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I and M Manual | Users Manual | 4.67 MiB | January 10 2008 | |||
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| 1 | Test Report | January 10 2008 | ||||||
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| 1 | I and M Manual | Users Manual | 4.67 MiB | January 10 2008 |
86, Bushey Road Raynes Park, London SW20 0JW Tel: +44 (0)20 8946 8011 Fax: +44 (0)20 8946 7530 INSTALLATION AND MAINTENANCE MANUAL Satellite Data Unit (SDU) 82155 Series SDU Configuration Module (SCM) 82158 Series Revision No. 01 First 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 companys prior written approval 1 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Section 1 INTRODUCTION Page 1.1. 1.2. 1.3. 1.4. 1.5. 1.6. Purpose of Manual . 1-1 Special Precautions. 1-1 Contact Information . 1-2 Scope of Manual . 1-2 Reference documents . 1-2 Compliance to Regulations . 1-3 A. Federal Communication Commision . 1-3 B. European Aviation Safety Agency. 1-3 Section 2 DESCRIPTION Page 2.1. 2.2. 2.3. 2.4. 2.5. 2.6. TFS Satellite Communication System Domain . 2-1 TFS System Overview. 2-1 system Configurations . 2-2 A. Single Aisle TFS System. 2-2 B. SDU Type 82155D TFS system . 2-3 SDU Component Description. 2-4 A. Hardware. 2-4
(1) SDU Type 82155A . 2-4
(2) SDU Type 82155D . 2-4 B. Functionality . 2-5
(1) SDU Type 82155A.. 2-5
(2) SDU Type 82155D.. 2-5 C. Software . 2-6 D. ORT Parameters . 2-6 E. General Operation. 2-6 F. Sub-modules Basic Detailed Operation . 2-7 G. Operating Environment . 2-8
(1) Normal Operating temperature: . 2-8
(2) Cooling:. 2-8
(3) Heat dissipation: . 2-8 H. Environment Conditions . 2-8 I. Identification Label . 2-10 J. Weight and Dimensions . 2-12
(1) SDU Type 82155A . 2-12
(2) SDU Type 82155D . 2-12 K. SDU Electrical Characteristics . 2-15 System Interfaces . 2-15 A. Aircraft Power Utility Service. 2-15 B. Avionics Interfaces . 2-16 C. Cockpit Interfaces (SDU Type 82155D only) . 2-17 D. Maintenance System Interfaces . 2-17 SDU Configurable Pinout and Pin Description . 2-17 A. Mandatory Configuration Pins. 2-18 THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval i Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 2.7. 2.8. SDU Interconnect Data . 2-18 A. ARINC 600 Standard Interwiring Connector . 2-18
(1) ARINC 600 Pin Assignment . 2-19 B. Electrical Interconnection Diagrams . 2-24 Interconnection Cables . 2-35 C.
(1) RF Coaxial Cables . 2-35
(2) Power Cables . 2-36
(3) ARINC 429 Connections. 2-36
(4) Ethernet . 2-36 SCM Component Description . 2-36 A. Hardware. 2-36
(1) External Description . 2-36
(2) Internal Description. 2-37 B. ORT Parameters . 2-38 C. ORT Synchronisation . 2-39 D. Basic Operation. 2-39 E. Environment Condition . 2-39 F. Identification Label . 2-40 G. SCM Electrical Characteristics . 2-41 H. Weight and Dimensions . 2-41 I. SCM Connector. 2-42 J. Equipment Electrical Interconnection Diagram . 2-42 Section 3 INSTALLATION GUIDELINES Page 3.1. 3.2. 3.3. 3.4. 3.5. 3.6. 3.7. 3.8. Introduction . 3-1 Interchangeability . 3-1 SDU/SCM Location and Accessibility Guidelines . 3-2 Mounting Tray . 3-2 Cooling . 3-3 Power Requirements . 3-3 SDU RF Connections . 3-4 D. Insertion Losses . 3-4 E. Product InterModulation (PIM) . 3-5 F. VSWR . 3-5 G. Torque Settings. 3-5 H. Cleaning . 3-5 Bonding Requirements . 3-5 Section 4 INSPECTION AND SYSTEM CHECKOUT Page 4.1. 4.2. Inspection/Check Procedure . 4-1 A. Check Wiring and RF cables. 4-1 B. Check SDU . 4-1 C. Check SCM . 4-2 System checkout . 4-2 A. Post-Installation Test. 4-2 THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval ii Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Section 5 FAULT ISOLATION Page 5.1. 5.2. 5.3. Bite Function . 5-1 Test Functions . 5-2 A. OMS or CFDS . 5-2 B. BITE . 5-2
(1) POST . 5-3
(2) PAST . 5-4 fault isolation . 5-5 A. Failures . 5-5 B. Front Panel Indications . 5-5 C. Fault Logging . 5-8 D. Service Availability Discretes . 5-8 E. Service Availability Discrete Lamps . 5-9 F. CFDS/ARINC 604 BITE . 5-9 Section 6 MAINTENANCE Practices Page 6.1. 6.2. 6.3. 6.4. 6.5. 6.6. 6.7. 6.8. General . 6-1 Equipment and Materials. 6-1 Procedure For The SDU . 6-2 A. Removal and Installation Procedure . 6-2
(1) Remove the SDU . 6-2
(2) Install the SDU . 6-3 B. Adjustment Procedure. 6-3 C. Repair Procedure . 6-3 D. Return to Service Procedures . 6-3 Procedure For The SCM . 6-4 A. Removal and Installation Procedure . 6-4
(1) Remove the SCM . 6-4
(2) Install the SCM . 6-4 B. Adjustment Procedure. 6-5 C. Repair Procedure . 6-5 D. Return to Service Procedures . 6-5 Cleaning of Mechanical Parts . 6-5 Periodic Checks. 6-6 Cabling and Connections. 6-6 Instructions For Continued Airworthiness . 6-6 Section 7 COMMISSIONING Page 7.1. General . 7-1 A. Registration . 7-1 B. Classic Packet Data Verification . 7-3 C. Classic Cockpit Voice Calls. 7-3 D. SBB Cabin Wifi Data Connectivity (Background Context) . 7-3 E. SBB Cabin Wifi Data Connectivity (Streaming Context) . 7-4 F. Cabin VoIP service . 7-5 G. Cabin ISDN Data service . 7-5 H. Cabin ISDN Voice service. 7-6 I. Cabin GSM Call and SMS Service . 7-7 THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval iii Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval iv Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series RECORD OF REVISIONS Revision No:
Revision Date Date Inserted By Revision No:
Revision Date Date Inserted By THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval v Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval vi Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series List of Abbreviations ac ACARS ADL AES AGS AIM AMO AMU AOR-E AOR-W APM ARINC ATE BGAN BITE BSU CCM CDU CFDS CMM CMU CPM dc DLNA EASA Alternating Current Aircraft Communication Addressing and Report-
ing System Airborne Data Loader Aeronautical Earth Station Airborne GSM Server Antenna Interface Mounting Approved Maintenance Organization Audio Management Unit Atlantic Ocean Region-East Atlantic Ocean Region-West Avionics Processor Module Aeronautical Radio Inc Automatic Test Equipment Broadband Global Area Network Built In Test Equipment Beam Steering Unit Channel Card Module Control Display Unit Cenralised Fault Display System Component Maintenance Manual Communication Management Unit Communication Processor Module Direct Current Diplexer and Low Noise Amplifier European Aviation Safety Agency THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval vii Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series External Configuration Memory Environmental Control System Electromagnetic Compatibility Electro Static Discharge Electro Static Discharge Sensitive Flange Mounted High Power Amplifier Front Panel LED Ground Earth Station Global Navigation Satellite System Global Positioning System High Power Amplifier Intermediate Gain Antenna International Mobile Equipment Identity Installation and Maintenance Manual International Mobile Subscriber Identity International Maritime Satellite Organization Indian Ocean Region Internet Protocol Illustrated Parts List Inertial Reference System Input/Output Integrated Service Digital Network Light Emitting Diode Land Earth Station Line Replaceable Unit MilliAmpere Multi-function Control and Display Unit List of Abbreviations ECM ECS EMC ESD ESDS FMHPA FPL GES GNSS GPS HPA IGA IMEI IMM IMSI INMARSAT IOR IP IPC IRS I/O ISDN LED LES LRU mA MCDU THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval viii Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Modular Concept Unit Minimum Equipment Level Mobile Earth Station Management Information Base Non Volatile Memory Onboard Monitoring System Owner Requirements Table Oven Controlled Crystal Oscillator Person Activated Self Test Personal Computer Public Land Mobile Network Part Number Pacific Ocean Region Power On Self-Test Point To Point Protocol over Ethernet Power Supply Module Public Switched Telephone Network Radio Frequency Single Aisle Satellite Communication SwiftBroadband Satellite Control Display Unit SDU Configuration Module Satellite Data Unit Subscriber Identity Module Standalone Interface System Simple Network Management Protocol List of Abbreviations MCU MEL MES MIB NVM OMS ORT OCXO PAST PC PLMN PNR POR POST PPPoE PSM PSTN RF SA SATCOM SBB SCDU SCM SDU SIM SIS SNMP THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval ix Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series List of Abbreviations SRU STC SW TCP/IP TFS UMTS USIM Wi Fi WLAN WOW Shop Replaceable Unit Supplemental Type Certificate Software Transmission Control Protocol/Internet Protocol TopFlight Satcom Universal Mobile Telecommunication System Universal Subscriber Identity Module Wireless Fidelity Wireless Local Area Network Weight On Wheels THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval x Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series SECTION 1 10000INTRODUCTION 1.1. PURPOSE OF MANUAL This manual sets forth installation and maintenance guidelines, and theory of operation for the THALES TopFlight Satcom (TFS) Satellite Data Unit (SDU), and SDU Configuration Module (SCM). The SDU and SCM installation specific and general guidelines contained within this manual are supported by mechanical and electrical interconnection drawings and interface information. Drawings should be reviewed by the installation organisation, and any requirements specific to a particular airframe should be assessed before installation is commenced. The Manual covers the following topics:
