Thales Avionics TFS-SDU82155D Topflight Satcom Satellite Data unit User Manual Tpage

Thales Avionics Limited Topflight Satcom Satellite Data unit Tpage

IM Manual

86, Bushey RoadRaynes Park, LondonSW20 0JWTel: +44 (0)20 8946 8011Fax: +44 (0)20 8946 75301Jun 30/2008Revision No. 01First Issue: Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval INSTALLATION AND MAINTENANCE MANUALSatellite Data Unit (SDU)82155 SeriesSDU Configuration Module (SCM)82158 Series
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 SeriesiJun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Section 1 INTRODUCTION Page1.1. Purpose of Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11.2. Special Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11.3. Contact Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21.4. Scope of Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21.5. Reference documents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21.6. Compliance to Regulations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3A. Federal Communication Commision . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3B. European Aviation Safety Agency. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3Section 2 DESCRIPTION Page2.1. TFS Satellite Communication System Domain . . . . . . . . . . . . . . . . . . . . . . . . . 2-12.2. TFS System Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12.3. system Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2A. Single Aisle TFS System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2B. SDU Type 82155D TFS system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32.4. SDU Component Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4A. Hardware. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4(1) SDU Type 82155A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4(2) SDU Type 82155D . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4B. Functionality . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5(1) SDU Type 82155A.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5(2) SDU Type 82155D.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5C. Software . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6D. ORT Parameters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6E. General Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6F. Sub-modules Basic Detailed Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7G. Operating Environment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8(1) Normal Operating temperature: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8(2) Cooling:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8(3) Heat dissipation: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8H. Environment Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8I. Identification Label . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10J. Weight and Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12(1) SDU Type 82155A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12(2) SDU Type 82155D . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12K. SDU Electrical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-152.5. System Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15A. Aircraft Power Utility Service. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15B. Avionics Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16C. Cockpit Interfaces (SDU Type 82155D only) . . . . . . . . . . . . . . . . . . . . . . 2-17D. Maintenance System Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-172.6. SDU Configurable Pinout and Pin Description . . . . . . . . . . . . . . . . . . . . . . . . 2-17A. Mandatory Configuration Pins. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 SeriesiiJun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 2.7. SDU Interconnect Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18A. ARINC 600 Standard Interwiring Connector . . . . . . . . . . . . . . . . . . . . . . . 2-18(1) ARINC 600 Pin Assignment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19B. Electrical Interconnection Diagrams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-24C. Interconnection Cables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35(1) RF Coaxial Cables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35(2) Power Cables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-36(3) ARINC 429 Connections. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-36(4) Ethernet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-362.8. SCM Component Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-36A. Hardware. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-36(1) External Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-36(2) Internal Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-37B. ORT Parameters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-38C. ORT Synchronisation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-39D. Basic Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-39E. Environment Condition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-39F. Identification Label . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-40G. SCM Electrical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-41H. Weight and Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-41I. SCM Connector. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-42J. Equipment Electrical Interconnection Diagram . . . . . . . . . . . . . . . . . . . . . 2-42Section 3 INSTALLATION GUIDELINES Page3.1. Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13.2. Interchangeability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13.3. SDU/SCM Location and Accessibility Guidelines . . . . . . . . . . . . . . . . . . . . . . . 3-23.4. Mounting Tray . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-23.5. Cooling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-33.6. Power Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-33.7. SDU RF Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-4D. Insertion Losses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-4E. Product InterModulation (PIM) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5F. VSWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5G. Torque Settings. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5H. Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-53.8. Bonding Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5Section 4 INSPECTION AND SYSTEM CHECKOUT Page4.1. Inspection/Check Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1A. Check Wiring and RF cables. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1B. Check SDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1C. Check SCM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-24.2. System checkout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-2A. Post-Installation Test. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-2
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 SeriesiiiJun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Section 5 FAULT ISOLATION Page5.1. Bite Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-15.2. Test Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2A. OMS or CFDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2B. BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2(1) POST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-3(2) PAST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-45.3. fault isolation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-5A. Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-5B. Front Panel Indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-5C. Fault Logging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-8D. Service Availability Discretes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-8E. Service Availability Discrete Lamps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-9F. CFDS/ARINC 604 BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-9Section 6 MAINTENANCE Practices Page6.1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-16.2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-16.3. Procedure For The SDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2A. Removal and Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2(1) Remove the SDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2(2) Install the SDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3B. Adjustment Procedure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3C. Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3D. Return to Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-36.4. Procedure For The SCM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4A. Removal and Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4(1) Remove the SCM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4(2) Install the SCM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4B. Adjustment Procedure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-5C. Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-5D. Return to Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-56.5. Cleaning of Mechanical Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-56.6. Periodic Checks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-66.7. Cabling and Connections. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-66.8. Instructions For Continued Airworthiness . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-6Section 7 COMMISSIONING Page7.1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1A. Registration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1B. Classic Packet Data Verification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-3C. Classic Cockpit Voice Calls. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-3D. SBB Cabin Wifi Data Connectivity (Background Context) . . . . . . . . . . . . . 7-3E. SBB Cabin Wifi Data Connectivity (Streaming Context) . . . . . . . . . . . . . . . 7-4F. Cabin VoIP service . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-5G. Cabin ISDN Data service . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-5H. Cabin ISDN Voice service . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-6I. Cabin GSM Call and SMS Service . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-7
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 SeriesivJun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 SeriesvJun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval RECORD OF REVISIONSRevision No:Revision DateDate InsertedBy Revision No:Revision DateDate InsertedBy
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 SeriesviJun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 SeriesviiJun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval List of Abbreviationsac Alternating CurrentACARS Aircraft Communication Addressing and Report-ing SystemADL Airborne Data LoaderAES Aeronautical Earth StationAGS Airborne GSM Server AIM Antenna Interface MountingAMO Approved Maintenance OrganizationAMU Audio Management UnitAOR-E Atlantic Ocean Region-EastAOR-W Atlantic Ocean Region-WestAPM Avionics Processor ModuleARINC Aeronautical Radio IncATE Automatic Test EquipmentBGAN Broadband Global Area NetworkBITE Built In Test EquipmentBSU Beam Steering UnitCCM Channel Card ModuleCDU Control Display UnitCFDS Cenralised Fault Display SystemCMM Component Maintenance ManualCMU Communication Management UnitCPM Communication Processor Moduledc Direct CurrentDLNA Diplexer and Low Noise AmplifierEASA European Aviation Safety Agency
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 SeriesviiiJun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval ECM External Configuration MemoryECS Environmental Control SystemEMC Electromagnetic CompatibilityESD Electro Static DischargeESDS Electro Static Discharge SensitiveFMHPA Flange Mounted High Power AmplifierFPL Front Panel LEDGES Ground Earth StationGNSS Global Navigation Satellite SystemGPS Global Positioning SystemHPA High Power AmplifierIGA Intermediate Gain AntennaIMEI International Mobile Equipment IdentityIMM Installation and Maintenance ManualIMSI International Mobile Subscriber IdentityINMARSAT International Maritime Satellite OrganizationIOR Indian Ocean RegionIP Internet ProtocolIPC Illustrated Parts ListIRS Inertial Reference SystemI/O Input/OutputISDN Integrated Service Digital NetworkLED Light Emitting DiodeLES Land Earth StationLRU Line Replaceable UnitmA MilliAmpereMCDU Multi-function Control and Display UnitList of Abbreviations
