

• Ensure that a continuity check of all the installation wiring

harness had been carried out, and that all the sources are

correctly rated on the correct pins

• Check that none of the cables have been damaged, and

cannot be damaged by components that are installed later

• Check that the cable runs are spaced away from any

moving or hot part that could damage cables when in use

• Verify that the various RF cables are within their minimum

radius of curvature tolerances

• Check that any attenuators that may have been used for

the installation have not been omitted or mismatched

SDU

• Examine the assembly for external condition (absences of

fractures, dents, deformations, cracks, and/or any other

abnormal damage)

• Check that the unit is properly installed and that hold down

clamps are firmly tightened

• Check screws and nuts general condition

• Check that the contact resistance between the SDU/SCM

and a point on the aircraft structure close to the

component does not exceed 20 milliohms

• Check that the correct air cooling and air flow is provided

to the SDU

SCM

• Examine the assembly for external condition (absences of

fractures, dents, deformations, cracks, and/or any other

abnormal damage)

• Check that the unit is properly installed, that all fixing

screws are firmly tightened, and the cable to the SDU is

secure

Table 1: Installation Inspection/Check procedure.

4.2. System Checkout

At this stage of the installation it is assumed that a continuity check of the wiring has

been made, a visual check of the installation harness and RF cabling has been

performed, and that the inspection/check procedure has been carried out.

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4.2.1. Post-installation Test

This test requires that all the Satcom system LRUs (SDU, SCM, DLNA, Antenna) be

connected and operating properly, with a means of displaying any system faults

detected by the LRUs during the BITE (Built In Test Equipment) test. The results of

the test are indicated on the SDU front panel LEDs. Refer to the Testing and Fault

Isolation section for information on the SDU fault detection capabilities.

If no system faults are indicated by the BITE test, then the subsystem installation

should be considered acceptable. If any subsystem LRU fails the test, it must be

returned to the vendor (refer to your vendor customer support).

WARNING

THE RF POWER RADIATED BY THE TFS SYSTEM ANTENNA CAN CAUSE

BODILY HARM. A PERSON IS IN DANGER IN A ZONE WHERE THE POWER

FLUX IS 1 MW/CM2, OR GREATER. DURING SATCOM OPERATION THE

SAFETY DISTANCE FROM THE ANTENNA MUST BE NO LESS THAN 3.5M OR

12 FEET (INTERMEDIATE GAIN ANTENNA). SINCE THERE ARE VARIOUS

POSSIBLE ANTENNA LOCATIONS, IT IS THE RESPONSIBILITY OF THE

OPERATOR TO DETERMINE THE AREA OF HAZARD FOR THEIR TFS SYSTEM

CONFIGURATION AND TO TRAIN PERSONNEL IN GROUND SAFETY

PROCEDURES.

WARNING

DURING ANTENNA OPERATION (TRANSMISSION), ENSURE MINIMUM

EXPOSURE OF ALL PERSONNEL TO ANY REFLECTED, SCATTERED, OR

DIRECT BEAMS.

CAUTION

WHEN TESTING THE COMPLETE TFS SYSTEM (ANTENNA SYSTEM INCLUDED)

REFER TO THE SPECIFIC ANTENNA IMM FOR FURTHER SAFETY

REQUIREMENTS AND SPECIFICATIONS. THE SDU MUST NOT BE POWERED

WITHOUT AN ANTENNA OR SUITABLE LOAD CONNECTED ON THE HIGH

POWER TRANSMIT OUTPUT PORT.

CAUTION

NEVER CONNECT OR DISCONNECT A SATCOM LRU WHEN POWER IS

APPLIED, IN ADDITION, NEVER APPLY HIGH-LEVEL RF SIGNAL TO A

POWERED-DOWN LRU.

CAUTION

ENSURE THAT THE APPROPRIATE ORT DATABASE IS INSTALLED IN THE SCM

AND/OR SDU BEFORE PERFORMING SYSTEM OPERATIONS.

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5. MAINTENANCE

5.1. Introduction

Field lubrication or other maintenance procedures are not required. The design of the

SDU and SCM is such that they do not require field maintenance to maintain

airworthiness. If functional problems occur, the SDU Built-in-Test Equipment (BITE)

capability identifies the faulty LRU. The SDU and SCM maintenance is limited to

replacement on verified failure.

CAUTION

TO AVOID INJURY TO PERSONNEL OR DAMAGE TO EQUIPMENT, ENSURE

ADEQUATE PRECAUTIONS ARE TAKEN WHILE PERFORMING ANY WORK IF

THE ELECTRICAL POWER IS APPLIED TO THE LRUs.