Title Page a. Record of Revisions b. Table of Content c. d. Introduction e. Description f. g. h. i. Maintenance Practices j. Commissioning. Installation Guidelines Inspection and System Checkout Fault Isolation 1.2. SPECIAL PRECAUTIONS Advisory 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 injury b. A CAUTION is used to denote the possibility of damage to materiel but not danger to personnel c. A NOTE is used to convey, or draw attention to, information that is extraneous to the immediate subject of the text. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 1-1 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 1.3. CONTACT INFORMATION For any queries related to information contained within this Manual contact the following:
THALES TFS Project Manager 86 Bushey Road Raynes Park, London SW20 0JW, UK Tel. +44 (0)20 8946 8011 Fax. +44 (0)20 8946 7530 1.4. SCOPE OF MANUAL The Thales SDU and SCM comply with the design requirements set forward in the ARINC 781 Characteristic. An ARINC 781 compliant system is intended to support one or more of the Inmarsat aeronautical services known as Classic-Aero, Swift 64, and SwiftBroadband. This manual provides information specific for the SDU and SCM capable of providing those services highlighted above. The SDU and SCM covered in this manual support Inmarsat Class 3A, 6 and 7 services only. 1.5. REFERENCE DOCUMENTS The following publications provide additional useful information:
Table 1.1 Reference Documents THALES SCM Component Maintenance Manual THALES SDU Component Maintenance Manual EMS AMT-3500 Intermediate Gain Antenna Subsystem Installation Manual Mark 33 Digital Information Transfer System Air Transport Avionics Equipment Interfaces Airborne Computer High speed Data Loader Ethernet Based Data loading Mark III Aviation Satellite Communication (Satcom) Sys-
tem Avionics 44-35-33 44-35-32 MN-1242-20047 ARINC 429 ARINC 600 ARINC 615 ARINC 615A ARINC 781 THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 1-2 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 1.6. COMPLIANCE TO REGULATIONS A. Federal Communication Commision The SDU is designed to be compliant with part 15 and part 87 of the Federal Communication Commission (FCC) regulations B. European Aviation Safety Agency The 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. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 1-3 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 1-4 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series SECTION 2 20000DESCRIPTION 2.1. TFS SATELLITE COMMUNICATION SYSTEM DOMAIN Satellite Communications (SATCOM) systems provide users with long-range voice and data communication by accessing global satellite and ground communications networks. The introduction of Pico-Cells on aircrafts, and the I3 and I4 INMARSAT constellation of geostationary satellites have been the enabling technologies for the development of significantly smaller, more capable terminals such as the Thales TopFlight Satcom system. SwiftBroadband (SBB) is the aeronautical service, which operates on the INMARSAT Broadband Global Area Network (BGAN) infrastructure. SBB supports Circuit Switched and always-on TCP/IP data (packet switched) services. Thales SBB TopFlight Satcom system supports the Inmarsat Classes of service 3A, 6, 7 and Classic Aero H+. Tav_e_0000700_00 Inmarsat domain User Terminals Antenna I4 Satellite Backbone Networks IP, PLMN, PSTN TFS System Satellite Access Station Aeronautical Segment Space Segment Inmarsat domain Figure 2.1 Example of TFS communications system overview 2.2. TFS SYSTEM OVERVIEW The TFS system conforms to the Aeronautical Radio Incorporated (ARINC) 781 Characteristic, and interfaces with onboard avionics and communication equipment to provide the aircraft with a range of communication services by transmitting and THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-1 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series receiving L Band signals to and from the fourth generation of INMARSAT satellites. For this purpose the INMARSAT satellite constellation is connected to the ground backbone telecommunication network through Satellite Access Stations (SAS) operated by service providers. 2.3. SYSTEM CONFIGURATIONS TFS Satcom may be installed in different aircraft configurations, some examples are as follows:
A. Single Aisle TFS System The 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. SCM Power RF Rx SDU RF Tx DNLA External Interfaces RF Bite/
Control ARINC 781 ANTENNA
(Contains BSU Functions) Tav_e_0000706_00 ARINC 429
(Multicontrol) ARINC 429
(Bite from Antenna) Figure 2.2 Example of Single Aisle TFS system interfacing THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-2 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series B. SDU Type 82155D TFS system The 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 Powe r Amplifier (FMHPA) (If required) RF cables. Figure 2.3 illustrates a typical aircraft installation of the SDU Type 82155D System. SCM Power External Interfaces RF Rx SDU RF Tx RF Tx DNLA FMHPA Bite RF Bite/
Control ARINC 781 ANTENNA
(Contains BSU Functions) Tav_e_0000707_00 ARINC 429
(Multicontrol) ARINC 429
(Bite from Antenna) Figure 2.3 Example of SDU Type 82155D TFS system interfacing THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-3 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 2.4. SDU COMPONENT DESCRIPTION A. Hardware NOTE:
SDU hardware is targeted at RTCA/DO-254 level C. The SDU hardware meets RTCA/DO-254 level D requirements, and it is composed of the following internal sub-assemblies (Refer to Figure 2.4):
(1) SDU Type 82155A High Power Amplifier (HPA) Channel Card Module (CCM) x 1 Communication Pro cessor 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 is packaged in an ARINC 600 6 Modular Concept Unit (MCU) housing suitable for mounting in the equipment bay of an aircraft. Two hold-down clamps are used to secure the SDU, permitting it to be firmly held in position in the mounting rack. A handle fitted on the front panel of the SDU permits removal, installation and carrying of the SDU. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-4 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Figure 2.4 Example of SDU sub-system modules exploded B. Functionality The 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)). THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-5 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series C. Software The software in the SDU can be considered as being supplied in two elements, one contained within the CCM the other operating on the SDU processors (CPM & APM). The SDUs application software primarily functions as the system controller providing system level tasks such as CCM control, BITE reporting, Avionics interfacing via ARINC-429 (including Inertial Reference System (IRS)) and providing external interfaces (such as Ethernet) as well as routing functions between the external interfaces and the CCM as necessary. The SDUs APM and CPM application software meets RTCA/DO-178B level D requirements, and the CCM application software meets RTCA/DO-178 level E (Level D for Classic only) requirements. D. ORT Parameters The primary source of Owner Requirement Table (ORT) is the SCM ORT and is also stored inside the SDU. The ORT database contains configuration data that is used to customize the operation of the TFS system. It allows various preferences to be set to enable the efficient use of the equipment in normal operation. The SDU is delivered to customers with a default ORT. E. General Operation The SDU controls and processes all essential data in order to manage the reception and transmission of data through the satellite link. The SDU controls the set-up of the required channel types, providing modulation/demodulation, error correction, coding, and data rates associated with the satellite communication channel(s). The SDU is of modular design and can be configured for use on a wide variety of aircraft. That is cabin only, cockpit only or cabin and cockpit services. The SDU converts digital/audio inputs to Radio Frequency (RF), and contains a HPA function providing the necessary output power to support communication between the aircraft and the satellite. It also controls the associated antenna sub-system and uses the SCM for its own configuration data purposes. When the distance between the SDU and the DLNA would require an RF cable with a loss 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. The SDU internal HPA will then run at a reduced power output. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-6 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 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 Operation The Front Panel assembly gives visual indications for system status, external maintenance interface connections, the SDU Person Activated Self-Test (PAST) push button and a connector for the Standalone Interface System (SIS). The Backplane assembly makes interconnections between external interfaces and the SDU internal sub-assemblies. The APM provides interfacing to external avionics. It receives aircraft position, speed and heading information from external avionics via ARINC 429, and updates the CCM with position information every second. The APM manages satellite selection based on aircraft position, and maintains antenna pointing to the wanted satellite beam steering via ARINC 429. The APM manages RF resources and set CCM transmit power levels, taking into consideration antenna gain and cable losses stored within the ORT. The CPM handles and controls all communications interfaces (Ethernet, RS232 and RS422) and analog audio (cockpit 4-wire). The CCM converts users input/output data to signals suitable for transmitting and receiving L-Band signals using the satellite link. The HPA module amplifies the low level RF signals from the CCM to produce high power output prior to connection to the antenna. The PSM operates from 115 Vac and supplies low level dc power supplies to SRUs within the SDU and 12 Vdc to the SCM. The OCXO provides 10 MHz clock reference signal for the CCM circuit. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-7 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 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 50 kg/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 Conditions The SDU complies with the RTCA/DO-160-E (ED-14E). The environmental qualifications categories complied with, are as per listed refer (Table 2.1). Table 2.1 Environmental Test categories for SDU and SCM RTCA DO-160E (ED-14E) Environmental Categories Section Condition Category 4.0 4.5.4 5.0 6.0 7.0 8.0 9.0 10.0 11.0 12.0 13.0 Temperature/Altitude Loss of Cooling Temp Var Humidity Shock/Crash Vibration Vibration Curve Explosion Waterproof Fluids Sand/Dust Fungus A2 V B B B,E R C E X X X F THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-8 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series RTCA DO-160E (ED-14E) Environmental Categories Section Condition 14.0 15.0 16.0 17.0 18.0 19.0 20.0 21.0 22.0 23.0 24.0 25.0 26.0 Salt Fog Magnetic Effect Power Input Harmonics Voltage Spike Conducted Audio Susceptibility Induced Signal Susceptibility RF Susceptibility RF Emissions Lightning Induced Lightning Direct Effects Icing ESD Fire, Flammability Category X A A(CF), A(NF), A(WF) H A K(CF), K(NF) K(WF) CW TT M A3G33
(SDU 82155A only) X X TBC TBD THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-9 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series I. Identification Label Figure 2.5 represent the SDU Front Panel Identification Panel, for detalied description of the numbered field Refer to Table 2.2. 3 4 5 6 7 8 18 17 16 15 14 13 12 1 2 SATELLITE DATA UNIT (SDU) Supply 115VAC CSD cm Wt. 9.5kg (max) FAA TC FCC id HW DO-254 Level C SW DO-178B Level D DO-160E Env. Cat
[(A2)Z]BAE[SC]EXXXFXA[
A(WF)]A[R(WF)][ZW][RR
]M[A3G33]XXAC CAUTION THIS EQUIPMENT REQUIRES FIELD LOADABLE SOFTWARE ENSURE CORRECT SOFTWARE IS LOADED REFER TO AMM MFR MFR K0385 SER SER NO DMF DMF AMDT A B C D E F G H I J K L INSPECT S I S HW PNR HW PNR 82155X30 Minor Rev. A SW PNR SW PNR TEST TEST PORT SDU SCM Antenna DLNA Ext. HPA Ext. BSU Ext. Data Bus ORT/Config. Sat. Link #1 Sat. Link #2 LED INDICATIONS MAY RELATE TO OTHER EQUIPMENT OR AIRCRAFT WIRING CAUTION CAUTION HOT SURFACE 11 10 9 Tav_e_0000727_00 Figure 2.5 Example of SDU Front Panel Legend THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-10 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series SDU Front Panel Legend Table 2.2 SDU Front Panel Legend 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Manufacturers Name Voltage Supply,Compass Safe Distance Manufacturers Code Equipment Serial Number Date of Final Factory Inspection (month and year) Amendment Label Inspection Stamp Standalone Identification System, Weight of Equipment, FCC ID, Hardware and Software Compliance Reference Caution labels Carrying Handle Hold Down Lugs Status Light Emitting Diodes (LEDs) Ethernet RJ45 Maintenance Connector Field Loadable Software Warning Push To Test Switch Software Part Number Hardware Minor Revision Hardware Part Number THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-11 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series J. Weight and Dimensions NOTE:
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. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-12 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 217.7 (8.6") 52.3 (2") 190.9 (7.5") REF. 188.0 (7.4") 2.2 (0.1") 62.4 (2.46") 50.9 (2") 3.2 (0.12") COOLING OUTLET AREA (ARINC) 382.6 (15") REF. 320.2 (12.6") CofG Dim. 'C' (See Table) 53.4 (2.1")
5 0 0
4 1
8 7 7 6 1 4 1
. F E R 1
. 7 9 1
6 4
. 0
3 7
. 1 1 132.1 (5.2") CofG Dim. 'B'
9.65 (0.38") 34.6 (1.36") REF. 116.8 (4.56") 285.7 (11.25") 168.9 (6.652) REF.
1 2 0
F E R 4 5
2 2 0
6 5
1 7
9 9 7 1
. 190.5 (7.5")
2 6 7
5 3 9 1
4 1 0
6 3
8 8 4
9 3 2 1
. Tav_e_0000733_00 Figure 2.6 SDU Overall Dimensions. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-13 Jun 30/2008
A
. i m D G o C f Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-14 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 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 INTERFACES The SDU interfaces with various aircraft systems. A. Aircraft Power Utility Service The TFS interfaces with the aircraft primary power generator (Refer to Figure 2.7):
Tav_e_0000712_00 Aircraft Power supply SDU BP01 115 Vac Cold BP05 BP03 115 Vac Hot F E 18 19 A 22 DLNA IGA/
HGA 115 Vac-7.5 AMP Circuit Breaker Chassis Ground Power Source 12 VDC SCM Power Return MP01D MP02D SCM Figure 2.7 TFS example of aircraft Power Distribution diagram THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-15 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series B. Avionics Interfaces The 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 be provided with the aircraft present position within 1500m in three dimensions, referenced to WGS-84 (GPS) . In order to comply with this requirement the TFS SDU requires ARINC 429 Nav Data labels (Refer to Table 2.3). The values apply to aircraft where only one Nav Data bus is connected. For Classic and S64 only IRS present position is required. Table 2.3 ARINC 429 Nav Data Labels - Hybrid PARAMETERS Latitude GNSS - Hybrid/Inertial Longitude GNSS - Hybrid/Inertial Ground Speed GNSS - Hybrid Track Angle True GNSS Hybrid True Heading Hybrid Pitch Angle Roll Angle ARINC 429 LABELS 254/Inertial 255/Inertial 175 137 132 324 325 GNSS Height (HAE) or Hybrid Altitude MSL 370 or 261 GNSS UTC (Binary) GNSS Date 150 260 THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-16 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series PARAMETERS GNSS Sensor Status GNSS HDOP ARINC 429 LABELS 273 101 C. Cockpit Interfaces (SDU Type 82155D only) Cockpit Audio Management Unit (AMU) Centralised Fault Display System (CFDS) Communications Management Unit (CMU)
Multi-Purpose Control a nd Display Unit (MCDU). D. Maintenance System Interfaces The 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 Thales TFS product support representative at the following address:
86 Bushey Road Raynes Park, London SW20 0JW, UK Tel. +44 (0)20 8946 8011 (Switchboard) Tel. +44 (0)20 8946 5169 (Hot desk). 2.6. SDU CONFIGURABLE PINOUT AND PIN DESCRIPTION In the case of using the mandatory configuration straps the SDU is configurable via the SDU ARINC 600 configuration straps as defined in ARINC 781. The straps input values will be read only at unit power-up to determine the system configuration. The SDU configuration will be selectable by multiplexing the Configuration Straps inputs with the service availability discrete outputs as per ARINC 781 Attachment 1-4. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-17 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series A. Mandatory Configuration Pins The link between pins Top plug (TP)3D and TP3E must be removed when an external FMHPA is connected. They are used as hardware implemented safety override to force the internal HPA function into low power mode. Pin TP3G must be used on all aircraft installations since one of its functions is to indicate whether all other configuration pins (excluding TP3D, TP3E, TP3F, TP3G, and TP4D) should be used by the SDU. Pin TP4D should be used on all aircraft installations since it indicates the SDU number (1 or 2). Pin TP3F must be used on all aircraft installations since it indicates that the number of all configuration pins (excluding TP3D) including the parity pin itself connected to service availability discrete (or TP3D) is odd. 2.7. SDU INTERCONNECT DATA A. ARINC 600 Standard Interwiring Connector The SDU ARINC 600 connector provides:
Input/Output connections EMC filtering to input and output interfaces ESD (Electrostatic Discharge) (R efer DO-160 E section 25 Cat A). The SDU is provided with a low insertion force, size 2-shell receptacle in accordance with ARINC 600 Attachment 19. This connector accommodates coaxial and signal interconnections in the TP insert, Quadrax and signal interconnections in the middle plug (MP) insert, and coaxial, fibre and power interconnections in the Bottom Plug (BP) insert. The contact arrangements are as follows:
Insert arrangement 08 receptac le in accordance with ARINC Specification 600, Attachment 11 for the top insert (Size 1 Coax cavity and Size 22 Signal sockets) Insert arrangement 120Q2 receptac le 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 recept acle 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). THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-18 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 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 Assignment The layout of the rear panel ARINC 600 connector and the Pin assignment are shown in the figures 2.8, 2.9, 2.10 and 2.11. For further Information regarding the ARINC 600 connector refer ARINC 781 (Refer to Figure 2.8). THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-19 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Top Plug Middle Plug Index code 81