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 SeriesixJun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval MCU Modular Concept UnitMEL Minimum Equipment LevelMES Mobile Earth StationMIB Management Information BaseNVM Non Volatile MemoryOMS Onboard Monitoring SystemORT Owner Requirements TableOCXO Oven Controlled Crystal OscillatorPAST Person Activated Self TestPC Personal ComputerPLMN Public Land Mobile NetworkPNR Part NumberPOR Pacific Ocean RegionPOST Power On Self-TestPPPoE Point To Point Protocol over EthernetPSM Power Supply ModulePSTN Public Switched Telephone NetworkRF Radio FrequencySA Single AisleSATCOM Satellite CommunicationSBB SwiftBroadbandSCDU Satellite Control Display UnitSCM SDU Configuration ModuleSDU Satellite Data UnitSIM Subscriber Identity ModuleSIS Standalone Interface SystemSNMP Simple Network Management ProtocolList of Abbreviations
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 SeriesxJun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SRU Shop Replaceable UnitSTC Supplemental Type CertificateSW SoftwareTCP/IP Transmission Control Protocol/Internet ProtocolTFS TopFlight SatcomUMTS Universal Mobile Telecommunication SystemUSIM Universal Subscriber Identity ModuleWi Fi Wireless FidelityWLAN Wireless Local Area NetworkWOW Weight On WheelsList of Abbreviations
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series1-1Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 110000INTRODUCTION1.1. PURPOSE OF MANUALThis manual sets forth installation and maintenance guidelines, and theory of operationfor the THALES TopFlight Satcom (TFS) Satellite Data Unit (SDU), and SDUConfiguration Module (SCM). The SDU and SCM installation specific and generalguidelines contained within this manual are supported by mechanical and electricalinterconnection drawings and interface information. Drawings should be reviewed bythe installation organisation, and any requirements specific to a particular airframeshould be assessed before installation is commenced.The Manual covers the following topics:a. Title Pageb. Record of Revisionsc. Table of Contentd. Introductione. Descriptionf. Installation Guidelinesg. Inspection and System Checkouth. Fault Isolationi. Maintenance Practicesj. Commissioning.1.2. SPECIAL PRECAUTIONSAdvisory notes presented within this manual such as: ‘Warnings, Cautions and Notes’are applicable to the TFS system as follows:a. A WARNING is used to alert the reader to possible hazard which may cause loss of life or physical injuryb. A CAUTION is used to denote the possibility of damage to materiel but not danger to personnelc. A NOTE is used to convey, or draw attention to, information that is extraneous to the immediate subject of the text.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series1-2Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 1.3. CONTACT INFORMATIONFor any queries related to information contained within this Manual contact thefollowing:THALES TFS Project Manager86 Bushey RoadRaynes Park, LondonSW20 0JW, UKTel. +44 (0)20 8946 8011Fax. +44 (0)20 8946 75301.4. SCOPE OF MANUALThe Thales SDU and SCM comply with the design requirements set forward in theARINC 781 Characteristic. An ARINC 781 compliant system is intended to support oneor 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 providingthose services highlighted above. The SDU and SCM covered in this manual supportInmarsat Class 3A, 6 and 7 services only.1.5. REFERENCE DOCUMENTSThe following publications provide additional useful information:Table 1.1 Reference DocumentsTHALES SCM Component Maintenance Manual 44-35-33THALES SDU Component Maintenance Manual 44-35-32EMS AMT-3500 Intermediate Gain Antenna Subsystem Installation Manual MN-1242-20047Mark 33 Digital Information Transfer System ARINC 429Air Transport Avionics Equipment Interfaces ARINC 600Airborne Computer High speed Data Loader ARINC 615Ethernet Based Data loading ARINC 615A Mark III Aviation Satellite Communication (Satcom) Sys-tem AvionicsARINC 781
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series1-3Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 1.6. COMPLIANCE TO REGULATIONSA. Federal Communication CommisionThe SDU is designed to be compliant with part 15 and part 87 of the FederalCommunication Commission (FCC) regulationsB. European Aviation Safety AgencyThe installation must be compliant to the following European Aviation Safety Agency(EASA) regulations:• 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.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series1-4Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-1Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 220000DESCRIPTION2.1. TFS SATELLITE COMMUNICATION SYSTEM DOMAINSatellite Communications (SATCOM) systems provide users with long-range voice anddata communication by accessing global satellite and ground communications networks.The introduction of Pico-Cells on aircrafts, and the I3 and I4 INMARSAT constellationof geostationary satellites have been the enabling technologies for the development ofsignificantly smaller, more capable terminals such as the Thales TopFlight Satcomsystem.SwiftBroadband (SBB) is the aeronautical service, which operates on the INMARSATBroadband Global Area Network (BGAN) infrastructure. SBB supports CircuitSwitched and always-on TCP/IP data (packet switched) services. Thales SBB TopFlightSatcom system supports the Inmarsat Classes of service 3A, 6, 7 and Classic Aero H+.2.2. TFS SYSTEM OVERVIEWThe TFS system conforms to the Aeronautical Radio Incorporated (ARINC) 781Characteristic, and interfaces with onboard avionics and communication equipment toprovide the aircraft with a range of communication services by transmitting andFigure 2.1 Example of TFS communications system overviewInmarsat domainTFS SystemI4 SatelliteBackbone NetworksIP, PLMN, PSTNUser TerminalsAeronautical SegmentSatelliteAccessStationSpace Segment Inmarsat domainTav_e_0000700_00Antenna
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-2Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval receiving L Band signals to and from the fourth generation of INMARSAT satellites. Forthis purpose the INMARSAT satellite constellation is connected to the ground backbonetelecommunication network through Satellite Access Stations (SAS) operated by serviceproviders.2.3. SYSTEM CONFIGURATIONSTFS Satcom may be installed in different aircraft configurations, some examples are asfollows:A. Single Aisle TFS SystemThe Single Aisle TFS System consists of the following Line Replacement Units (LRU):• One Satellite Data Unit (SDU) • One SDU Configuration Module (SCM)• One Diplexer Low Noise Ampliier (DLNA)• One Intermediate Gain Antenna (IGA) or High Gain Antenna (HGA)• RF cables.Figure 2.2 illustrates a typical aircraft installation of the TFS for a Single Aisle Aircraft.Figure 2.2 Example of Single Aisle TFS system interfacingSCMSDU DNLA ARINC 781ANTENNA(Contains BSUFunctions)PowerARINC 429(Multicontrol)ARINC 429(Bite from Antenna)RFRF RxRF TxBite/ControlExternalInterfacesTav_e_0000706_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-3Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval B. SDU Type 82155D TFS systemThe TFS System consists of the following Line Replacement Units (LRU):• One Satellite Data Unit (SDU) • One SDU Configuration Module (SCM)• One Diplexer Low Noise Ampliier (DLNA)• One Intermediate Gain Antenna (IGA) or High Gain Antenna (HGA)• One Flange-Mounted High Power Amplifier (FMHPA) (If required)• RF cables.Figure 2.3 illustrates a typical aircraft installation of the SDU Type 82155D System.Figure 2.3 Example of SDU Type 82155D TFS system interfacingSCMSDU DNLA ARINC 781ANTENNA(Contains BSUFunctions)PowerARINC 429(Multicontrol)ARINC 429(Bite from Antenna)RFRF RxRF TxBite/ControlExternalInterfacesRF TxFMHPABiteTav_e_0000707_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-4Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 2.4. SDU COMPONENT DESCRIPTIONA. HardwareNOTE: SDU hardware is targeted at RTCA/DO-254 level C.The SDU hardware meets RTCA/DO-254 level D requirements, and it is composed ofthe following internal sub-assemblies (Refer to Figure 2.4):(1) SDU Type 82155A• 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.(2) SDU Type 82155D•HPA • CCM x 2•CPM• PSM•OCXO•APM• Backplane• Front Panel.The SDU enclosure is constructed of machined lightweight aluminium alloy and it ispackaged in an ARINC 600 6 Modular Concept Unit (MCU) housing suitable formounting in the equipment bay of an aircraft.Two hold-down clamps are used to secure the SDU, permitting it to be firmly held inposition in the mounting rack. A handle fitted on the front panel of the SDU permitsremoval, installation and carrying of the SDU.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-5Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval B. FunctionalityThe Functionality of the SDU is as follows:(1) SDU Type 82155A.Single Channel Class 3A SBB Services.(2) SDU Type 82155D.Dual Channel Class 6 and 7 SBB Services with reversion to Dual S64 Services.Classic Aero Voice and Data Services (Aero I , Aero H+ (up to 2 x Voice and 1 x Data)).Figure 2.4 Example of SDU sub-system modules exploded
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-6Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval C. SoftwareThe software in the SDU can be considered as being supplied in two elements, onecontained within the CCM the other operating on the SDU processors (CPM & APM).The SDU’s application software primarily functions as the system controller providingsystem level tasks such as CCM control, BITE reporting, Avionics interfacing viaARINC-429 (including Inertial Reference System (IRS)) and providing externalinterfaces (such as Ethernet) as well as routing functions between the external interfacesand the CCM as necessary.The SDU’s APM and CPM application software meets RTCA/DO-178B level Drequirements, and the CCM application software meets RTCA/DO-178 level E (Level Dfor Classic only) requirements.D. ORT ParametersThe primary source of Owner Requirement Table (ORT) is the SCM ORT and is alsostored inside the SDU. The ORT database contains configuration data that is used tocustomize the operation of the TFS system. It allows various preferences to be set toenable the efficient use of the equipment in normal operation. The SDU is delivered tocustomers with a default ORT.E. General OperationThe SDU controls and processes all essential data in order to manage the reception andtransmission of data through the satellite link. The SDU controls the set-up of therequired 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 ofaircraft. That is cabin only, cockpit only or cabin and cockpit services.The SDU converts digital/audio inputs to Radio Frequency (RF), and contains a HPAfunction providing the necessary output power to support communication between theaircraft and the satellite. It also controls the associated antenna sub-system and uses theSCM for its own configuration data purposes.When the distance between the SDU and the DLNA would require an RF cable with aloss of >1.4dB or if more than 30W of RF power is required when cable loss is < 1.4dB,an FMHPA may be placed between the SDU and the DLNA to amplify the signal. TheSDU internal HPA will then run at a reduced power output.