CAUTION

TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFT POWER OFF

BEFORE REMOVING OR INSTALLING LRUs.

5.2. Cleaning of Mechanical Parts

Equipment chassis covers give the necessary protection to keep dust away from

electronic circuits. If cleaning is required this has to be limited to the removal of

particles of dust, oil, grease, condensation, etc and only limited for those equipment

accessible parts. Before any cleaning action is carried out ensure that the equipment

is disconnected from all electrical power sources, and all the necessary ESD

precautions are observed.

For mechanical part cleaning:

 For dust removal use a cleaning wipe, a silk paintbrush or low-pressure

compressed air

 For removal of finger marks, grease, etc, clean the parts with a cleaning wipe

and isopropyl alcohol, exercising care to not damage information labels

CAUTION

MOISTURE AND DIRT CAN CAUSE DAMAGE TO EQUIPMENT.

5.3. Periodic Checks

See Inspection/ Check procedure in Table 1.

5.4. Cabling and Connections

Periodically check cable connectors (recommended) and if required, tighten

connectors as needed with connector manufacturer’s specifications.

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6. TESTING AND FAULT ISOLATION

Information within this section describes how the TFS system, SDU, SCM, and

Antenna failures are monitored detected, and reported.

6.1. BITE Function

The primary purpose of BITE is to assist aircraft maintenance personnel in the

correct maintenance of avionics equipment in a cost effective manner. The BITE

does not contribute to the required function of the TFS system, but makes it easier to

test or debug it.

The SDU controls the TFS system BITE. It collects BITE information from other

LRUs, and can request other LRUs to run tests. The BITE automatically detects

failures, providing a mechanism to discover erroneous behaviour of TFS system

components.

Fault information is reported to a local maintenance system (e.g. CFDS system or

other OMS), and this information is made available to maintenance personnel by

means of discretes and/or LEDs on the SDU front panel. Failures can also be

reported to a dedicated local maintenance function through SNMP (Simple Network

Management Protocol) and the MIB (Management Information Base).

The System BITE failure data is stored in the SDU within a Non-Volatile Memory

(NVM) area. The BITE operates at various levels as indicated in Figure 4-1 below.

Figure 6-1: Example of BITE communication for TFS system.

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6.2. Test Functions

An operator can verify the operational serviceability of the SDU and SCM by means

of a set of testing facilities installed within the SDU. The SDU performs two distinctive

types of test:

 A Power On Self-Test (POST) is automatically activated at SDU start up

 A Person Activated Self Test (PAST) can be initiated by an operator by

depressing a Self-Test push button located on the front panel of the SDU,

(see Figure 2-5 item 17)

6.2.1. POST

At SDU start up (Power On), and with aircraft in the ‘on ground’ condition the FPL

(Front Panel LEDs) will display the following test sequence:

A

pply

power

Start

A

ll LEDs illuminate Amber for

approximately 90 seconds

LEDs flash Green for

approximately 3-5 seconds

LEDs remain in Off condition

for the duration of

approximately 75 seconds

LEDs driven to indicate a

steady Green condition

Figure 6-2: POST LEDs sequence.

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6.2.2. PAST

The PAST function is initiated by depressing the front panel Test Button (This

function is only possible with aircraft on ground). To acknowledge PAST initialisation

all the front panel LEDs start to flash green at the frequency of 2Hz. After

approximately 75 seconds the SDU will transit into Operational Mode with the LEDs

displaying the TFS system serviceability condition.

This feature represents an interactive, manual test facility, which assists in the

following:

 Active search of failures by triggering a series of system diagnostic tests

 Verification testing e.g. after the installation of a replacement unit

 Failure confirmation purpose

NOTE: PAST test can only be initiated after the POST test has completed.

Push front

panel Test

Button

All LEDs extinguish and

remain in Off condition for

approximately 90 seconds

Start

LEDs flash Green for 3-20

seconds

LEDs driven to Indicate

a stead

y

Green condition

Time variations are

due to ORT

synchronisation

Figure 6-3: PAST LEDs sequence.

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6.3. Fault Isolation

6.3.1. Failures

Failures are reported to an operator by means of a set of multicoloured LEDs located

on the SDU front panel. LEDs can enter the following steady states:

 Normal equipment operation indicated by the relevant LEDs displayed in a

steady Green condition

 Equipment Hard Failures are indicated by all relevant LEDs displayed in a

steady Red condition

 Partial equipment failures are indicated by all relevant LEDs displayed in a

steady Amber condition

 An LED in OFF (extinguished) condition indicates that the relevant

equipment and or a resource is not active or not installed

6.3.2. Front Panel Indications

Table 2 provides LED status decoding information.