(5,2,2) NOTE: The index code pins dark colour represents the post Bottom Plug A B C D E F G H J A B C D E F G H J A B C D E F G H J 1 2 1 3 1 4 1 5 9 8 11 10 12 5 1 5 7 1 3 6 1 5 7 1 2 3 4 5 6 7 8 9 1 0 1 1 2 4 7 Figure 2.8 ARINC 600 Connector Layout Tav_e_0000734_00 THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-20 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series RF TX To HPA or DLNA A ATE Pin 1 A ATE Pin 11 B ATE Pin 2 B ATE Pin 12 Ethernet 1 Ethernet 1 TX A RX A Ethernet 1 Ethernet 1 RX B Empty Cavity TX B Empty Cavity Ethernet 2 Ethernet 2 TX RX MCDU 3 MCDU 3 A A Ethernet 2 Ethernet 2 RX B TX B 1 2 3 4 5 6 7 Tav_e_0000735_00 C ATE Pin 3 D ATE Pin 4 E ATE Pin 5 F ATE Pin 6 G ATE Pin 7 H ATE Pin 8 J ATE Pin 9 K ATE Pin 10 ATE Pin 13 ATE Pin 14 ATE Pin 15 ATE Pin 16 ATE Pin 17 ATE Pin 18 ATE Pin 19 ATE Pin 20 Empty Cavity Config Pin 1 Config Pin 2 Config Pin 3 Config Pin 4 Empty Cavity Config Pin 5 Config Pin 6 Config Pin 7 Config Pin 8 SPARE ISDN 1 TX A ISDN 1 RX B SPARE ISDN 1 ISDN 1 RX A TX B Empty Cavity Config Pin 9 Config Pin 10 Config Pin 11 Config Pin 12 SPARE SPARE SPARE Empty Cavity Config Pin 13 Config Pin 14 Empty Cavity Config Pin 17
(Spare) Config Pin 18
(Spare) Config Pin 15
(Spare) Config Pin 19
(Spare) Config Pin 16
(Spare) Config Pin 20
(Spare) SPARE ISDN 2 TX A ISDN 2 RX B SPARE ISDN 2 ISDN 2 RX A TX B Figure 2.9 ARINC 600 Top Plug THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-21 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 2 4 28V HOT 28V GND 9 8 ETHERNET 7 ETHERNET 6 11 10 ETHERNET 9 ETHERNET 8 12 ETHERNET 10 5 115v HOT 1 3 115V COLD CHASSIS GROUND DLNA SPARE 7 6 Tav_e_0000736_00 Figure 2.10 ARINC 600 Bottom Plug THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-22 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Spare Discrete Spare ARINC Input 429 Output 429 Output C Call Place/End Discrete Input 1 CP Voice Chime Signal Contact Cockpit Voice Call Light Output 1 Cockpit Voice Mic On Input 1 CP Voice Go Ahead Chime Reset 1 Spare Discrete Input WOW Discrete Input A B Data from MCDU 1 Data from MCDU 1 A B Data from primary Data from primary IRS A Data from CMU 1 A Cockpit Audio Input 1 High Cockpit Audio Output 1 High Spare Discrete Input IRS B Data from CMU 1 B Cockpit Audio Input 1 Low Cockpit Audio Output 1 Low Spare Discrete Input AES ID Input AES ID Input A Data from CFDS A B Data from CFDS B D SCM Pwr
+12V SCM Pwr Return 0V E Multi-
Control Output A BITE Input F Multi-
Control Output B BITE Input from HPA from HPA SDU Data to SCM A SDU Data to SCM B SCM Data to SDU A SCM Data to SDU B WOW Input 1 A Spare Discrete Output Spare Discrete Output Spare Discrete Output Ethernet 5 10 Base T
(spare) from SDU to User+
Ethernet 5 10 Base T
(spare) from User to SDU +
Data Loader Link A Dual System Select B Spare Discrete Input Spare Discrete Input Ethernet 5 10 Base T
(spare) from SDU to User-
Ethernet 5 10 Base T
(spare) from User to SDU -
TX Mute Input Dual System Disable BITE Input Top/Port BSU/Ant BITE Input Top/Port BSU/Ant A B From Airborne From Airborne Crosstalk Crosstalk from from Data Loader Data Loader other SDU other SDU A Data from B Data from A B Port BSU Port BSU HPA HPA Discrete I/O LNA On /
Off Control Discrete Inp. BITE Input from LNA MCDU 3 MCDU 3 Mute Input Mute Input A POTS 1 B A POTS 1 Cabin B Cabin CEPT-E1 Data Output CEPT-E1 Data Output Service Availability Discretes Service Availability Discretes A B A B 1 2 Ethernet 3 TX A Ethernet 3 RX A Ethernet 3 RX B Ethernet 3 TX B Service Availability Discretes Service Availability Discretes 3 4 Service Availability Discretes Service Availability Discretes 5 6 Service Availability Discretes Service Availability Discretes 7 8 Service Availability Discretes Service Availability Discretes 9 10 J K Data from MCDU 2 Data from MCDU 2 A Data from B Data from secondary secondary IRS A Data from CMU 2 A Cockpit Audio Input 2 High Cockpit Audio Output 2 High Spare ARINC 429 Input A Data to CMU 1 & 2 A Data to A To IRS B Data from CMU 2 B Cockpit Audio Input 2 Low Cockpit Audio Output 2 Low Spare ARINC 429 Input B Data to CMU 1 & 2 B Data to CFDS B To Airborne Airborne Data Loader Data Loader A Data to MCDU 1, 2, 3 A B Data to MCDU 1, 2, 3 B POTS 2 POTS 2 G Resv Ext Reset Discrete Input RSVD Mfr-Specific 0-28V Discrete Output SPARE SPARE H Call Place/End Discrete Input 2 CP Voice Chime Signal Contact Cockpit Voice Call Light Output 2 Cockpit Voice Mic On Input 2 Spare ARINC A Spare ARINC 429 Input A Spare ARINC B Spare ARINC 429 Input B Spare ARINC 429 Output 429 Output A BITE Input B BITE Input A Crosstalk to other SDU A STBD B Crosstalk to other SDU B STBD BSU HPA Mute Input BSU HPA Mute Input A Cabin CEPT-E1 Data Input A B Cabin CEPT-E1 Data Input STBD BSU STBD BSU CFDS B A B Ethernet 4 RX A Ethernet 4 TX B Ethernet 4 TX A Ethernet 4 RX B 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Tav_e_0000725_00 Figure 2.11 ARINC 600 Connect Arrangement For Middle Plug Insert THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-23 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series B. Electrical Interconnection Diagrams The SDU interconnection diagrams (refer to 2.12 to 2.16) illustrate all the necessary connection between the SDU and all the other interfaced equipment. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-24 Jun 30/2008 F DLNA
(Note 5) E A D/LNA BITE D/LNA BITE Return RX Port TX Port D/LNA Control Antenna Port H J B
(Note 2) 18 19 Antenna
(Note 4) 22 9 10 11 4 6 8 7 3 5 8 15 7 3 4 1 2 7 SCM
(Note 3) Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 115V AC - 7.5 AMP Type A Circuit Breaker Aircraft Power Supply 115 Vac Cold 115 Vac Hot BP01 BP05 BP03 115 Vac Cold 115 Vac Hot Chassis Ground SDU RF Input from D/LNA SDU RF Output to D/LNA BP07 TP71
(Note 2) Navigation Data Navigation Data External HPA not fitted See Note 13 for Signal Details External Reset See Note 1 for Signal Details System Failed Indication TX Mute
(Note 11) ARINC 615A Data Loader Connector RX +
RX -
TX +
TX -
See Figure 2 -13 for list of Explanatory Notes Tav_e_0000704_00 BITE Input Top/Port BSU/Ant (A) BITE Input Top/Port BSU/Ant (B) MP02A MP02B Primary Nav Data (A) Primary Nav Data (B) Multi-Control Output (A) Multi-Control Output (B) MP08C MP08D MP01E MP01F MP01J MP01K TP3D TP3E MP1G MP11F MP8F Secondary Nav Data (A) Secondary Nav Data (B) Config Pin 1 Config Pin 2 SPARE Service Availability Discrete 2 TX Mute Input SCM Power Source SCM Power Return MP01D MP02D Data to SCM (A) Data to SCM (B) MP03D MP04D Data from SCM (A) Data from SCM (B) MP05D MP06D TP01A TP01C Rear Ethernet TX (A) Rear Ethernet TX (B) TP01B TP01D Rear Ethernet RX (A) Rear Ethernet RX (B) Ethernet 3 TX (A) Q1 Ethernet 3 TX (B) Q1 1T-1 1T-3 Ethernet 3 RX (A) Q1 Ethernet 3 RX (B) Q1 1T-2 1T-4
(Note 6) RX +
RX -
TX +
TX -
Client Ethernet Port Connector SDU
(Notes 1,7,10) 5 4
J R l e n a P t n o r F 3 6 RX+
RX-
TX+
TX-
1 2
(Note 12)
(Note 8) TX+
TX-
RX+
RX-
Maintenance Terminal Connector Figure 2.12 TFS System Interconnection Block Diagram - SDU Type 82155A (Single Aisle Configuration) THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-25 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-26 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series ARINC 600 SDU Connector defined in ARINC 781 - see Note 1 Size 1 Co-ax Plug. Radial:
P/N:620 001 (male center connector) Notes A B C D E F G H J Note 6 : Uses Star-Quad cable as defined in ARINC 664 Part 2. Cross-over to be provided in cable. Note 1 : System interconnections are as per ARINC781 - refer to ARINC 781 for clarification / further detail. Quadrax Insert 1T 1 5 7 1 2 3 4 5 6 7 8 9 1 0 1 1 2 4 7 A A B C D E B C D E F F G H G H J J 1 2 1 3 1 4 1 5 9 8 11 10 12 5 1 5 7 1 3 6 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. Quadrax Insert 2T Note 2 RF Cable Losses Note 4 IGA/HGA Power and Control Connector Index code 81 (5,2,2) SDU to D/LNA D/LNA to Antenna D/LNA to SDU Loss Loss 6 dB RF Loss 1.4 dB 0.3 dB Loss 25 dB The IGA mount RF connector (J2), the DLNA mount Antenna connector (J1) and the DLNA mount RX (SDU input) connector (J2) are all TNC Jack (female) type connectors. 14 13 12 21 1 15 The DLNA mount TX (SDU output) connector (J3) is a N-Type Jack (female) type connector. 11 20 Size 5 Co-ax Plug. Radial P/N:
620 121 (female center connector) See Note 8 10 19 9 Note 3 SCM Connector 22 18 8 7 4 3 5 2 6 16 17 ARINC 600 - Shell Size #2 Connector View above is looking at the SDU mount connector, Radiall Part Number: 620-600-703. Tray-mount mating half is supplied with all necessary inserts, except 1 x Size 5 Socket Coax insert (male centre contact) (Radiall P/No: 620-021), which should be ordered separately. See Radiall specification for 620-600-700 for further details on supplied inserts. Fibre inserts are not required and will not be populated on the SDU mount connector, filler plugs will be used to fill cavities. Size 5 Coax insert BP-6 is not required on the SDU mount connector and will not be populated, a filler plug will be used to fill cavity. Index Code: 81 (5,2,2)
(Top Insert: 08 / Middle Insert: 120Q2 / Bottom Insert: 12F5C2) For the index code pins above, the dark colour represents the post. Tav_e_0000737_00 Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Signal Description Data to SDU A (RS422) Data to SDU B (RS422) Data from SDU A (RS422 Data from SDU B (RS422) Reserved RS232 GND1 Spare Chassis Ground Power Input +8 to +15V Reserved- Enable RS2321 Reserved 0V strap output1 Spare Reserved RS232 Tx1 Reserved RS232 Rx1 Spare Power Return 0V Data to SDU A Data to SDU B Data from SDU A Data from SDU B Connection Not required ConnectionNot required Chassis Ground SCM Power Input Connection Not required Connection Not required Connection Not required Connection Not required Connection Not required Connection Not required SCM Power Return The 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)
. The IGA/HGA Connector is a receptacle -