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-7Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 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 F. Sub-modules Basic Detailed OperationThe Front Panel assembly gives visual indications for system status, externalmaintenance interface connections, the SDU Person Activated Self-Test (PAST) pushbutton and a connector for the Standalone Interface System (SIS).The Backplane assembly makes interconnections between external interfaces and theSDU internal sub-assemblies.The APM provides interfacing to external avionics. It receives aircraft position, speedand heading information from external avionics via ARINC 429, and updates the CCMwith position information every second. The APM manages satellite selection based onaircraft position, and maintains antenna pointing to the wanted satellite beam steeringvia ARINC 429. The APM manages RF 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 andRS422) and analog audio (cockpit 4-wire).The CCM converts user’s input/output data to signals suitable for transmitting andreceiving L-Band signals using the satellite link.The HPA module amplifies the low level RF signals from the CCM to produce highpower output prior to connection to the antenna.The PSM operates from 115 Vac and supplies low level dc power supplies to SRUswithin the SDU and 12 Vdc to the SCM.The OCXO provides 10 MHz clock reference signal for the CCM circuit.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-8Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval G. Operating Environment(1) Normal Operating temperature:Between -15o C (5o F) and +70o C (158o F)NOTE: Short term operating Temperature - 40oC(2) Cooling:Forced air type in accordance with ARINC 600, requiring minimum airflow rate of 50kg/hr, blowing from bottom to top. Maximum inlet air temperature +70o C (158o F)(3) Heat dissipation:250W (assuming 100% duty cycle with HPA operating at 30W output).NOTE: Typically 170W with dual SBB channels.H. Environment ConditionsThe SDU complies with the RTCA/DO-160-E (ED-14E). The environmentalqualifications categories complied with, are as per listed refer (Table 2.1).Table 2.1 Environmental Test categories for SDU and SCMRTCA DO-160E (ED-14E) Environmental CategoriesSection Condition Category4.0 Temperature/Altitude A24.5.4 Loss of Cooling V5.0 Temp Var B6.0 Humidity B7.0 Shock/Crash B,E8.0 Vibration RVibration Curve C9.0 Explosion E10.0 Waterproof X11.0 Fluids X12.0 Sand/Dust X13.0 Fungus F
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-9Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 14.0 Salt Fog X15.0 Magnetic Effect A16.0 Power Input A(CF), A(NF), A(WF)Harmonics H17.0 Voltage Spike A18.0 Conducted Audio Susceptibility K(CF), K(NF) K(WF)19.0 Induced Signal Susceptibility CW20.0 RF Susceptibility TT21.0 RF Emissions M22.0 Lightning Induced A3G33 (SDU 82155A only)23.0 Lightning Direct Effects X24.0 Icing X25.0 ESD TBC26.0 Fire, Flammability TBDRTCA DO-160E (ED-14E) Environmental CategoriesSection Condition Category
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-10Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval I. Identification LabelFigure 2.5 represent the SDU Front Panel Identification Panel, for detalied descriptionof the numbered field Refer to Table 2.2.Figure 2.5 Example of SDU Front Panel LegendHW PNRMinor Rev.SW PNRTESTSDUSCMAntennaHW PNR 82155X30 SW PNRATEST PORTDLNAExt. HPAExt. BSUExt. Data BusORT/Config.Sat. Link #1Sat. Link #2LED INDICATIONS MAY RELATE TOOTHER EQUIPMENT OR AIRCRAFT WIRINGCAUTIONTHIS EQUIPMENTREQUIRES FIELDLOADABLE SOFTWAREENSURE CORRECTSOFTWARE IS LOADEDREFER TO AMMSupply 115VACCSD cmWt. 9.5kg (max)FAA TCFCC idHW DO-254 Level CSW DO-178B Level DDO-160E Env. Cat[(A2)Z]BAE[SC]EXXXFXA[A(WF)]A[R(WF)][ZW][RR]M[A3G33]XXACSATELLITE DATA UNIT (SDU)MFRSERDMFMFR K0385SER NODMFINSPECTAMDT ABCDEFGH I J KLSSI1821634510 9781416CAUTION CAUTIONSURFACEHOTTav_e_0000727_001112131517
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-11Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Table 2.2 SDU Front Panel LegendSDU Front Panel Legend1 Manufacturer’s Name2 Voltage Supply,Compass Safe Distance3 Manufacturer’s Code4 Equipment Serial Number5 Date of Final Factory Inspection (month and year)6 Amendment Label7 Inspection Stamp8 Standalone Identification System, Weight of Equipment, FCC ID, Hardware and Software Compliance Reference9 Caution labels10 Carrying Handle11 Hold Down Lugs12 Status Light Emitting Diodes (LEDs)13 Ethernet RJ45 Maintenance Connector14 Field Loadable Software Warning15 Push To Test Switch16 Software Part Number17 Hardware Minor Revision18 Hardware Part Number
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-12Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval J. Weight and DimensionsNOTE: Weights and measurements in this manual use both U.S (inches) and S.I.(metric, m.m.) values.(1) SDU Type 82155A• For overall dimensions (refer to Figure 2.6)• Form Factor: ARINC 600, 6 MCU• Mass: 9.5 kg (21 lb) maximum.(2) SDU Type 82155D• For overall dimensions (refer to Figure 2.6)• Form Factor: ARINC 600, 6 MCU• Mass: 11 kg (24 lb) maximum.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-13Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.6 SDU Overall Dimensions.9.65 (0.38")CofG Dim. 'C' (See Table)193.5 (7.62")320.2 (12.6")3.2 (0.12")382.6 (15") REF.62.4 (2.46")190.5 (7.5")3.6 (0.14")285.7 (11.25")34.6 (1.36") REF.123.9 (4.88")116.8 (4.56")168.9 (6.652) REF.COOLING OUTLET AREA (ARINC)50.9 (2") 53.4 (2.1")52.3 (2")217.7 (8.6")5.4 REF (0.21").179.9 (7.1")5.6 (0.22")1.4 (0.05")141.6 7.78")CofG Dim. 'B' CofG Dim. 'A' 2.2 (0.1")132.1 (5.2")190.9 (7.5") REF.197.1 REF.11.73 (0.46")188.0 (7.4")Tav_e_0000733_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-14Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-15Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval K. SDU Electrical Characteristics• Normal Operation, Supply voltage: 100 to 122 Vrms, ac, Frequency Range 360 Hz to 800 Hz• Power consumption: 280W maximum• RF Power Rating: Internal HPA variable up to 30W depending upon services required.2.5. SYSTEM INTERFACESThe SDU interfaces with various aircraft systems.A. Aircraft Power Utility ServiceThe TFS interfaces with the aircraft primary power generator (Refer to Figure 2.7):Figure 2.7 TFS example of aircraft Power Distribution diagramSDUDLNA IGA/HGASCMAircraftPowersupply115 Vac Cold115 Vac HotChassis Ground115 Vac-7.5 AMP Circuit Breaker BP01BP05BP03Power Source 12 VDC SCM Power ReturnMP01DMP02DFE 18 19A22Tav_e_0000712_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-16Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval B. Avionics InterfacesThe following avionics interfaces are supported:• External 35W FMHPA• Specific to type Cabin Network domain• ARINC 781 High Gain Antennas (HGA) and Intermediate Gain antennas (IGA)• ARINC 429 interfaced equipment (IRS, Global Positioning System (GPS), MCDU, CMU, CMS)• EASA/FAR 25.1309 Equipment, systems and installations•DLNA•SCM• Nav Data from Navigation Systems.In order to comply with transmit burst time, INMARSAT requires the SDU to beprovided with the aircraft present position within 1500m in three dimensions, referencedto WGS-84 (GPS) . In order to comply with this requirement the TFS SDU requiresARINC 429 Nav Data labels (Refer to Table 2.3). The values apply to aircraft whereonly one Nav Data bus is connected.For Classic and S64 only IRS present position is required.Table 2.3 ARINC 429 Nav Data Labels - HybridPARAMETERS ARINC 429 LABELSLatitude GNSS - Hybrid/Inertial 254/InertialLongitude GNSS - Hybrid/Inertial 255/InertialGround Speed GNSS - Hybrid 175Track Angle True GNSS – Hybrid 137True Heading – Hybrid 132Pitch Angle 324Roll Angle 325GNSS Height (HAE) or Hybrid Altitude MSL 370 or 261GNSS UTC (Binary) 150GNSS Date 260
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-17Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval C. Cockpit Interfaces (SDU Type 82155D only)• Cockpit Audio Management Unit (AMU)• Centralised Fault Display System (CFDS)• Communications Management Unit (CMU)• Multi-Purpose Control and Display Unit (MCDU).D. Maintenance System InterfacesThe SDU supports the following maintenance system 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 ThalesTFS product support representative at the following address: 86 Bushey RoadRaynes Park, LondonSW20 0JW, UKTel. +44 (0)20 8946 8011 (Switchboard)Tel. +44 (0)20 8946 5169 (Hot desk).2.6. SDU CONFIGURABLE PINOUT AND PIN DESCRIPTIONIn the case of using the mandatory configuration straps the SDU is configurable via theSDU ARINC 600 configuration straps as defined in ARINC 781.The straps input values will be read only at unit power-up to determine the systemconfiguration. The SDU configuration will be selectable by multiplexing theConfiguration Straps inputs with the service availability discrete outputs as per ARINC781 Attachment 1-4.GNSS Sensor Status 273GNSS HDOP 101PARAMETERS ARINC 429 LABELS
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-18Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval A. Mandatory Configuration PinsThe link between pins Top plug (TP)3D and TP3E must be removed when an externalFMHPA is connected. They are used as hardware implemented safety override to forcethe internal HPA function into low power mode.Pin TP3G must be used on all aircraft installations since one of its functions is to indicatewhether 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 itindicates the SDU number (1 or 2).Pin TP3F must be used on all aircraft installations since it indicates that the number ofall configuration pins (excluding TP3D) including the parity pin itself connected toservice availability discrete (or TP3D) is odd.2.7. SDU INTERCONNECT DATAA. ARINC 600 Standard Interwiring ConnectorThe SDU ARINC 600 connector provides:• Input/Output connections• EMC filtering to input and output interfaces• ESD (Electrostatic Discharge) (Refer DO-160 E section 25 Cat A).The SDU is provided with a low insertion force, size 2-shell receptacle in accordancewith ARINC 600 Attachment 19. This connector accommodates coaxial and signalinterconnections in the TP insert, Quadrax and signal interconnections in the middleplug (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).
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-19Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval • Index pin code 081 in accordance with ARINC Specification 600, Attachment 18 should be used on both the SDU and the aircraft rack connectors(1) ARINC 600 Pin AssignmentThe layout of the rear panel ARINC 600 connector and the Pin assignment are shown inthe figures 2.8, 2.9, 2.10 and 2.11. For further Information regarding the ARINC 600connector refer ARINC 781 (Refer to Figure 2.8).
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-20Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.8 ARINC 600 Connector LayoutABCDEFGHJ157157ABCDEFGHJABCDEFGHJ14913235678101112141513675429811 1012Index code 81 (5,2,2)Top PlugMiddle PlugBottom PlugNOTE: The index code pins dark colour represents the postTav_e_0000734_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-21Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.9 ARINC 600 Top PlugATE ATEATE ATEEmpty Config Config ConfigSPAREATEPin 1AATEPin 2BPin 3 Pin 4ATEPin 5ATEPin 6ATEPin 7ATEPin 8ATEPin 9ATEPin 10ATEPin 11ATEPin 12ATEPin 13ATEPin 14 Pin 15 Pin 16ATEPin 17ATEPin 18ATEPin 19ATEPin 20Ethernet 1TXAEthernet 1RXAEmptyCavityConfigPin 1ConfigPin 2ConfigPin 3ConfigPin 4SPAREISDN 1TXAISDN 1RXBEthernet 1RXBEthernet 1TXBCavity Pin 5ConfigPin 6 Pin 7 Pin 8ISDN 1RXAISDN 1TXBEmptyCavityEmptyCavityEmptyCavityConfigPin 9ConfigPin 10ConfigPin 11ConfigPin 12SPARE SPARE SPARE12345A B C D G H J K67Empty Config Config ConfigSPAREEthernet 2TXMCDU 3AEthernet 2RXMCDU 3ACavity Pin 13ConfigPin 14 Pin 15(Spare)Pin 16(Spare)ISDN 2TXAISDN 2RXBEthernet 2RXBEthernet 2TXBEmptyCavityConfigPin 17(Spare)ConfigPin 18(Spare)ConfigPin 19(Spare)ConfigPin 20(Spare)SPAREISDN 2RXAISDN 2TXBRF TXTo HPA or DLNAE FTav_e_0000735_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-22Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.10 ARINC 600 Bottom Plug28VHOT115VCOLDCHASSISGROUND28VGNDSPAREDLNA115vHOT13675429811 1012ETHERNET 7 ETHERNET 6ETHERNET 8ETHERNET 9ETHERNET 10Tav_e_0000736_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-23Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.11 ARINC 600 Connect Arrangement For Middle Plug InsertData InputServiceServiceAvailabilityDiscretes4ServiceAvailabilityDiscretes6AvailabilityDiscretes8ServiceAvailabilityDiscretes10CallSpareCockpit Spare CockpitCP Voice SpareSpare Spare SpareWOW WOWData TX MutePort BSU Port BSU BITE Input STBD STBDData fromMCDU 1AData