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LED Name Flashing Green Steady Green Amber Red Off

SDU SDU in Self-Test

SDU OK

Partial Failure (Not Indicted)1 or

ARINC 429 / AFDX / RS-422

Bus Failure3 SDU Failed (Indicted)2 SDU Not Powered

SCM SDU in Self-Test SCM/USIM(s) OK SCM Memory Fail

(Not Indicted)1 or RS-422 Bus

Failure3

USIM Read/Write Fail. No

attempt at SBB registration SCM Not Installed or SDU

Not Powered

Antenna SDU in Self-Test Antenna OK Partial Failure (Not Indicted)1 or

ARINC 429 Bus Failure 3 Antenna Failed (Indicted) 2 SDU Not Powered

DLNA SDU in Self-Test DLNA OK N/A DLNA Failed

(Indicted)2 SDU Not Powered

Ext. HPA SDU in Self-Test NA NA NA NA

Ext. BSU SDU in Self-Test NA NA NA NA

Ext. Data

Bus SDU in Self-Test All Data Buses (ARINC 429

/ AFDX / RS-422) OK

Nav Data not available. ARINC

429 Bus from IRS(s) inactive or

IRS Data invalid 4

Bus Failed3 (ARINC 429 /

AFDX / RS-422) SDU Not Powered

ORT/Config. SDU in Self-Test ORT(s)/Hardware

Configuration Straps ORT Minor Failure5

(Not Indicted)1

ORT Major Failure6 or

Hardware Configuration

Straps Parity Failure

(Indicted)2

SDU Not Powered

Sat. Link #1 SDU in Self-Test Channel #1 Service

Available, ie Logged-On or

Registered

Channel #1

attempting Log-On or

Registration N/A Channel #1 Not attempting

Log-On or Registration7

Sat. Link #2 SDU in Self-Test Channel #2 Service

Available, ie Logged-On or

Registered

Channel #2

attempting Log-On or

Registration N/A Channel #2 Not attempting

Log-On or Registration7

NOTE: See next page for list of Explanatory Note.

Table 2: Front Panel indications.

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List of Explanatory Notes for Table 2

1. Not Indicted means that there is an equipment ‘partial’ failure such that

service Registration / Log-On is still attempted.

2. Indicted means that there is an equipment failure such that Registration / Log-

On is not attempted.

3. In the event of a Bus Inactive Failure, the ‘Data Bus’ LED illuminates Red and

the appropriate LRU status LEDs illuminate Amber, e.g. if the SDU reports

that the Antenna to SDU bus is inactive or the Antenna reports that the SDU

to Antenna bus is inactive, then the ‘Data Bus’ LED illuminates Red and the

SDU and Antenna LEDs illuminates Amber.

4. This is a special case. There will be frequent legitimate occurrences of IRS(s)

being switched off whilst On-Ground and even after an IRS is switched on;

there is an alignment period, during which the Nav Data is invalid. Under

these circumstances, the only action is to illuminate the ‘Data Bus’ LED

Amber, irrespective of whether in On-Ground or In-Air state.

5. The ORT/Configuration LED illuminate Amber in the following circumstances:

a. Type 1 ORT Synchronization Minor Failure – Secure ORT within SCM

- If the Secure ORT read from the SCM is not valid and if ‘local copy’

Secure ORT is valid.

b. Type 4 ORT Synchronization Failure - User ORT within SCM - If the

User ORT read from the SCM is not valid AND if ‘local copy’ User

ORT is valid.

c. Type 5 ORT Synchronization Failure - User ORT in SDU - if SDU User

ORT is invalid.

6. The ORT/Configuration LED illuminates Red in the following circumstances:

a. Type 1 ORT Synchronization Major Failure - Secure ORT within SCM

- If the Secure ORT read from the SCM is not valid AND if ‘local copy’

Secure ORT is not valid.

b. Type 2 ORT Synchronization

c. Type 3 ORT Synchronization Failure - Secure ORT in SDU that is

integral part of SW - if SDU Secure ORT is invalid.

d. Hardware Straps Parity Failure. SDU be indicted.

7. There are many reasons why a channel will not attempt Log-On or

Registration, including (but not limited to), OCXO warming up, equipment

indictment, commanded Log-Off or De-Registration.

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6.3.3. Fault Logging

All information of degraded and abnormal equipment function will be logged internally

and made available to a dedicated local maintenance system (e.g. CFDS).

6.3.4. Service Availability Discretes

The status of various system functions can be reported by means of the Service

Availability Discretes available on the ARINC 600 connector.