13-35 insert of the MIL-C-38999 Series III family: D38999/24FC35PN which mates with D38999/26FC35S on the cable Note 5 H A B G K J C F E D The D/LNA Connector is MS3470L1210P which mates with MS3476L1210S on the cable PIN No 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 SIGNAL
+28 Vdc 28 Vdc RTN Antenna BITE A Antenna BITE SCRN Antenna BITE B Antenna Control A Antenna Control SCRN Antenna Control B D/LNA BITE D/LNA SCRN D/LNA CTL Serial SCRN 1 1 RS422 RXD A RS422 RXD B 1 RS422 TXD A 1 RS422 TXD B 1 ATE Pin 115 Vac Hot 115 Vac Return
Chassis Ground DESCRIPTION Connection Not Required Connection Not Required ARINC 429 from antenna Screen for ARINC 429 ARINC 429 from antenna ARINC 429 to antenna Screen for ARINC429 ARINC 429 to antenna BITE from D/LNA Screen/RTN for D/LNA D/LNA on/off control from antenna Connection Not Required Connection Not Required Connection Not Required Connection Not Required Connection Not Required Connection Not Required Aircraft ac power Aircr aft ac power Connection Not Required Connection Not Required Chassis Ground D/LNA Power and Control Connector Pin Pin A Pin B Pin C Pin D Pin E Pin F P in G Pin H Pin J Pin K Signal Chassis Ground LNA Control Future Spare Future Spare 115 Vac Cold 115 Vac Hot
+28V DC Hot LNA BITE LNA BITE Return
+28V DC Return Description Chassis Ground LNA Control Connection Not required Connection Not required Aircraft AC Power Aircraft AC Power Connection Not required LNA Bite LNA BITE Return Connection Not required Figure 2.13 SDU Type 82155A Interconnection Diagram Notes THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-27 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-28 Jun 30/2008 H J B
(Note 14)
(Note 4) 18 19 Note 6 Antenna 22 9 10 11 6 8 7 3 5 4 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series J1-X TX Port J1-Y J1-J FMHPA
(Note 10) HPA RF Output to DLNA J3
(Note) 4 TX Port F E A DLNA
(Note 7) DLNA BITE DLNA BITE Return DLNA Control Antenna Port SDU RF Input from DLNA BP07
(Note 3, 4) SDU RF Output to DLNA TP71
(Note 4) BITE Input from HPA (A) BITE Input from HPA (B) MP02E MP02F J2 J1-A J1-B J1-T J1-P J1-R J1-S Multi-Control Output (A) MP01E MP01F Multi-Control Output (B) BITE Input Top/Port BSU/Ant (A) BITE Input Top/Port BSU/Ant (B)
(Note 13) MP08C MP08D 115V AC - 7.5 AMP Type A Circuit Breaker Aircraft Power Supply 115 Vac Cold 115 Vac Hot BP01 BP05 BP03 115 Vac Cold 115 Vac Hot Chassis Ground Navigation Data
(IRS) See Assumption 1
(Note 13) MP02A MP02B Data from Prim. IRS (A) Data from Prim. IRS (B) Navigation Data
(IRS) See Assumption 1
(Note 13) MP02J MP02K Data from Sec. IRS (A) Data from Sec. IRS (B) Data Loader Link A MP08E
(Note 14) To Data Loader (A) To Data Loader (B) MP09J MP09K From Data Loader (A) From Data Loader (B) MP09A MP09B
(Note 13) ARINC 615 Data Loader See Assumption 2 TP03D TP03E Config Pin 1 Config Pin 2 SDU Note 1,9,12
(Note 13) AES ID BUS See Assumption 1 MP07A MP07B Data from AES (A) Data from AES (B) Tav_e_0000703_00
(Note 15)
(Note 18) SCM Power Source SCM Power Return MP01D MP02D Data to SCM (A) Data to SCM (B) MP03D MP04D Data from SCM (A) Data from SCM (B) MP05D MP06D 8 15 7 3 4 1 2
(Note 17) SCM Note 5 M3 Chassis Stud Figure 2.14 TFS System Interconnection Block Diagram - SDU Type 82155D (with External FMHPA) - HGA THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-29 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-30 Jun 30/2008 ARINC 600 SDU Connector defined in ARINC 781 - see Note 1 Size 1 Co-ax Plug. Radial:
P/N:620 001 (male center connector) Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Notes Note 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 should be used where possible Note 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). Assumptions 1: As per ARINC 781 attachment 1-4, note 15. If hybrid IRS data is not available , then connection to separate, autonomous inertial and GNSS navigation equipment 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 781-1 attachment 1-4, note 15, connection to AES ID is required for GPS derived latitue and longitude. Quadrax Insert 2T 2:Mandatory configuration pins are not connected since an external HPA is fitted. Index code 81 (5,2,2) Note 4 RF Cable Losses SDU to D/LNA D/LNA to Antenna D/LNA to SDU Loss Loss 6 dB RF Loss 1.4 dB 0.3 dB Loss 25 dB The IGA mount RF connector (J2), the DLNA mount Antenna connector (J1) and the DLNA mount RX (SDU input) connector (J2) are all TNC Jack (female) type connectors. The DLNA mount TX (SDU output) connector (J3) is a N-Type Jack (female) type connector. 11 20 Size 5 Co-ax Plug. Radial P/N:
620 121 (female center connector) See Note 8 10 19 9 Note 5 SCM Connector 22 18 8 7 Tav_e_0000708_00 ARINC 600 - Shell Size #2 Connector View above is looking at the SDU mount connector, Radiall Part Number: 620-600-703. Tray-mount mating half is supplied with all necessary inserts, except 1 x Size 5 Socket Coax insert (male centre contact) (Radiall P/No: 620-021), which should be ordered separately. See Radiall specification for 620-600-700 for further details on supplied inserts. Fibre inserts are not required and will not be populated on the SDU mount connector, filler plugs will be used to fill cavities. Size 5 Coax insert BP-6 is not required on the SDU mount connector and will not be populated, a filler plug will be used to fill cavity. Index Code: 81 (5,2,2)
(Top Insert: 08 / Middle Insert: 120Q2 / Bottom Insert: 12F5C2) For the index code pins above, the dark colour represents the post. Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Signal Description Data to SDU A (RS422) Data to SDU B (RS422) Data from SDU A (RS422 Data from SDU B (RS422) Reserved RS232 GND1 Spare Chassis Ground Power Input +8 to +15V Reserved- Enable RS2321 Reserved 0V strap output1 Spare Reserved RS232 Tx1 Reserved RS232 Rx1 Spare Power Return 0V Data to SDU A Data to SDU B Data from SDU A Data from SDU B Connection Not required ConnectionNot required Chassis Ground SCM Power Input Connection Not required Connection Not required Connection Not required Connection Not required Connection Not required Connection Not required SCM Power Return The 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 6 IGA/HGA Power and Control Connector 14 13 12 21 1 15 4 3 5 2 6 16 17 The IGA/HGA Connector is a receptacle -
13-35 insert of the MIL-C-38999 Series III family: D38999/24FC35PN which mates with D38999/26FC35S on the cable Note 7 H A B G K J C F E D The D/LNA Connector is MS3470L1210P which mates with MS3476L1210S on the cable PIN No 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 SIGNAL
+28 Vdc 28 Vdc RTN Antenna BITE A Antenna BITE SCRN Antenna BITE B Antenna Control A Antenna Control SCRN Antenna Control B D/LNA BITE D/LNA SCRN D/LNA CTL Serial SCRN 1 1 RS422 RXD A RS422 RXD B 1 RS422 TXD A 1 RS422 TXD B 1 ATE Pin 115 Vac Hot 115 Vac Return
Chassis Ground DESCRIPTION Connection Not Required Connection Not Required ARINC 429 from antenna Screen for ARINC 429 ARINC 429 from antenna ARINC 429 to antenna Screen for ARINC429 ARINC 429 to antenna BITE from D/LNA Screen/RTN for D/LNA D/LNA on/off control from antenna Connection Not Required Connection Not Required Connection Not Required Connection Not Required Connection Not Required Connection Not Required Aircraft ac power Aircr aft ac power Connection Not Required Connection Not Required Chassis Ground D/LNA Power and Control Connector Pin Pin A Pin B Pin C Pin D Pin E Pin F P in G Pin H Pin J Pin K Signal Chassis Ground LNA Control Future Spare Future Spare 115 Vac Cold 115 Vac Hot
+28V DC Hot LNA BITE LNA BITE Return
+28V DC Return Description Chassis Ground LNA Control Connection Not required Connection Not required Aircraft AC Power Aircraft AC Power Connection Not required LNA Bite LNA BITE Return Connection Not required Figure 2.15 SDU Type 82155D Interconnection Diagram Notes THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-31 Jun 30/2008 Quadrax Insert 1T A B C D E F G H J A A B C D E B C D E F F G H G H J J 1 2 1 3 1 4 1 5 9 8 11 10 12 5 1 5 7 1 3 6 1 5 7 1 2 3 4 5 6 7 8 9 1 0 1 1 2 4 7 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-32 Jun 30/2008 Tav_e_0000710_00 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Cockpit Voice Call Light Output 1 Cockpit Voice Call Light Output 2 Cockpit Voice Mic On Input 1 Cockpit Voice Mic On Input 2 Cockpit Voice Go Ahead Chime Reset 1 Cockpit Voice Chime Signal Contact 1 Cockpit Voice Chime Signal Contact 2 Call Place/End Discrete Input 1 Call Place/End Discrete Input 2 Cockpit Audio Input 1 Hi Cockpit Audio Input 1 Lo Cockpit Audio Output 1 Hi Cockpit Audio Output 1 Lo Cockpit Audio Input 2 Hi Cockpit Audio Input 2 Lo Cockpit Audio Output 2 Hi Cockpit Audio Output 2 Lo CFDS CMU 1&2
(Data-2 / Data-3) MP08A MP08B Data from CFDS (A) Data from CFDS (B) MP08J MP08K Data to CFDS (A) Data to CFDS (B) SDU Note 1,9,12 MP03A MP03B MP03J MP03K Data from CMU 1 (A) Data from CMU 1 (B) Data from CMU 2 (A) Data from CMU 2 (B) Data 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) MP07J MP07K Data to CMU 1&2 (A) Data to CMU 1&2 (B) Data to MCDU 1,2,3 (A) Data to MCDU 1,2,3 (B) MP03C MP03H MP04C MP04H MP05C MP02C MP02H MP01C MP01H MP04A MP04B MP05A MP05B MP04J MP04K MP05J MP05K MP01A MP01B MP01J MP01K MP10A MP10B MP10J MP10K Cockpit Audio Management Unit MCDU 1,2,3 Figure 2.16 TFS System Interconnection Block Diagram - SDU Type 82155D Full Cockpit Interfaces THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-33 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-34 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series C. Interconnection Cables