fromMCDU 1BPlace/EndDiscreteInput 1SCM Pwr+12VMulti-ControlOutputAMulti-ControlOutputBCallPlace/EndDiscreteInput 2 Data fromMCDU 2AData fromMCDU 2BData fromprimaryIRSAData fromprimaryIRSBCP VoiceChimeSignalContactSCM PwrReturn 0VBITEInputfrom HPAABITEInputfrom HPABCP VoiceChimeSignalContactDatafromsecondaryIRS ADatafromsecondaryIRS BDatafromCMU 1ADatafromCMU 1BCockpitVoiceCall LightOutput 1SDUDatato SCMASpareDiscreteOutputDiscreteInputSPARE CockpitVoiceCall LightOutput 2DatafromCMU 2ADatafromCMU 2BCockpitAudioInput 1HighCockpitAudioInput 1LowVoiceMic OnInput 1SDUDatato SCMBSpareDiscreteOutputDiscreteInputSPAREVoiceMic OnInput 2CockpitAudioInput 2HighCockpitAudioInput 2LowCockpitAudioOutput 1HighCockpitAudioOutput 1LowGo AheadChimeReset 1SCMDatato SDUASpareDiscreteOutputDiscreteInputSpareARINC429 OutputASpareARINC429 OutputBCockpitAudioOutput 2HighCockpitAudioOutput 2LowDiscreteInputDiscreteInputDiscreteInputSCMDatato SDUBSpareARINC429 InputASpareARINC429 InputBSpareARINC429 InputASpareARINC429 InputBAES IDInputAAES IDInputBDiscreteInputInput 1SpareARINC429 OutputASpareARINC429 OutputBDatato CMU1 & 2ADatato CMU1 & 2BDatafromCFDSADatafromCFDSBBITE InputTop/PortBSU/AntABITE InputTop/PortBSU/AntBLoaderLinkAInputBITEInputSTBD BSUABITEInputSTBD BSUBDatatoCFDSADatatoCFDSBFromAirborneData LoaderAFromAirborneData LoaderBCrosstalkfromother SDUACrosstalkfromother SDUBDualSystemSelectDiscrete I/ODualSystemDisableDiscrete Inp.Crosstalkto otherSDUACrosstalkto otherSDUBToAirborneData LoaderAToAirborneData LoaderBDatafromMCDU 3ADatafromMCDU 3BHPAMute InputAHPAMute InputBLNA On /Off Control from LNA BSU HPAMute InputABSU HPAMute InputBData toMCDU1, 2, 3AData toMCDU1, 2, 3BPOTS 1APOTS 1BCabinCEPT-E1Data OutputACabinCEPT-E1Data OutputBServiceAvailabilityDiscretes1ServiceAvailabilityDiscretes2CabinCEPT-E1Data InputACabinCEPT-E1BPOTS 2APOTS 2BServiceAvailabilityDiscretes3ServiceAvailabilityDiscretes5ServiceAvailabilityDiscretes7ServiceAvailabilityDiscretes91234567891011A B C D E F G H J K12151314Ethernet 3TX A Ethernet 3RX AEthernet 3TX BEthernet 3RX BEthernet 4RX A Ethernet 4TX BEthernet 4RX BEthernet 4TX AEthernet 510 Base T(spare)from SDUto User+Ethernet 510 Base T(spare)from SDUto User-Ethernet 510 Base T(spare)from User to SDU +Ethernet 510 Base T(spare)from User to SDU -Resv ExtResetDiscreteInputRSVDMfr-Specific0-28VDiscreteOutputTav_e_0000725_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-24Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval B. Electrical Interconnection DiagramsThe SDU interconnection diagrams (refer to 2.12 to 2.16) illustrate all the necessaryconnection between the SDU and all the other interfaced equipment.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-25Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.12 TFS System Interconnection Block Diagram - SDU Type 82155A (Single Aisle Configuration)SDU(Notes 1,7,10)AntennaDLNATP3DTP3EService Availability Discrete 2MP11FConfig Pin 1Config Pin 2Primary Nav Data (A)Primary Nav Data (B)Navigation DataMP02AMP02BAircraftPowerSupplyBP01BP05BP03115 Vac Cold115 Vac HotChassis Ground115V AC - 7.5 AMPType A CircuitBreaker 1918EF115 Vac Cold115 Vac HotJ10D/LNA BITE Return ClientEthernet PortConnectorEthernet 3 RX (A) Q1Ethernet 3 TX (B) Q1Ethernet 3 TX (A) Q1Ethernet 3 RX (B) Q11T-11T-31T-21T-4SCMData to SCM (B)Data to SCM (A)Data from SCM (B)Data from SCM (A)SCM Power ReturnSCM Power Source MP01DMP02DMP03DMP04DMP05DMP06D 21348153568MP08CMP08DBITE Input Top/Port BSU/Ant (B)BITE Input Top/Port BSU/Ant (A)Multi-Control Output (B)Multi-Control Output (A) MP01EMP01F74(Note 5)(Note 4)(Note 3)22A(Note 6)7See Figure 2 -13 for list of ExplanatoryNotes7Front Panel RJ-45MaintenanceTerminalConnectorTX+TX-RX-RX+RX+TX-RX-TX+ 2163(Note 8)External HPAnot fittedMP8F TX Mute InputSystem FailedIndicationTX MuteARINC 615AData LoaderConnectorTP01ATP01CTP01BTP01DRear 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 1for SignalDetailsMP1G SPAREExternalResetSee Note 13for SignalDetailsSecondary Nav Data (A)Secondary Nav Data (B)Navigation DataMP01JMP01KRX PortTX PortAntenna Port (Note 2)D/LNA BITE H9BD/LNA Control 11TP71SDU RF Output to D/LNASDU RF Input from D/LNA BP07(Note 2)Tav_e_0000704_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-26Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-27Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.13 SDU Type 82155A Interconnection Diagram NotesARINC 600 - Shell Size #2 ConnectorView 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 (malecentre contact) (Radiall P/No: 620-021), which should be ordered separately. See Radiall specificationfor 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 beused to fill cavities. Size 5 Coax insert BP-6 is not required on the SDU mount connector and will not bepopulated, 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 600SDU Connectordefined in ARINC 781 - see Note 1ABCDEF GHJ157157ABCDEF GHJABCDEFGHJ14913235678101112141513675429811 1012Index code 81 (5,2,2)Size 5 Co-ax Plug. Radial P/N:620 121 (female center connector)See Note 8Quadrax Insert 2TQuadrax Insert 1TSize 1 Co-ax Plug. Radial:P/N:620 001 (male centerconnector)PIN No SIGNAL DESCRIPTION1 +28 Vdc Connection Not Required2 28 Vdc RTN Connection Not Required3 Antenna BITE A ARINC 429 from antenna4 Antenna BITE SCRN Screen for ARINC 4295 Antenna BITE B ARINC 429 from antenna6 Antenna Control A ARINC 429 to antenna7 Antenna Control SCRN Screen for ARINC429 8 Antenna Control B ARINC 429 to antenna9 D/LNA BITE BITE from D/LNA 10 D/LNA SCRN Screen/RTN for D/LNA11 D/LNA CTL D/LNA on/off control from antenna12 Serial SCRN 1Connection Not Required13 RS422 RXD A 1Connection Not Required14 RS422 RXD B 1Connection Not Required15 RS422 TXD A 1Connection Not Required16 RS422 TXD B 1Connection Not Required17 ATE Pin Connection Not Required18 115 Vac Hot Aircraft ac power19 115 Vac Return Aircr aft ac power20 -- Connection Not Required21 -- Connection Not Required22 Chassis Ground Chassis Ground The IGA/HGA Connector is a receptacle -13-35 insert of the MIL-C-38999 Series IIIfamily: D38999/24FC35PN which mates withD38999/26FC35S on the cable 12321201918171615765489101112131422IGA/HGA Power and Control ConnectorNote 4Pin Signal Description1 Data to SDU A (RS422) Data to SDU A2 Data to SDU B (RS422) Data to SDU B3 Data from SDU A (RS422 Data from SDU A4 Data from SDU B (RS422) Data from SDU B5 Reservedÿ RS232 GND1Connection Not required6 Spare ConnectionNot required7 Chassis Ground Chassis Ground8 Power Input +8 to +15V SCM Power Input9 Reserved- Enable RS2321Connection Not required10 Reservedÿ 0V strap output1Connection Not required11 Spare Connection Not required12 Reservedÿ RS232 Tx1Connection Not required13 Reservedÿ RS232 Rx1Connection Not required14 Spare Connection Not required15 Power Return 0V SCM Power ReturnSCM ConnectorNote3The SCM connector is a DB15 male connector, mating with a DB-15 female connectoron the cable, in accordance with MIL-DTL-24308 (15 pins - gauge 20).Note 5Pin Signal DescriptionPin A Chassis Ground Chassis GroundPin B LNA Control LNA ControlPin C Future Spare Connection Not requiredPin D Future Spare Connection Not requiredPin E 115 Vac Cold Aircraft AC PowerPin F 115 Vac Hot Aircraft AC PowerP in G +28V DC Hot Connection Not requiredPin H LNA BITE LNA BitePin J LNA BITE Return LNA BITE ReturnPin K +28V DC Return Connection Not requiredThe D/LNA Connector is MS3470L1210P whichmates with MS3476L1210S on the cableF E DH A BK J CGD/LNA Power and Control ConnectorThe 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) typeconnector.RF Cable Losses 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 Note 2Tav_e_0000737_00Note 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.Notes
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-28Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-29Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.14 TFS System Interconnection Block Diagram - SDU Type 82155D (with External FMHPA) - HGASDUNote 1,9,12AntennaDLNAAntenna PortDLNA BITEBHDLNA Control911TP71SDU RF Output to DLNASDU RF Input from DLNA BP07AircraftPowerSupplyBP01BP05BP03115 Vac Cold115 Vac HotChassis Ground115V AC - 7.5 AMPType A CircuitBreaker 1918EF115 Vac Cold115 Vac Hot J10DLNA BITE ReturnSCMData to SCM (B)Data to SCM (A)Data from SCM (B)Data from SCM (A)SCM Power ReturnSCM Power Source MP01DMP02DMP03DMP04DMP05DMP06D 21348153568MP08CMP08DBITE Input Top/Port BSU/Ant (B)BITE Input Top/Port BSU/Ant (A)Multi-Control Output (B)Multi-Control Output (A) MP01EMP01F74(Note 4)(Note 4)(Note 3, 4)(Note 7)Note6Note5M3 Chassis Stud22ATX PortData from Sec. IRS (A)Data from Sec. IRS (B)Navigation Data(IRS)See Assumption 1MP02JMP02KData from Prim. IRS (A)Data from Prim. IRS (B)Navigation Data(IRS)See Assumption 1MP02AMP02BData from AES (A)Data from AES (B)AES ID BUSSee Assumption 1MP07AMP07BTo Data Loader (B)To Data Loader (A)From Data Loader (B)From Data Loader (A)Data Loader Link A MP08EMP09JMP09KMP09AMP09BARINC 615DataLoaderFMHPATX PortHPA RF Output to DLNA (Note) 4J2J3MP02EMP02FJ1-YJ1-XJ1-JJ1-AJ1-BJ1-PJ1-R(Note 10)J1-TJ1-SBITE Input from HPA (A)BITE Input from HPA (B)7(Note 17)TP03DTP03EConfig Pin 1Config Pin 2SeeAssumption 2(Note 13)(Note 13)(Note 13)(Note 13)(Note 13)(Note 14)(Note 14)(Note 15)(Note 18)Tav_e_0000703_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-30Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-31Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.15 SDU Type 82155D Interconnection Diagram NotesARINC 600 - Shell Size #2 ConnectorView 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 (malecentre contact) (Radiall P/No: 620-021), which should be ordered separately. See Radiall specificationfor 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 beused to fill cavities. Size 5 Coax insert BP-6 is not required on the SDU mount connector and will not bepopulated, 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 600SDU Connectordefined in ARINC 781 - see Note 1ABCDEFGHJ157157ABCDEFGHJABCDEFGHJ14913235678101112141513675429811 1012Index code 81 (5,2,2)Size 5 Co-ax Plug. Radial P/N:620 121 (female center connector)See Note 8Quadrax Insert 2TQuadrax Insert 1TSize 1 Co-ax Plug. Radial:P/N:620 001 (male centerconnector)PIN No SIGNAL DESCRIPTION1 +28 Vdc Connection Not Required2 28 Vdc RTN Connection Not Required3 Antenna BITE A ARINC 429 from antenna4 Antenna BITE SCRN Screen for ARINC 4295 Antenna BITE B ARINC 429 from antenna6 Antenna Control A ARINC 429 to antenna7 Antenna Control SCRN Screen for ARINC429 8 Antenna Control B ARINC 429 to antenna9 D/LNA BITE BITE from D/LNA 10 D/LNA SCRN Screen/RTN for D/LNA11 D/LNA CTL D/LNA on/off control from antenna12 Serial SCRN 1Connection Not Required13 RS422 RXD A 1Connection Not Required14 RS422 RXD B 1Connection Not Required15 RS422 TXD A 1Connection Not Required16 RS422 TXD B 1Connection Not Required17 ATE Pin Connection Not Required18 115 Vac Hot Aircraft ac power19 115 Vac Return Aircr aft ac power20 -- Connection Not Required21 -- Connection Not Required22 Chassis Ground Chassis Ground The IGA/HGA Connector is a receptacle -13-35 insert of the MIL-C-38999 Series IIIfamily: D38999/24FC35PN which mates withD38999/26FC35S on the cable 12321201918171615765489101112131422IGA/HGA Power and Control ConnectorNote 6Pin Signal Description1 Data to SDU A (RS422) Data to SDU A2 Data to SDU B (RS422) Data to SDU B3 Data from SDU A (RS422 Data from SDU A4 Data from SDU B (RS422) Data from SDU B5 Reservedÿ RS232 GND1Connection Not required6 Spare ConnectionNot required7 Chassis Ground Chassis Ground8 Power Input +8 to +15V SCM Power Input9 Reserved- Enable RS2321Connection Not required10 Reservedÿ 0V strap output1Connection Not required11 Spare Connection Not required12 Reservedÿ RS232 Tx1Connection Not required13 Reservedÿ RS232 Rx1Connection Not required14 Spare Connection Not required15 Power Return 0V SCM Power ReturnSCM ConnectorNote5The SCM connector is a DB15 male connector, mating with a DB-15 female connectoron the cable, in accordance with MIL-DTL-24308 (15 pins - gauge 20).Note 7Pin Signal DescriptionPin A Chassis Ground Chassis GroundPin B LNA Control LNA ControlPin C Future Spare Connection Not requiredPin D Future Spare