Function Pin

Allocation Steady State Open Circuit Steady Ground1

SDU Not Powered MP 15F SDU Powered SDU Not Powered

System Failed MP 11F System OK System Failed2

SDU Failed MP 12E SDU OK SDU Failed3

SCM Failed MP 12F SCM OK or not installed SCM Failed4

Ext HPA Failed MP 13E Ext HPA OK or not installed Ext HPA Failed

DLNA Failed MP 13F DLNA OK DLNA Failed

Antenna Failed MP 14E Antenna OK Antenna Failed

Ext BSU Failed MP 14F BSU OK or not installed BSU Failed

Bus Failed5 MP 15E All external data buses OK

(ARINC 429/AFDX/RS422) Bus Failed (ARINC

429/AFDX/RS422)

Sat Link #1 Not

Available MP 11E Satcom Channel #1 Logged

On/Registered

Satcom Channel #1

Not Logged On/Not

Registered

Sat Link #2 Not

Available TP 01K Satcom Channel #2 Logged

On/Registered

Satcom Channel #2

Not Logged On/Not

Registered

Table 3: SDU Service Availability Discretes.

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List of Explanatory Notes for Table 3

1. The ‘Steady Ground’ state corresponds to the equivalent LED Red state,

except for the Sat Link #1 and #2 Not Available discretes, for which the

‘Steady Ground’ state corresponds to the equivalent LED Off or Amber states.

2. The System Failed discrete ‘Steady Ground’ state corresponds to one or

more LEDs being illuminated red.

3. SDU Failed discrete only to be asserted in the event that an SDU H/W or S/w

failure is detected, not in the event that there is an ORT or configuration

straps parity failure. In the latter case, only the System Failed discrete should

be asserted.

4. SCM Failed discrete only to be asserted in the event that an SCM H/W failure

is detected, not in the event that there is an ORT failure. In the latter case,

only the System Failed discrete should be asserted.

5. The Bus Failed discrete provides no indication of activity on the Ethernet

buses.

6.3.5. Service Availability Discrete Lamps

The Service Availability Discretes have open circuit and ground states that are

capable of driving incandescent lamps connected to an external supply.

Typically, each discrete is fed via one or two (in parallel) incandescent lamps to an

aircraft 28 Vdc supply. This 28 Vdc supply can be dimmed to approximately 14 Vdc

for night time operation. The 28 Vdc is a nominal value and can vary as defined in

RTCA/DO-160E. A typical incandescent lamp would be 28Vdc, 20mA.

Each Service Availability Discrete is able to continuously sink at least 50mA and be

capable of holding a cold inrush current of up to 490 mA during the first 10

millisecond of activation as per ARINC 781.

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7. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

Maintenance requirements and instructions for continued airworthiness of the TFS

SDU and SCM components are contained in the paragraphs that follow.

Installation of SDU and SCM on an aircraft by an amendment to the Type Certificate

(TC), Supplemental Type Certificate (STC) or Form 337 obligates the aircraft

operator to include the maintenance information supplied by this manual (and listed

below) in the operator’s Aircraft Maintenance Manual and the operator’s Aircraft

Scheduled Maintenance Program.

 Maintenance information for SDU and SCM, TFS LRUs (system

description, removal, installation, testing, etc.)

 The part numbers (see section 2) of the LRUs being installed (SDU and

SCM) should be placed into the aircraft operator’s appropriate aircraft

Illustrated Parts Catalogue (IPC).

 Wiring connection information contained in this manual (see sections 2

and 3) should be placed into the aircraft operator’s appropriate Wiring

Diagram Manual.

 The SDU maintenance is considered as an “On-condition”, and as such

no additional maintenance is required other than a check for security and

operation at normal inspection intervals.

 The SCM equipment is subject to minimal preventative maintenance,

which is specific to life limitations associated to the internal USIM cards.

For further details refer to your Thales representative.

 If a system LRU is inoperative remove the specific unit, secure cables and

wiring, collar applicable switches and circuit breakers, and placard them

inoperative. Revise equipment list and weight and balance as applicable

prior to flight and make a log book entry that the unit was removed (refer

to section 91.213 of the FAR or the aircraft’s Minimum Equipment List

(MEL).

 SDU and SCM can be repaired by an Approved Maintenance

Organization

 Once repaired, reinstall the LRU in the aircraft in accordance with the

original Form 337 approved data or instructions in this manual. Perform a

Return to Service test of the system and approve it for return to service

with a logbook entry required by section 43.9.

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

Thales Avionics Limited Topflight SATCOM Satellite data unit Satellite Data Unit SDU

Installation and maintenance manual

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