Connection Not requiredPin E 115 Vac Cold Aircraft AC PowerPin F 115 Vac Hot Aircraft AC PowerP in G +28V DC Hot Connection Not requiredPin H LNA BITE LNA BitePin J LNA BITE Return LNA BITE ReturnPin K +28V DC Return Connection Not requiredThe D/LNA Connector is MS3470L1210P whichmates with MS3476L1210S on the cableF E DH A BK J CGD/LNA Power and Control ConnectorThe 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) typeconnector.RF Cable Losses 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 Note 4Note 1: System interconnections are per ARINC 781-1 Note 3:An RF attenuator may be needed if loss in DLNA to SDU cable does not fall within range specified in Note 4. Note 8:Ethernet and ISDN connections should use “star Quad” cable as defined in ARINC 664 part 2. Cross-over to be provided in cable.Note 9:SDU Pins not required are not listed and should be left “Not-connected”.Note 10:HPA power and control connector.Note 11:Radial P/N:620-600-700 does not include all necessary contacts; 1x Size 5 crimp Socket Coaxial Contact must also be ordered, Radial P/N:620-021.Note 12:Pigtails for wiring shields/screens are to be made as short as possible to reduce susceptibility to interference. Shielded cabled and EMI backshells shouldbe used where possibleNote 13:A-429 (shielded twisted pair).Note 14:Discrete.Note 15:Power.Note 16:Male quadrax insert.Note 17:Connection of shields and grounding for SDU and Cabin/EFB Server are as shown. Connection of shields for SCM and ethernet ports is as per airframe manufacturers grounding and shielding policy.Note 18:RS-422 (shielded/twisted pair).Assumptions1: As per ARINC 781 attachment 1-4, note 15. If hybrid IRS data is not available , then connection to separate, autonomous inertial and GNSS navigationequipment may be required. It is assumed that hybrid IRS data is not available. If at least one IRS bus is not providing GNSS or hybrid labels as per ARINC 781-1attachment 1-4, note 15, connection to AES ID is required for GPS derived latitue and longitude.2:Mandatory configuration pins are not connected since an external HPA is fitted. Tav_e_0000708_00Notes
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-32Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-33Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.16 TFS System Interconnection Block Diagram - SDU Type 82155D Full Cockpit InterfacesSDUNote 1,9,12Cockpit Audio Input 1 HiCockpit Audio Input 1 LoCockpit Audio Output 1 HiCockpit Audio Output 1 LoCockpit Audio Input 2 HiCockpit Audio Input 2 LoCockpit Audio Output 2 HiCockpit Audio Output 2 LoMP04AMP04BMP05AMP05BMP04JMP04KMP05JMP05KCockpit Voice Call Light Output 1Cockpit Voice Call Light Output 2Cockpit Voice Mic On Input 1Cockpit Voice Mic On Input 2Cockpit Voice Go Ahead Chime Reset 1Cockpit Voice Chime Signal Contact 1Cockpit Voice Chime Signal Contact 2Call Place/End Discrete Input 1Call Place/End Discrete Input 2MP03CMP03HMP04CMP04HMP05CMP02CMP02HMP01HMP01CCockpit AudioManagementUnitData from CMU 2 (A)Data from CMU 2 (B)CMU 1&2(Data-2 / Data-3)MP03JMP03KData to CMU 1&2 (A)Data to CMU 1&2 (B)MP07JMP07KMCDU 1,2,3Data from MCDU 1 (A)Data from MCDU 1 (B)Data from MCDU 2 (A)Data from MCDU 2 (B)Data from MCDU 3 (A)Data from MCDU 3 (B)MP10AMP10BMP01JMP01KMP01AMP01BData to MCDU 1,2,3 (A)Data to MCDU 1,2,3 (B)MP10JMP10KData from CMU 1 (A)Data from CMU 1 (B)MP03AMP03BData from CFDS (A)Data from CFDS (B)CFDSMP08AMP08BData to CFDS (A)Data to CFDS (B)MP08JMP08KTav_e_0000710_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-34Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-35Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval C. Interconnection Cables(1) RF Coaxial CablesThe SDU is connected to the DLNA or FMHPA and Antenna (refer to Figures 2.12 to2.15), by means of a RF low loss coaxial cable. The distance between the devices, andthe cable selected for the installation must be such that the cable losses remains withinthe limits indicated within Figure 2-15, Note 4. If the cable losses cannot remain withinthe limits then an FMHPA must be installed between the SDU and the DLNA (Refer toFigure 2.13). All coaxial cable should be 50 Ohms nominally.NOTE: Interconnect cables should be routed away from sources of potentialelectromagnetic interference. Use shielded wires and cables wherenecessary.a. SDU to DLNA Tx PortRF cable characteristics for the SDU or FMHPA to DLNA Tx port are as follows:.Table 2.4 b. DLNA to SDU Rx PortRF cable characteristics for the DLNA to SDU Rx portTable 2.5 c. DLNA to Antenna PortRF cable characteristics for the DLNA to Antenna port Table 2.6 Maximum Path Loss Nominal Max Power Frequency Range1.4 dB (see Note) 60 W 1626.5 – 1660.5 MHzLoss Range Nominal Max Power Frequency Range6 – 25 dB (see Note) 0.5 W 1525 – 1559 MHzMax Path Loss Nominal Max Power Frequency Range 5th Order Inter-modulaion 7th order Inter-modulation0.3 dB (see Note) 46 W 1525 – 1660.5 MHz (see ARINC 781) (see ARINC 781)
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-36Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval d. SDU to FMHPARF cable characteristics for the SDU to FMHPATable 2.7 NOTE: Applied to the complete RF cable path and not to each component withinthe RF path.(2) Power CablesThe SDU mains power cable must be able to handle 115 Vac/7.5A (see note). NOTE: SDU 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.(3) ARINC 429 ConnectionsARINC 429 connection cable must be a size 22 single twisted and shielded pair of wirescable. (4) EthernetThe recommended Aerospace Grade 100Base Ethernet cable is P/N NF 24Q100. Theconductor AWG size (19 strands) is size 24.Flammability requirements for this cable meet or exceed FAR25.869 requirements.2.8. SCM COMPONENT DESCRIPTIONA. HardwareThe only SCM Part Number available is 82158D Series and all other different SDUconfigurations. The SCM hardware meets RTCA/DO-254 level D requirements.The SCM contains four USIM (Universal Subscriber Identity Module) cards. The SCMalso contains an External Configuration Memory (ECM) storing the OwnerRequirement Table.(1) External DescriptionThe SCM is composed by the following external elements (Refer to Figure 2.17):• The body of the SCM with one main identification label (1).Maximum Path Loss Nominal Max Power Frequency Range8-18 dB (see Note) 200 mW 1626.5 – 1660.5 MHz
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-37Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval • The 15-way D-type (male) socket (2)• The mounting plate with four attaching holes (3)(2) Internal DescriptionThe SCM is composed of the following internal parts (Refer to Figure 2.18):• One gasket between the D-type connector and the Body of the SCM (2)• One PEC card with a D-type connector attached (5)• Four USIM cards holders (4)• A plate attached to the body by four screws and washers (3)• A body attached to the single PEC card by four screws and washers (1)Figure 2.17 Example of SCM External View123Tav_e_0000730_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-38Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval B. ORT ParametersThe ORT is represented by a database containing a set of configuration data for theexclusive use of the SDU. The ORT is partitioned for two types of parameters inaccordance with ARINC 781:• User parameters, for operator use• Secure parameters, for aircraft specific configurationsThe ORT parameters are stored within the SCM and/or SDU, and are used to customisethe operation of the TFS system, allowing various preferences to be set to enable theFigure 2.18 SCM exploded view12345Tav_e_0000728_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-39Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval efficient use of the equipment within different platform configurations. The SDU andSCM are delivered with a default ORT. C. ORT SynchronisationAt each power up the SDU reads the ORT from the SCM, and compares it with its locallystored copy. In normal condition the SDU and SCM ORTs should be the same, but ifdifferent the SDU overwrites the local copy with the ORT read from the SCM. The SDUuses that ORT until the SDU is powered down. A small number of System Configuration Pins are mandatory. The others may beoptionally used by installers to define additional configuration details. If the optionalSystem Configuration Pins are not used then the configuration information may befound in the Owner Requirements Table (ORT). TP3G is used to define whether theoptional System Configuration Pins should be read by the SDU.The SDU stores the local copy of the SCM Secure and User ORTs over a power down incase one of the ORTs from the SCM is not valid when the SDU next powers up.NOTE:1. For more information concerning the operation of the SDU when itdetermines that an ORT is not valid refer to the ARINC 781 specificationsection 3.4.2 ‘Configuration & Identification Data’.NOTE:2. For more information concerning changes or updates regarding ORTcontact the Thales TFS product support representative. D. Basic OperationWhen operating, the SCM interfaces with the SDU CCM via the SDU CPM. The SCMoperation will not commence until an input voltage from the SDU is detected.Alternatively, when removed form the aircraft the SCM will also acknowledge an inputvoltage from a personal computer (PC), and will operate as if it were connected to anSDU.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.E. Environment ConditionRefer (Table 2.1)
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-40Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval F. Identification LabelThe main manufacturer label gives the following information (Refer to Figure 2.19):• 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 (Blank)• FCC id: Federal Communications Commission identification (Blank).Figure 2.19 Example of SCM Identification LabelPNRMinorREV.SW PNRSupply 12V D.C. CSD 10 cmWt. 0.25 kg MAXFAA TC xFCC id xxxxxx-xxxxSDU CONFIGURATIONMODULE (SCM)MFRSERDMFINSPECTABCDEFLKJIHGPLAE1Amdt Tav_e_0000724_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-41Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval G. SCM Electrical CharacteristicsElectrical characteristics of the SCM are as follows:• 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.H. Weight and DimensionsWeight and dimensions of the SCM are as folows:• For overall dimensions Refer to Figure 2.20• Mass = 0.25kg (0.44Lbs). Figure 2.20 SCM Overall Dimensions83.813.11106.1 88.91011.522.5Tav_e_0000731_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-42Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval I. SCM ConnectorThe SCM connector is a DB15 (15 pins – gauge 20) male connector (Refer to Figure2.21), mating with a DB-15 female connector on the cable. For complete description ofPin Assignment refer to Figure 2-13 Note 3. J. Equipment Electrical Interconnection DiagramThe SDU interconnection diagram (Refer to Figure 2.22). The diagram illustrates all thenecessary connection between the SCM and the SDU. For description of detailed pin-to-pin connection refer to Figure 2.12 (SDU Type 82155A) and Figure 2.14 (SDU Type82155D).Figure 2.21 Front View of 15 Pin D-Type Connector115Tav_e_0000729_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-43Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.22 SDU/SCM Interconnection DiagramSDU SCM+ 12V0VRS422_Rx_ARS422_Rx_BRS422_Tx_ARS422_Tx_B15 way D-Type connectorTav_e_0000713_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series2-44Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series3-1Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 330000INSTALLATION GUIDELINES3.1. INTRODUCTIONThe SDU and SCM should be installed in the aircraft in a manner consistent withacceptable workmanship and engineering practices, and in accordance with theinstructions set forth in this manual. To ensure that the system has been properly and safely installed in the aircraft theinstaller should make a through visual inspection and conduct an overall operationalcheck of the system on the ground prior to commissioning to the Customer and or aflight. NOTE: Before installing any components or cabling, read all notes containedwithin drawings.3.2. INTERCHANGEABILITYThe TFS comprises two major sub-systems and a number of individual units. Systeminterchangeability for each of the major sub-systems and unit interchangeability for theindividual units. The first major sub-system comprises the SDU and the SCM. Thesecond is the antenna sub-system, comprising two LRUs, the antenna with its integratedbeam steering function, and the DLNA. Interchangeability is also desired for theFMHPA.There are two instances whereby individual units are defined to be functional doublets.This means that the interwiring and pin out definitions are interchangeable, but due tounique protocol implementations, the supply and acquisition of these units aremanufacturer specific. Functional Doublets are different from Matched Pairs in that eachunit of the Functional Doublet may fail and be changed independently, whereas inMatched Pairs both units must be changed regardless of which unit has failed.The Functional Doublets are as follows:• SDU and SCM• SDU and FMHPA.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series3-2Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 3.3. SDU/SCM LOCATION AND ACCESSIBILITY GUIDELINESCAUTION: BEFORE EQUIPMENT INSTALLATION ENSURE THAT THEAIRCRAFT POWER SUPPLY CIRCUIT BREAKER ISPOSITIONED IN THE OFF CONDITION.The SDU must be installed in a pressurized zone that is also partially temperaturecontrolled, and mounted on an appropriate ARINC 600 compliant mounting rack. TheSDU requires external forced air-cooling (refer Section 2 G).The SCM should be installed as close to the SDU as possible in order to keep the cableruns to a maximum 10 feet.To determine the best location, the installer must select equipment locations to alloweasy access to these components and their connectors. Equipment location will vary withaircraft type and design/installation specifications.The location of LRUs must comply with ARINC 781 limitations. The electronic bay isthe prefered location to install this unit. The SDU must be installed in a location that allows the following facilities to beaccessible:a. Front Panel LEDsb. Front Panel TFS system Test Push Buttonc. Front Panel Test Port, Software loading RJ45 connector d. Front Panel SIS connector.3.4. MOUNTING TRAYThe mounting tray used for the installation of the SDU must comply with the designspecifications for the 6 MCU (Modular Concept Unit) form factor. Refer to the ARINC600 Specification for detailed information regarding the design of compatible equipmentand airframe installations.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series3-3Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 3.5. COOLINGThe 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 fromthe platform services at a maximum flow rate of 50 kg/hr and a temperature of up to40oC. The cooling air must enter the equipment chassis at the bottom via a plenumchamber and exhaust at the top.3.6. POWER REQUIREMENTSIt is the responsibility of the installer to select the appropriate gauge of wire for powerconnections, and to ensure that the required safety and voltage drop requirements arecomplied with.For SDU power supply specifications refer to:a. 2.3.K: SDU Electrical Characteristics.b. Figure 2.7: Aircraft Power Distribution.c. Figures 2.12 to 2.16: TFS System Interconnection Diagrams.For SCM power supply specifications refer to:a. 2.7.G: SCM Electrical Characteristics.b. Figure 2.12 to 2.16: TFS System Interconnection Diagrams.Figure 3.1 Example of an ARINC 600, 6 MCU Mounting Tray
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series3-4Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 3.7. SDU RF CONNECTIONSCAUTION: DO NOT EXCEED MINIMUM CABLE RADIUS OF CURVATUREFOR THE COAXIAL CABLE. USE DUMMY CABLES FOR AFIRST INSTALLATION TO DETERMINE CABLE RUNS. INSTALLFINAL CABLES AFTER THIS MODELLING OPERATION.CAUTION: ONLY PREFORMED RF CABLES SHALL BE CONNECTED TOTHE SATCOM SYSTEM EQUIPMENT. ATTEMPTING TO FORMCABLES OR APPLYING STRESS TO THE CABLES WHILETHEY ARE CONNECTED TO THE EQUIPMENT CONNECTORSMAY CAUSE DAMAGE TO THE EQUIPMENT.The SDU or FMHPA is connected to the DLNA through a RF coaxial cable. Installationdesigner 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 adiameter not compatible with the IGA and DLNA connectors, it is recommended toinstall a short portion of a smaller and more flexible cable at each end of this low losscable (pig tail type installation).If necessary, secure the cable by means of evenly spaced collars to prevent the cablefrom chafing on aircraft parts and surfaces. These collars must be of a design, whichavoids damaging the cable.NOTE: Interconnect cables should be routed away from sources of potentialelectromagnetic interference. Use shielded wires and cables wherenecessary.D. Insertion LossesThe SDU RF interface with the Antenna via a DLNA device. The diplexer and LNA arecombined into one unit for installation. The Diplexer function couples transmit signalsfrom the SDU to the respective antenna. The LNA amplifies the very low level L-bandreceive signal from its respective antenna and couples this amplified signal to the SDU.For detailed RF insertion losses refer to Section 2 C. To ensure these requirements aremet, some installations need the SDU to be installed in close proximity to the antennasubsystem 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 theRF cable type being used for a short cable length is less than 6 dB, an attenuator must befitted to ensure the required loss is achieved.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series3-5Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval E. Product InterModulation (PIM)Specific care should be taken to ensure that the RF cables and connectors do not produceintermodulation products at levels higher than those specified in ARINC 781.F. VSWRThe Voltage Standing Wave Ratio (VSWR) of all RF cables should be 1.2:1 or better.G. Torque SettingsThe cables are to be tightened to the torque settings recommended by the cablemanufacturer.H. CleaningRefer to Section 6.5 for cleaning.3.8. BONDING REQUIREMENTSThe bonding of all units to the airframe must not exceed 20 milliohms. However someaircraft manufacturers or design/installation organisation may require a lower value thanthe recommended 20 milliohms.NOTE: To assure proper grounding of the TFS system, the surface of themountings and units must be clean bare metal.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series3-6Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series4-1Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 440000INSPECTION AND SYSTEM CHECKOUT4.1. INSPECTION/CHECK PROCEDUREThe visual check procedures that follow should be performed during or after the SDU/SCM installation, or as a periodic maintenance inspection check of the installation:A. Check Wiring and RF cablesa. Ensure that a continuity check of all the installation wiring harness has been carried out, and that all the sources are correctly rated on the correct pins.b. Check that none of the cables have been damaged, and cannot be damaged by components that are installed later.c. Check that the cable runs are spaced away from any moving or hot part that could damage cables when in use.d. Verify that the various RF cables are within their minimum radius of curvature tolerances.e. Check that any attenuators that may have been used for the installation have not been omitted or mismatched.B. Check SDUa. Examine the assembly for external condition (absences of fractures, dents, deformations, cracks, and/or any other abnormal damage).b. Visually examine all the external surfaces for possible damage. Check dust cover and external connector for dust, corrosion or damage.c. Check that the unit is properly installed and that hold down clamps are firmly tightened.d. Check screws and nuts general condition.e. 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.f. Check that the correct air cooling and air flow is provided to the SDU.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series4-2Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval C. Check SCMa. Examine the assembly for external condition (absences of fractures, dents, deformations, cracks, and/or any other abnormal damage).b. Visually examine all the external surfaces for possible damage. Check dust cover and external connector for dust, corrosion or damage.c. Check that the unit is properly installed, that all fixing screws are firmly tightened, and the cable to the SDU is secure.4.2. SYSTEM CHECKOUTAt this stage of the installation it is assumed that a continuity check of the wiring hasbeen made, a visual check of the installation harness and RF cabling has been performed,and that the inspection/check procedure has been carried out.A. Post-Installation TestWARNING: THE RF POWER RADIATED BY THE TFS SYSTEM ANTENNACAN CAUSE BODILY HARM. A PERSON IS IN DANGER IN AZONE WHERE THE POWER FLUX IS 1 MW/CM2, ORGREATER. DURING SATCOM OPERATION THE SAFETYDISTANCE FROM THE ANTENNA MUST BE NO LESS THAN3.5M OR 12 FEET. SINCE THERE ARE VARIOUS POSSIBLEANTENNA LOCATIONS, IT IS THE RESPONSIBILITY OF THEOPERATOR TO DETERMINE THE AREA OF HAZARD FORTHEIR TFS SYSTEM CONFIGURATION AND TO TRAINPERSONNEL IN GROUND SAFETY PROCEDURES.WARNING: DURING ANTENNA OPERATION (TRANSMISSION), MAKESURE PERSONNEL ARE NOT EXPOSED TO ANYREFLECTED, SCATTERED, OR DIRECT BEAMS. ENSUREPERSONNEL ARE OUTSIDE THE MINIMUM DISTANCESPECIFIED.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series4-3Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval CAUTION: WHEN TESTING THE COMPLETE TFS SYSTEM (ANTENNASYSTEM INCLUDED) REFER TO THE APPLICABLE ANTENNAIMM FOR FURTHER SAFETY REQUIREMENTS ANDSPECIFICATIONS. THE SDU MUST NOT BE POWEREDWITHOUT AN ANTENNA OR SUITABLE LOADCONNECTED ONTHE HIGH POWER TRANSMIT OUTPUT PORT.CAUTION: NEVER CONNECT OR DISCONNECT A SATCOM LRU WHENPOWER IS APPLIED.CAUTION: NEVER APPLY HIGH-LEVEL RF SIGNAL TO A POWERED-DOWN LRU.CAUTION: NEVER DISCONNECT RF CABLES WHEN SYSTEMOPERATING.CAUTION: NEVER POWER-UP ANY LRU UNTIL ALL CONNECTIONS INTHE SYSTEM ARE MADE.CAUTION: ENSURE THAT THE APPROPRIATE ORT DATABASE ISINSTALLED IN THE SCM AND/OR SDU BEFORE PERFORMINGSYSTEM OPERATIONS.This test requires that all the Satcom system LRUs (SDU, SCM, FMHPA, DLNA,Antenna and cables) be connected and operating properly, with a means of displayingany system faults detected by the LRU during the Built-In Test Equipment (BITE) test.The results of the test are indicated on the SDU front panel LED. Type 82155D SDU bite is also sent to the CFDS.If no system faults are indicated by the BITE test, then the subsystem installation shouldbe considered acceptable. If any subsystem LRU fails the test, it must be returned to thevendor (refer to your vendor customer support).Refer to the Section 5 Fault Isolation for information on the SDU fault detectioncapabilities.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series4-4Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series5-1Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 550000FAULT ISOLATION5.1. BITE FUNCTIONThe primary purpose of BITE is to assist aircraft maintenance personnel in the correctmaintenance of avionics equipment in a cost effective manner. The BITE does notcontribute to the required function of the TFS system, but makes it easier to test or debugit.The SDU controls the TFS system BITE. It collects BITE information from other LRU,and can request other LRU 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 otherOMS), and this information is made available to maintenance personnel by means ofdiscretes and/or LED on the SDU front panel. Failures can also be reported to adedicated local maintenance function through Simple Network Management Protocol(SNMP) and the Management Information Base (MIB).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 6-1.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series5-2Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 5.2. TEST FUNCTIONSA. OMS or CFDSFault information can be displayed from an OMS/CFDS when the aircraft is soequipped. Faults that occur at anytime are stored in fault memory and reported to theOMS or CFDS. B. BITEAn operator can verify the operational serviceability of the SDU and SCM by means ofa set of testing facilities installed within the SDU. The SDU performs two distinctivetypes of test:• A Power-On Self Test (POST) is automatically activated at SDU start up.• An Person-Activated Self Test (PAST) can be initiated by an operator by depressing the Test push button located on the front panel of the SDU, (see Figure 2-5 item 17). PAST can also be initiated from the CFDS.Figure 5.1 Example of BITE communication for TFS system
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series5-3Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval (1) POSTAt SDU start up (Power On), and with aircraft in the ‘on ground’ condition the FrontPanel LED (FPL) will display the following test sequence:NOTE: Type 82155D SDU durations are longer, approximately 90 seconds.Figure 5.2 POST LEDs SequenceApplypowerSTARTAll LEDs illuminate Amber forapproximately 90 secondsLEDs flash Green forapproximately 3-5 seconds (see note)LEDs remain in Off conditionfor the duration of approximately 75 seconds (see note)LEDs driven to indicate aGreen steady conditionTav_e_0000716_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series5-4Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval (2) PASTThe PAST function is initiated by depressing the front panel TEST Button (This functionis only possible with aircraft on ground). To acknowledge PAST initialisation all thefront panel LED start to flash green at the frequency of 2Hz. After approximately 75seconds the SDU will transit into Operational Mode with the LED displaying the TFSsystem 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 can only be initiated after the POST has completed.Figure 5.3 PAST LEDs SequencePush frontpanel TestButtonAll LEDs extinguish andremain in Off condition forapproximately 90 secondsStartLEDs flash Green for 3-20 SecondsLEDs driven to indicate the Appropriate statusTime variations aredue to ORTsynchronisationTav_e_0000715_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series5-5Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 5.3. FAULT ISOLATIONA. FailuresFailures are reported to an operator by means of a set of multicoloured LED located onthe SDU front panel. LED can enter the following steady states:• Normal equipment operation indicated by the relevant LED displayed in a steady Green condition • Equipment Hard Failures are indicated by all relevant LED displayed in a steady Red condition• Partial equipment failures are indicated by all relevant LED 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.NOTE: A fault with an interconnecting cable may prevent an LED fromilluminating.B. Front Panel IndicationsTable 5.1 provides LED status decoding information.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series5-6Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Table 5.1 Front Panel IndicationsOffSDU Not PoweredSCM Not Installed or SDU Not PoweredSDU Not PoweredSDU Not PoweredN/AN/ASDU Not PoweredSDU Not PoweredChannel #1 Not attempt-ing Log-On or Registation7Channel #2 Not attempt-ing Log-On or Registation7RedSDU Failed (Indicted)2USIM Read/Write Fail. No attempt at SSB regis-trationAntenna Failed (Indicted)2DLNA Failed (Indicted)2N/AN/ABus Failed3 (ARINC 429 /AFDX/RS-422)ORT Major Failure6 or Hardware Configuration Straps Parity Fail-ure(Indicted)2 N/AN/AAmberPartial Failure (Not Indicted)1 or ARINC 429/AFDX /RS-422 Bus SCM Memory Fail (Not Indicted)1 or RS-422 Bus Failure3Partial Failure (Not Indicted)1 or ARINC 429 Bus Failure3N/AN/AN/ANav Data not available. ARINC 429 Bus from IRS inactive or IRS Data invalid4ORT Minor Failure5 (Not Indicted)Channel #1 attempting Log-On or RegistrationChannel #2 Service avail-able, ie Logged-On or RegisteredSteady GreenSDU okSCM/USIM okAntenna okDLNA okN/AN/AAll Data Buses (ARINC 429 /AFDX/RS-422) okORT / Hardware Configu-ration StrapsChannel #1 Service avail-able, ie Logged-On or RegisteredChannel #2 Service avail-able, ie Logged-On or RegisteredFlashing GreenSDU in Self-TestSDU in Self-TestSDU in Self-TestSDU in Self-TestSDU in Self-TestSDU in Self-TestSDU in Self-TestSDU in Self-TestSDU in Self-TestSDU in Self-TestLEDSDUSCMAntennaDLNAExt. HPAExt. BSUExt. Data BusORT/ Config.Sat. Link #1Sat.Link #2
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series5-7Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval List of Explanatory Notes for Table 5.1:1. 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 LED illuminates Amber4. This is a special case. There will be frequent legitimate occurrences of IRS 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 state5. The ORT/Configuration LED illuminate Amber in the following circumstances:- 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.- 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.- 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:- 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- Type 2 ORT Synchronization- Type 3 ORT Synchronization Failure - Secure ORT in SDU that is integral part of SW - if SDU Secure ORT is invalid.- Hardware Straps Parity Failure. SDU be indicted.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series5-8Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 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. C. Fault LoggingAll information of degraded and abnormal equipment function will be logged internallyand made available to a dedicated local maintenance system (e.g. CFDS).D. Service Availability DiscretesThe status of various system functions can be reported by means of the ServiceAvailability Discretes available on the ARINC 600 connector.Table 5.2 SDU Serviceability DiscretesFunction Pin Allocation Steady State Open Circuit Steady Ground1SDU MP 15F SDU Powered SDU Not PoweredSystem Failed MP 11F System ok System Failed2SDU Failed MP 12E SDU ok SDU Failed3SCM Failed MP 12F SCM ok or not installed SCM Failed4Ext. HPA Failed MP 13E Ext. HPA ok or not installed Ext. HPA FailedDLNA Failed MP 13F DLNA ok DLNA FailedAntenna Failed MP 14E Antenna ok Antenna FailedExt. BSU Failed MP 14F BSU ok or not installed BSU FailedBUS Failed5MP 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 RegisteredSat Link #2 Not available TP 01K Satcom Channel #2 Logged On/Registered Satcom Channel #2 Not Logged On/Not Registered
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series5-9Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval List of Explanatory Notes for Table 5.2:1. 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.E. Service Availability Discrete LampsThe Service Availability Discretes have open circuit and ground states that are capableof driving incandescent lamps connected to an external supply.Typically, each discrete is fed via one or two (in parallel) incandescent lamps to anaircraft 28 Vdc supply. This 28 Vdc supply can be dimmed to approximately 14 Vdc fornight 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 becapable of holding a cold inrush current of up to 490mA during the first 10 millisecondof activation as per ARINC 781.F. CFDS/ARINC 604 BITEThe SDU reports BITE status and faults to the CFDS using ARINC 429, 350 serieswords.The SDU software can raise a fault, a fault may or may not indict a particular Resource,many detailed faults may indict a single resource.Resources also have a hierachy defined, so a tier 1 resource may ripple up to a tier 2resource, and so on. Faults typically indict a tier 1 resource. An example of tier 1
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series5-10Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval resource might be ethernet Port1 (there are 4 in total), there also may be a tier 2 resorcethat represents the state of all tier 1 ethernet ports.The status of the ARINC 429, 350 series of labels are driven by the resources. If aparticular resource is indicted, then it may have a consequential impact on one or moreBits in the 350 words.Refer to ARINC 781 Attachment 2B for a definition of all the 350 words and thedefinition of each Bit within the words.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series6-1Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 660000MAINTENANCE PRACTICES6.1. GENERALThis section provides instructions for the removing, reinstalling and adjusting of theSDU and SCM that has been previously installed by the aircraft manufacturer orcompletion center.CAUTION: TO AVOID INJURY TO PERSONNEL OR DAMAGE TOEQUIPMENT, ENSURE ADEQUATE PRECAUTIONS ARETAKEN WHILE PERFORMING ANY WORK IF THE ELECTRICALPOWER IS APPLIED TO THE LRU.CAUTION: TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFTPOWER OFF BEFORE REMOVING OR INSTALLING LRU.Field lubrication or other maintenance procedures are not required. The design of theSDU and SCM is such that they do not require field maintenance to maintainairworthiness. If functional problems occur, the SDU Built-in Test Equipment (BITE)capability identifies the faulty LRU. The SDU and SCM maintenance is limited toreplacement on verified failure.6.2. EQUIPMENT AND MATERIALSCAUTION: BEFORE YOU USE A MATERIAL, REFER TO THEMANUFACTURERS‚ MATERIAL SAFETY DATA SHEETS FORSAFETY INFORMATION. SOME MATERIALS CAN BEDANGEROUS.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series6-2Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 6.3. PROCEDURE FOR THE SDUCAUTION: THE SDU IS ELECTROSTATIC DISCHARGE SENSITIVEEQUIPMENT. OBSERVE STANDARD ESD PROCEDURESWHEN HANDLING THE EQUIPMENT.A. Removal and Installation Procedure(1) Remove the SDUa. Ensure that electrical supply to the SDU is switched off.b. Loosen 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.c. 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.d. Visually check the SDU ARINC 600 connector and then install an ESD protection cap on the SDU ARINC 600 back connector.Figure 6.1 SDU Removal from ARINC 600 Mounting TrayTav_e_0000722_00 SDU removal direction Hold Down Clamps
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series6-3Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval (2) Install the SDUa. Remove ESD protective cap from the SDU ARINC 600 back connector.b. Carefully place the SDU on its mounting tray and slide it towards the mounting tray back connector.c. When the SDU is fully engaged into the connector raise the mounting tray Hold Down Clamps over the hooks of the SDU and hand tight in the clockwise direction.d. 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.CAUTION: ENSURE THAT THE THUMBSCREW HOLD DOWN CLAMPSARE FASTENED, AND THAT THE LRU IS SECURELY HELD INPLACE.B. Adjustment ProcedureNot Applicable.C. Repair ProcedureNot Applicable.D. Return to Service ProceduresDo the Post-Installation Test Procedures referenced in the Inspection and SystemCheckout Section of this manual.Figure 6.2 SDU Installation on to ARINC 600 Mounting Tray SDU installation direction Hold Down Clamps Tav_e_0000721_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series6-4Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 6.4. PROCEDURE FOR THE SCMCAUTION: THE SCM IS ELECTROSTATIC DISCHARGE SENSITIVEEQUIPMENT. OBSERVE STANDARD ESD PROCEDURESWHEN HANDLING THE EQUIPMENT.A. Removal and Installation Procedure(1) Remove the SCMa. Ensure that electrical supply to the SCM is switched off (switch off the SDU).b. Loosen the two (2) screw locks that secure the 15-pin D Type connector to the SCM.c. Disconnect the D connector. Bag and stow the cable as required.d. Install an ESD protection cap on the SCM D Type connector.e. 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.f. Remove the SCM, and visually inspect it for any signs of damage(2) Install the SCMa. Remove the ESD protection cap on the D Type connector.Figure 6.3 SCM Removal Fixing Screws (4 off) Tav_e_0000719_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series6-5Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval b. Place the SCM to the dedicated mounting fixture and insert the four fixing screws to finger tightness only. After all four fixing screw have been inserted tight the screws with an appropriate toolCAUTION: ENSURE THAT THE FIXING SCREWS HAVE BEEN FASTENED,AND THAT THE LRU IS SECURELY HELD IN POSITION.c. 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 female screw locks.B. Adjustment ProcedureNot Applicable.C. Repair ProcedureNot Applicable.D. Return to Service ProceduresDo the Post-Installation Test Procedures referenced in the Inspection and SystemCheckout Section of this manual.6.5. CLEANING OF MECHANICAL PARTSCAUTION: MOISTURE AND DIRT CAN CAUSE DAMAGE TO EQUIPMENTEquipment chassis covers give the necessary protection to keep dust away fromelectronic circuits. If cleaning is required this has to be limited to the removal of particlesFigure 6.4 SCM Installation D Type Connector (3) Fixing Screw (1) Screw locks (2) Tav_e_0000720_00
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series6-6Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval of dust, oil, grease, condensation, etc and only limited for those equipment accessibleparts. Before any cleaning action is carried out ensure that the equipment is disconnectedfrom all electrical power sources, and all the necessary ESD precautions are observed.a. For dust removal use a cleaning wipe, a silk paintbrush or low-pressure compressed airb. For removal of finger marks, grease, etc, clean the parts with a cleaning wipe and isopropyl alcohol, exercising care to not damage information labels.6.6. PERIODIC CHECKSSee Inspection/ Check procedure in Section 4.1.6.7. CABLING AND CONNECTIONSPeriodically check cable connectors (recommended) and if required, remove connector,inspect and re-connect connector to required torque values as specified by the cablemanufacture.6.8. INSTRUCTIONS FOR CONTINUED AIRWORTHINESSMaintenance requirements and instructions for continued airworthiness of the TFS SDUand 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 operatorto include the maintenance information supplied by this manual (and listed below) in theoperator‚ Aircraft Maintenance Manual and the operator‚ Aircraft ScheduledMaintenance Program.a. Maintenance information for SDU and SCM, TFS LRU (system description, removal, installation, testing, etc.).b. The part numbers (see section 2) of the LRU being installed (SDU and SCM) should be placed into the aircraft operator‚ appropriate aircraft Illustrated Parts Catalogue (IPC).c. Wiring connection information contained in this manual (see sections 2 and 3) should be placed into the aircraft operator‚ appropriate Wiring Diagram Manual.d. 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.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series6-7Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval e. 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.f. 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‚ Minimum Equipment List (MEL)).g. SDU and SCM can be repaired by an Approved Maintenance Organization or an appropriately rated FAA Part 145 repair station.h. 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.i. Once repaired, install the LRU in the aircraft in accordance with the original Form 337 approved data or instructions in this manual. Do a Return to Service test of the system and approve it for return to service with a log book entry in accordance with the requirements specified in FAR Part 43.9.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series6-8Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series7-1Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 770000COMMISSIONING7.1. GENERALThe purpose of the following tests is to confirm functionality of the services supportedby the SDU and associated equipment, both to confirm the installation has beensuccessful and to demostrate that the functionality is present to the customer.All but one of these tests (the SMS and GSM Test, I.) can be performed on the ground.Regulatory issues require that the GSM Pico cell not be operated below 10 000 feet, sothis test should be carried out on the next available test flight.Not all tests are run for all installations - which tests should be run depends on thecapabilities fitted to the aircraft, as per the following table:Table 7.1 Commissioning Tests ApplicabilityA. Registrationa. Power on the AGS (when fitted).b. Power on the TFS System and wait until the LEDs reach the following state (Refer to Table 7.2):Capability A B C D E F G H IBaseline SDU+SCMYesNoNoNoNoNoNoNoNo+ Cockpit audio/avionicsYesYesYesNoNoNoNoNoNo+ Wifi AP or wired EthernetYes No No Yes Yes Yes No No NoCabin ISDN YesNoNoNoNoNoYesYesNo+ GSM Pico cellYesNoNoNoNoNoNoNoYes
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series7-2Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Table 7.2 SDU LEDsNOTE: Unless an FMHPA is installed, in which case should be GREEN.c. Connect a laptop to the Test port on the SDU.Either:d. If an MCDU is present:i Enter the Satcom main menu.ii Both Sat-1 (and Sat-2 if Dual Channel) should be “READY”.iii Press Page Down.iv Select “CHANNEL STATUS”v Sat Modem1 should be in “SWIFT BB” with status “LOGGED ON”Or:e. If the cabin control panel is fitted:vi If the “Service is available” LED is lit then the Satcom system is registered.LED SDU - 82155A SDU - 82155DSDU GREEN GREENSCM GREEN GREENAntenna GREEN GREENDLNA GREEN GREENFMHPA OFF(see Note) OFF(see Note)Ext. BSU OFF OFFExt. Data Bus GREEN GREENORT/Config. GREEN GREENSat. Link #1 GREEN GREENSat. Link #2 OFF OFF
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series7-3Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval B. Classic Packet Data VerificationIf Cockpit functionality is fitted:a. Using any MCDU:i Press the “Menu” key to display the menu page.ii Select “ACARS”.iii Via the “MAINTENANCE”, “COMM CONTROL” or equivalent ACARS page, verify that Satcom is “AVAILABLE”.iv Send and receive several “FREE TEXT” ACARS messages.v Verify correct receipt of all messages.C. Classic Cockpit Voice CallsIf Cockpit functionality is fitted:a. Using any MCDU:i Enter the Satcom main menu.ii Both Sat-1 (and Sat-2 if Dual Channel) should be “READY” .iii Using the correct procedure based on the ORT options selected, place and receive Cockpit Voice calls using each of the available channels from the Audio Control Panels.iv In each case, verify correct operation.D. SBB Cabin Wifi Data Connectivity (Background Context)If either a Wifi access point or a wired Ethernet to the cabin is fitted:a. Start up a laptop (with Wifi capability if Wifi is to be used).b. Connect to the access point or wired Ethernet.c. Open a browser window and follow the instructions to gain default background access (if any).d. Open a command window (Start, Run, “cmd”).i Type “ping www.google.com -n 10 -w 10000”.ii 10 replies should be received.iii Type “ping www.google.com -1 1400 -n 10 -w 10000”.iv 10 replies should be received.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series7-4Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval e. Go to Google homepage and search for a random string to check HTML connectivity.f. Start an FTP client:i Connect to the Inmarsat FTP server.ii Change directory to a test directoryt.iii “Put” a file onto a server. The transfer should complete successfully.iv “Get” a file from the server. The transfer should complete successfully.v Disconnect the FTP client.g. Disconnect from the access point or wired Ethernet.E. SBB Cabin Wifi Data Connectivity (Streaming Context)If either a Wifi access point or wired Ethernet to the cabin is fitted:a. Start up a laptop (with Wifi capability if Wifi is to be used).b. Connect to the access point or wired Ethernet.c. Open a browser window and follow the instructions to gain access to a guaranteed streaming connection -32k.d. Set the Traffic Flow Template by associating the streaming connection with the FTP client.e. Open the billing/connection monitoring section of the local site, or open the properties for each network connection.f. Open a command window (Start, Run, “cmd”).i Type “ping www.google.com -n 10 -w 10000”.ii 10 replies should be received.iii Check that the traffic generated by this command went via the Background context and not the Streaming connection.g. Go to Google homepage and search for a random string to check HTML connectivity.h. Start an FTP client:i Connect to the Inmarsat FTP server.ii Change directory to a test directoryt.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series7-5Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval iii “Put” a file onto a server. The transfer should complete successfully.iv The traffic should have gone via the streaming context and the data rate should have been comparable to the guaranteed rate.v “Get” a file from the server. The transfer should complete successfully.vi The traffic should have gone via the streaming context and the data rate should have been comparable to the guaranteed rate.vii Disconnect the FTP client.i. Disconnect the streaming connection.j. Disconnect from the access point or wired Ethernet.F. Cabin VoIP serviceIf either a Wifi access point or wired Ethernet to the cabin is fitted:a. Ensure that the SDU is powered on and connected.b. Connect a laptop with headset or VoIP phone to the Cabin Wireless Access Point.c. Open a browser window and follow the instructions to gain default background access (if any):i Make a phone call to a PSTN number and have a short conversation. audio quality should be good.ii Arrange a call back and hang up. When the phone rings, answer and have a short conversation. Audio quality should be good.G. Cabin ISDN Data serviceIf ISDN to the cabin is fitted:a. Connect an ISDN modem to the laptop.b. Connect an ISDN modem to the ISDN port.c. Dial a suitable ISDN number for a data connection to the internet:i The modem should be able to receive the “on hook” status and dial a number.ii Arrange a call back and hang up. When the phone rings, answer and have a short conversation. Audio quality should be good.iii The connection should be set up over Satcom to the number dialed.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series7-6Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval iv Type “ping www.google.com -n 10 -w 10000”.v 10 replies should be received.vi Type “ping www.google.com -1 1400 -n 10 -w 10000”.vii 10 replies should be received.d. Go to the Google homepage and search for a random string to check HTML connectivity.e. Start an FTP client:i Connect to the Inmarsat FTP server.ii Change directory to a test directoryt.iii “Put” a file onto a server. The transfer should complete successfully.iv The data rate should have been comparable to the expected 64kbit rate.v “Get” a file from the server. The transfer should complete successfully.vi The data rate should have been comparable to the expected 64kbit rate.vii Disconnect the FTP client.f. Disconnect the ISDN connection.H. Cabin ISDN Voice serviceIf ISDN to the cabin is fitted:a. Connect an ISDN phone to the ISDN port.b. Dial a suitable ISDN number for an ISDN voice connection:i The modem should be able to receive the “on hook” status and dial a number.ii The connection should be set up over Satcom to the number dialed.iii Have a short conversation. The voice quality should be good.iv Request a call back and hang up.v The ISDN modem should be able to accept an ISDN ground to air voice call.vi Have a short conversation. The voice quality should be good.
Installation Maintenance ManualSDU 82155 SeriesSCM 82158 Series7-7Jun 30/2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval vii Hang up.I. Cabin GSM Call and SMS ServiceIf a GSM Pico cell is fitted:a. Ensure that the AGS is powered on and the call disable is off.b. Ensure that the SDU is powered on and connected.c. Switch on a GSM mobile phone.i The phone should register to the Pico cell, with the configured network name.ii Make a phone call to a PSTN number and have a short conversation. Audio quality should be good.iii Arrange a call back and hang up. when the phone rings, answer and have a short conversation. Audio quality should be good.iv Send an SMS message to a remote GSM phone, asking for a reply. The text message should reach recipient.v The SMS reply should be received.vi Switch on the call disable.vii Attempt to place a call from the GSM phone. The call should be blocked.viii Send an SMS message asking for a call back and a reply.ix The external call should be blocked and the SMS message should still be received.d. Power off the GSM phone and disable the Pico cell.
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