(1) RF Coaxial Cables The SDU is connected to the DLNA or FMHPA and Antenna (refer to Figures 2.12 to 2.15), by means of a RF low loss coaxial cable. The distance between the devices, and the cable selected for the installation must be such that the cable losses remains within the limits indicated within Figure 2-15, Note 4. If the cable losses cannot remain within the limits then an FMHPA must be installed between the SDU and the DLNA (Refer to Figure 2.13). All coaxial cable should be 50 Ohms nominally. NOTE:
Interconnect cables should be routed away from sources of potential electromagnetic interference. Use shielded wires and cables where necessary. a. SDU to DLNA Tx Port RF cable characteristics for the SDU or FMHPA to DLNA Tx port are as follows:. Maximum Path Loss Nominal Max Power Frequency Range 1.4 dB (see Note) 60 W 1626.5 1660.5 MHz Table 2.4 b. DLNA to SDU Rx Port RF cable characteristics for the DLNA to SDU Rx port Loss Range Nominal Max Power Table 2.5 6 25 dB (see Note) 0.5 W Frequency Range 1525 1559 MHz c. DLNA to Antenna Port RF cable characteristics for the DLNA to Antenna port Table 2.6 Max Path Loss Nominal Max Power Frequency Range 5th Order Inter-
modulaion 7th order Inter-
modulation 0.3 dB (see Note) 46 W 1525 1660.5 MHz
(see ARINC 781)
(see ARINC 781) THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-35 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series d. SDU to FMHPA RF cable characteristics for the SDU to FMHPA Table 2.7 Maximum Path Loss Nominal Max Power Frequency Range 8-18 dB (see Note) 200 mW 1626.5 1660.5 MHz NOTE:
Applied to the complete RF cable path and not to each component within the RF path.
(2) Power Cables The 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 Connections ARINC 429 connection cable must be a size 22 single twisted and shielded pair of wires cable.
(4) Ethernet The recommended Aerospace Grade 100Base Ethernet cable is P/N NF 24Q100. The conductor AWG size (19 strands) is size 24. Flammability requirements for this cable meet or exceed FAR25.869 requirements. 2.8. SCM COMPONENT DESCRIPTION A. Hardware The only SCM Part Number available is 82158D Series and all other different SDU configurations. The SCM hardware meets RTCA/DO-254 level D requirements. The SCM contains four USIM (Universal Subscriber Identity Module) cards. The SCM also contains an External Configuration Memory (ECM) storing the Owner Requirement Table.
(1) External Description The SCM is composed by the following external elements (Refer to Figure 2.17):
The body of the SCM with one main identification label (1). THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-36 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series The 15-way D-type (male) socket (2) The mounting plate with four attaching holes (3) 1 2 3 Tav_e_0000730_00 Figure 2.17 Example of SCM External View
(2) Internal Description The SCM is composed of the following internal parts (Refer to Figure 2.18):
One gasket between the D-type conne ctor 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) THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-37 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 1 5 2 3 4 Tav_e_0000728_00 B. ORT Parameters Figure 2.18 SCM exploded view The ORT is represented by a database containing a set of configuration data for the exclusive use of the SDU. The ORT is partitioned for two types of parameters in accordance with ARINC 781:
User parameters, for operator use Secure parameters, for aircraft specific configurations The ORT parameters are stored within the SCM and/or SDU, and are used to customise the operation of the TFS system, allowing various preferences to be set to enable the THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-38 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series efficient use of the equipment within different platform configurations. The SDU and SCM are delivered with a default ORT. C. ORT Synchronisation At each power up the SDU reads the ORT from the SCM, and compares it with its locally stored copy. In normal condition the SDU and SCM ORTs should be the same, but if different the SDU overwrites the local copy with the ORT read from the SCM. The SDU uses that ORT until the SDU is powered down. A small number of System Configuration Pins are mandatory. The others may be optionally used by installers to define additional configuration details. If the optional System Configuration Pins are not used then the configuration information may be found in the Owner Requirements Table (ORT). TP3G is used to define whether the optional 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 in case 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 it determines that an ORT is not valid refer to the ARINC 781 specification section 3.4.2 Configuration & Identification Data. NOTE:2. For more information concerning changes or updates regarding ORT contact the Thales TFS product support representative. D. Basic Operation When operating, the SCM interfaces with the SDU CCM via the SDU CPM. The SCM operation will not commence until an input voltage from the SDU is detected. Alternatively, when removed form the aircraft the SCM will also acknowledge an input voltage from a personal computer (PC), and will operate as if it were connected to an SDU. A single USIM card is required for each Swift Broadband channel operated by the SDU. The SCM contains an External Configuration Memory (ECM). The ECM is a non-
volatile memory, which stores the ORT database. E. Environment Condition Refer (Table 2.1) THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-39 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series F. Identification Label The 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 al phanumeric and bar code form SER: Basic part number and serial numbering alphanumeric and barcode from DMF: Date of final factor y inspection (month and year) Amdt: Amendments CSD: Compass Safe Distance
Wt: Weight FAA TC: Federal Aviation Administration Type Certificate (Blank) FCC id: Federal Communications Co mmission identification (Blank). SDU CONFIGURATION MODULE (SCM) PNR Minor REV. SW PNR MFR SER DMF Supply 12V D.C. CSD 10 cm Wt. 0.25 kg MAX FAA TC x FCC id xxxxxx-xxxx INSPECT 1 E F L E K D C B A J I H G t d m A A L P Tav_e_0000724_00 Figure 2.19 Example of SCM Identification Label THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-40 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series G. SCM Electrical Characteristics Electrical 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 Dimensions Weight and dimensions of the SCM are as folows:
For overall dimensions Refer to Figure 2.20
Mass = 0.25kg (0.44Lbs). 13.1 110 83.8 1 0 1
. 9 8 8 1 6
. 5
. 1 5
. 2 2 Tav_e_0000731_00 Figure 2.20 SCM Overall Dimensions THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-41 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series I. SCM Connector The SCM connector is a DB15 (15 pins gauge 20) male connector (Refer to Figure 2.21), mating with a DB-15 female connector on the cable. For complete description of Pin Assignment refer to Figure 2-13 Note 3. 1 15 Tav_e_0000729_00 Figure 2.21 Front View of 15 Pin D-Type Connector J. Equipment Electrical Interconnection Diagram The SDU interconnection diagram (Refer to Figure 2.22). The diagram illustrates all the necessary connection between the SCM and the SDU. For description of detailed pin-to-
pin connection refer to Figure 2.12 (SDU Type 82155A) and Figure 2.14 (SDU Type 82155D). THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-42 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Tav_e_0000713_00 15 way D-Type connector
+ 12V 0V RS422_Rx_A RS422_Rx_B RS422_Tx_A RS422_Tx_B SCM Figure 2.22 SDU/SCM Interconnection Diagram SDU THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-43 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 2-44 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series SECTION 3 30000INSTALLATION GUIDELINES 3.1. INTRODUCTION The SDU and SCM should be installed in the aircraft in a manner consistent with acceptable workmanship and engineering practices, and in accordance with the instructions set forth in this manual. To ensure that the system has been properly and safely installed in the aircraft the installer should make a through visual inspection and conduct an overall operational check of the system on the ground prior to commissioning to the Customer and or a flight. NOTE:
Before installing any components or cabling, read all notes contained within drawings. 3.2. INTERCHANGEABILITY The TFS comprises two major sub-systems and a number of individual units. System interchangeability for each of the major sub-systems and unit interchangeability for the individual units. The first major sub-system comprises the SDU and the SCM. The second is the antenna sub-system, comprising two LRUs, the antenna with its integrated beam steering function, and the DLNA. Interchangeability is also desired for the FMHPA. 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 to unique protocol implementations, the supply and acquisition of these units are manufacturer specific. Functional Doublets are different from Matched Pairs in that each unit of the Functional Doublet may fail and be changed independently, whereas in Matched Pairs both units must be changed regardless of which unit has failed. The Functional Doublets are as follows:
SDU and SCM SDU and FMHPA. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 3-1 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 3.3. SDU/SCM LOCATION AND ACCESSIBILITY GUIDELINES CAUTION: BEFORE EQUIPMENT INSTALLATION ENSURE THAT THE IS AIRCRAFT POWER SUPPLY CIRCUIT BREAKER POSITIONED IN THE OFF CONDITION. The SDU must be installed in a pressurized zone that is also partially temperature controlled, and mounted on an appropriate ARINC 600 compliant mounting rack. The SDU requires external forced air-cooling (refer Section 2 G). The SCM should be installed as close to the SDU as possible in order to keep the cable runs to a maximum 10 feet. To determine the best location, the installer must select equipment locations to allow easy access to these components and their connectors. Equipment location will vary with aircraft type and design/installation specifications. The location of LRUs must comply with ARINC 781 limitations. The electronic bay is the prefered location to install this unit. The SDU must be installed in a location that allows the following facilities to be accessible:
a. b. c. d. Front Panel LEDs Front Panel TFS system Test Push Button Front Panel Test Port, Software loading RJ45 connector Front Panel SIS connector. 3.4. MOUNTING TRAY The mounting tray used for the installation of the SDU must comply with the design specifications for the 6 MCU (Modular Concept Unit) form factor. Refer to the ARINC 600 Specification for detailed information regarding the design of compatible equipment and airframe installations. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 3-2 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Figure 3.1 Example of an ARINC 600, 6 MCU Mounting Tray 3.5. COOLING The SDU is designed to accept an installation configuration able to provide forced air-
cooling as defined in Section 3.5 of the ARINC Specification 600. In normal operation the SDU will be cooled by forced convection with air supplied from the platform services at a maximum flow rate of 50 kg/hr and a temperature of up to 40oC. The cooling air must enter the equipment chassis at the bottom via a plenum chamber and exhaust at the top. 3.6. POWER REQUIREMENTS It is the responsibility of the installer to select the appropriate gauge of wire for power connections, and to ensure that the required safety and voltage drop requirements are complied with. For SDU power supply specifications refer to:
a. b. c. 2.3.K: SDU Electrical Characteristics. Figure 2.7: Aircraft Power Distribution. Figures 2.12 to 2.16: TFS System Interconnection Diagrams. For SCM power supply specifications refer to:
a. b. 2.7.G: SCM Electrical Characteristics. Figure 2.12 to 2.16: TFS System Interconnection Diagrams. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 3-3 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 3.7. SDU RF CONNECTIONS CAUTION: DO NOT EXCEED MINIMUM CABLE RADIUS OF CURVATURE FOR THE COAXIAL CABLE. USE DUMMY CABLES FOR A FIRST INSTALLATION TO DETERMINE CABLE RUNS. INSTALL FINAL CABLES AFTER THIS MODELLING OPERATION. CAUTION: ONLY PREFORMED RF CABLES SHALL BE CONNECTED TO THE SATCOM SYSTEM EQUIPMENT. ATTEMPTING TO FORM CABLES OR APPLYING STRESS TO THE CABLES WHILE THEY ARE CONNECTED TO THE EQUIPMENT CONNECTORS MAY CAUSE DAMAGE TO THE EQUIPMENT. The SDU or FMHPA is connected to the DLNA through a RF coaxial cable. Installation designer must be aware that the shorter the cable is, the better system performance. As the SDU/DLNA low loss cable is sometimes almost rigid and it could have a diameter not compatible with the IGA and DLNA connectors, it is recommended to install a short portion of a smaller and more flexible cable at each end of this low loss cable (pig tail type installation). If necessary, secure the cable by means of evenly spaced collars to prevent the cable from chafing on aircraft parts and surfaces. These collars must be of a design, which avoids damaging the cable. NOTE:
Interconnect cables should be routed away from sources of potential electromagnetic interference. Use shielded wires and cables where necessary. Insertion Losses D. The SDU RF interface with the Antenna via a DLNA device. The diplexer and LNA are combined into one unit for installation. The Diplexer function couples transmit signals from the SDU to the respective antenna. The LNA amplifies the very low level L-band receive signal from its respective antenna and couples this amplified signal to the SDU. For detailed RF insertion losses refer to Section 2 C. To ensure these requirements are met, some installations need the SDU to be installed in close proximity to the antenna subsystem components or the use of low loss coaxial cable. The total loss between the DLNA and the SDU must be in the range 6 to 25 dB. If the RF cable type being used for a short cable length is less than 6 dB, an attenuator must be fitted to ensure the required loss is achieved. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 3-4 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series E. Product InterModulation (PIM) Specific care should be taken to ensure that the RF cables and connectors do not produce intermodulation products at levels higher than those specified in ARINC 781. F. VSWR The Voltage Standing Wave Ratio (VSWR) of all RF cables should be 1.2:1 or better. G. Torque Settings The cables are to be tightened to the torque settings recommended by the cable manufacturer. H. Cleaning Refer to Section 6.5 for cleaning. 3.8. BONDING REQUIREMENTS The bonding of all units to the airframe must not exceed 20 milliohms. However some aircraft manufacturers or design/installation organisation may require a lower value than the recommended 20 milliohms. NOTE:
To assure proper grounding of the TFS system, the surface of the mountings and units must be clean bare metal. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 3-5 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 3-6 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series SECTION 4 40000INSPECTION AND SYSTEM CHECKOUT 4.1. INSPECTION/CHECK PROCEDURE The 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 cables a. b. c. 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. Check that none of the cables have been damaged, and cannot be damaged by components that are installed later. Check that the cable runs are spaced away from any moving or hot part that could damage cables when in use. d. Verify that the various RF cables are within their minimum radius of curvature tolerances. Check that any attenuators that may have been used for the installation have not been omitted or mismatched. B. Check SDU a. 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. Check that the unit is properly installed and that hold down clamps are firmly tightened. Check screws and nuts general condition. Check that the contact resistance between the SDU/SCM and a point on the aircraft structure close to the component does not exceed 20 milliohms. Check that the correct air cooling and air flow is provided to the SDU. e. c. d. e. f. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 4-1 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series C. Check SCM a. 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. Check that the unit is properly installed, that all fixing screws are firmly tightened, and the cable to the SDU is secure. c. 4.2. SYSTEM CHECKOUT At this stage of the installation it is assumed that a continuity check of the wiring has been made, a visual check of the installation harness and RF cabling has been performed, and that the inspection/check procedure has been carried out. A. Post-Installation Test WARNING: THE RF POWER RADIATED BY THE TFS SYSTEM ANTENNA CAN CAUSE BODILY HARM. A PERSON IS IN DANGER IN A ZONE WHERE THE POWER FLUX IS 1 MW/CM2, OR GREATER. DURING SATCOM OPERATION THE SAFETY DISTANCE FROM THE ANTENNA MUST BE NO LESS THAN 3.5M OR 12 FEET. SINCE THERE ARE VARIOUS POSSIBLE ANTENNA LOCATIONS, IT IS THE RESPONSIBILITY OF THE OPERATOR TO DETERMINE THE AREA OF HAZARD FOR THEIR TFS SYSTEM CONFIGURATION AND TO TRAIN PERSONNEL IN GROUND SAFETY PROCEDURES. WARNING: DURING ANTENNA OPERATION (TRANSMISSION), MAKE SURE PERSONNEL ARE NOT EXPOSED TO ANY REFLECTED, SCATTERED, OR DIRECT BEAMS. ENSURE PERSONNEL ARE OUTSIDE THE MINIMUM DISTANCE SPECIFIED. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 4-2 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series CAUTION: WHEN TESTING THE COMPLETE TFS SYSTEM (ANTENNA SYSTEM INCLUDED) REFER TO THE APPLICABLE ANTENNA IMM FOR FURTHER SAFETY REQUIREMENTS AND SPECIFICATIONS. THE SDU MUST NOT BE POWERED WITHOUT AN ANTENNA OR SUITABLE LOADCONNECTED ON THE HIGH POWER TRANSMIT OUTPUT PORT. CAUTION: NEVER CONNECT OR DISCONNECT A SATCOM LRU WHEN POWER IS APPLIED. CAUTION: NEVER APPLY HIGH-LEVEL RF SIGNAL TO A POWERED-
DOWN LRU. CAUTION: NEVER DISCONNECT RF CABLES WHEN SYSTEM OPERATING. CAUTION: NEVER POWER-UP ANY LRU UNTIL ALL CONNECTIONS IN THE SYSTEM ARE MADE. CAUTION: ENSURE THAT THE APPROPRIATE ORT DATABASE IS INSTALLED IN THE SCM AND/OR SDU BEFORE PERFORMING SYSTEM 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 displaying any 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 should be considered acceptable. If any subsystem LRU fails the test, it must be returned to the vendor (refer to your vendor customer support). Refer to the Section 5 Fault Isolation for information on the SDU fault detection capabilities. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 4-3 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 4-4 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series SECTION 5 50000FAULT ISOLATION 5.1. BITE FUNCTION The primary purpose of BITE is to assist aircraft maintenance personnel in the correct maintenance of avionics equipment in a cost effective manner. The BITE does not contribute to the required function of the TFS system, but makes it easier to test or debug it. The SDU controls the TFS system BITE. It collects BITE information from other 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 other OMS), and this information is made available to maintenance personnel by means of discretes and/or LED on the SDU front panel. Failures can also be reported to a dedicated 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. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 5-1 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Figure 5.1 Example of BITE communication for TFS system 5.2. TEST FUNCTIONS A. OMS or CFDS Fault information can be displayed from an OMS/CFDS when the aircraft is so equipped. Faults that occur at anytime are stored in fault memory and reported to the OMS or CFDS. B. BITE An operator can verify the operational serviceability of the SDU and SCM by means of a set of testing facilities installed within the SDU. The SDU performs two distinctive types of test:
A Power-On Self Test (POST) is automatically activated at SDU start up. 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. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 5-2 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series
(1) POST At SDU start up (Power On), and with aircraft in the on ground condition the Front Panel LED (FPL) will display the following test sequence:
START Apply power All LEDs illuminate Amber for approximately 90 seconds LEDs flash Green for approximately 3-5 seconds (see note) LEDs remain in Off condition for the duration of approximately 75 seconds (see note) LEDs driven to indicate a Green steady condition Tav_e_0000716_00 Figure 5.2 POST LEDs Sequence NOTE:
Type 82155D SDU durations are longer, approximately 90 seconds. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 5-3 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series
(2) PAST The PAST function is initiated by depressing the front panel TEST Button (This function is only possible with aircraft on ground). To acknowledge PAST initialisation all the front panel LED start to flash green at the frequency of 2Hz. After approximately 75 seconds the SDU will transit into Operational Mode with the LED displaying the TFS system serviceability condition. This feature represents an interactive, manual test facility, which assists in the following:
Active search of failur es 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. Start Push front panel Test Button All LEDs extinguish and remain in Off condition for approximately 90 seconds LEDs flash Green for 3-20 Seconds Time variations are due to ORT synchronisation LEDs driven to indicate the Appropriate status Tav_e_0000715_00 Figure 5.3 PAST LEDs Sequence THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 5-4 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 5.3. FAULT ISOLATION A. Failures Failures are reported to an operator by means of a set of multicoloured LED located on the 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 indicat ed by all relevant LED displayed in a steady Amber condition An LED in OFF (extinguished) cond ition 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 from illuminating. B. Front Panel Indications Table 5.1 provides LED status decoding information. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 5-5 Jun 30/2008
Installation Maintenance Manual SDU 82155 Series SCM 82158 Series Table 5.1 Front Panel Indications d e r e w o P t o N U D S 2
) d e t c i d n I
d e l i a F A N L D d e r e w o P t o N U D S A N
A N
9 2 4 C N R A I
3 d e l i a F s u B A N
A N
d e r e w o P t o N U D S n o i t a r u g i f n o C e r a w d r a H r o 6 e r u l i a F r o j a M T R O
l i a F y t i r a P s p a r t S 2
) d e t c i d n I
e r u
) 2 2 4
S R X D F A
9 2 4 C N R A I r o 1
) d e t c i d n I 3 e r u l i a F s u B A N
A N
A N
. e l b a l i a v a t o n a t a D v a N C N R A I k o A N L D
A N
A N
s e s u B a t a D l l A t s e T
f l e S n i U D S t s e T
f l e S n i U D S t s e T
f l e S n i U D S t s e T
f l e S n i U D S S R I m o r f s u B 9 2 4 C N R A I k o
) 2 2 4
S R X D F A
9 2 4 a t a D S R I r o e v i t c a n i 4 d i l a v n i t o N
5 e r u l i a F r o n i M T R O
) d e t c i d n I
u g i f n o C e r a w d r a H
T R O s p a r t S n o i t a r t s e T
f l e S n i U D S
t p m e t t a t o N 1
l e n n a h C A N
g n i t p m e t t a 1
l e n n a h C
l i a v a e c i v r e S 1
l e n n a h C
t p m e t t a t o N 2
l e n n a h C 7 n o i t a t s i g e R r o n O
g o L g n i r o n O
g o L g n i 7 n o i t a t s i g e R A N
l i a v a e c i v r e S 2
l e n n a h C
l i a v a e c i v r e S 2
l e n n a h C r o n O
d e g g o L e i
, e l b a r o n O
d e g g o L e i
, e l b a d e r e t s i g e R d e r e t s i g e R n o i t a r t s i g e R r o n O
g o L r o n O
d e g g o L e i
, e l b a d e r e t s i g e R t s e T
f l e S n i U D S t s e T
f l e S n i U D S d e r e w o P t o N U D S r o d e l l a t s n I t o N M C S 2
) d e t c i d n I
d e l i a F U D S
9 2 4 C N R A I r o 1
) d e t c i d n I s u B 2 2 4
S R
X D F A t o N
e r u l i a F l a i t r a P k o U D S t s e T
f l e S n i U D S
. l i a F e t i r W
d a e R M I S U t o N
l i a F y r o m e M M C S k o M I S U M C S
t s e T
f l e S n i U D S d e r e w o P t o N U D S
s i g e r B S S t a t p m e t t a o N n o i t a r t s u B 2 2 4
S R r o 1
) d e t c i d n I 3 e r u l i a F d e r e w o P t o N U D S 2
) d e t c i d n I
d e l i a F a n n e t n A t o N
e r u l i a F l a i t r a P k o a n n e t n A t s e T
f l e S n i U D S f f O d e R r e b m A n e e r G y d a e t S n e e r G g n i h s a l F D E L U D S M C S a n n e t n A A P H
. t x E U S B
. t x E A N L D s u B a t a D
. t x E
. g i f n o C
T R O 1
k n L i
. t a S 2
k n L i
. t a S THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 5-6 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 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. 3. 4. 5.
6.
Indicted means that there is an equipment failure such that Registration
/ Log-On is not attempted. 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 Amber 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 state 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. 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. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 5-7 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 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 Logging All information of degraded and abnormal equipment function will be logged internally and made available to a dedicated local maintenance system (e.g. CFDS). D. Service Availability Discretes The status of various system functions can be reported by means of the Service Availability Discretes available on the ARINC 600 connector. Function SDU System Failed SDU Failed SCM Failed Table 5.2 SDU Serviceability Discretes Steady State Open Pin Allocation Circuit Steady Ground1 MP 15F MP 11F MP 12E MP 12F SDU Powered SDU Not Powered System ok SDU ok System Failed2 SDU Failed3 SCM ok or not installed SCM Failed4 Ext. HPA Failed MP 13E Ext. HPA ok or not installed DLNA Failed MP 13F Antenna Failed MP 14E DLNA ok Antenna ok Ext. HPA Failed DLNA Failed Antenna Failed Ext. BSU Failed MP 14F BSU ok or not installed BSU Failed BUS Failed5 MP 15E All external data buses ok (ARINC 429/AFDX/
RS422) Bus Failed
(ARINC 429/
AFDX/RS422) Sat Link #1 Not available MP 11E Satcom Channel #1 Logged On/Registered Sat Link #2 Not available TP 01K Satcom Channel #2 Logged On/Registered Satcom Channel
#1 Not Logged On/
Not Registered Satcom Channel
#2 Not Logged On/
Not Registered THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 5-8 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series List of Explanatory Notes for Table 5.2:
1. 2. 3. 4. 5. 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. The System Failed discrete Steady Ground state corresponds to one or more LEDs being illuminated red. 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. 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. The Bus Failed discrete provides no indication of activity on the Ethernet buses. E. Service Availability Discrete Lamps The Service Availability Discretes have open circuit and ground states that are capable of driving incandescent lamps connected to an external supply. Typically, each discrete is fed via one or two (in parallel) incandescent lamps to an aircraft 28 Vdc supply. This 28 Vdc supply can be dimmed to approximately 14 Vdc for night time operation. The 28 Vdc is a nominal value and can vary as defined in RTCA/
DO-160E A typical incandescent lamp would be 28Vdc, 20mA. Each Service Availability Discrete is able to continuously sink at least 50mA and be capable of holding a cold inrush current of up to 490mA during the first 10 millisecond of activation as per ARINC 781. F. CFDS/ARINC 604 BITE The SDU reports BITE status and faults to the CFDS using ARINC 429, 350 series words. 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 2 resource, and so on. Faults typically indict a tier 1 resource. An example of tier 1 THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 5-9 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series resource might be ethernet Port1 (there are 4 in total), there also may be a tier 2 resorce that 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 a particular resource is indicted, then it may have a consequential impact on one or more Bits in the 350 words. Refer to ARINC 781 Attachment 2B for a definition of all the 350 words and the definition of each Bit within the words. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 5-10 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series SECTION 6 60000MAINTENANCE PRACTICES 6.1. GENERAL This section provides instructions for the removing, reinstalling and adjusting of the SDU and SCM that has been previously installed by the aircraft manufacturer or completion center. CAUTION: TO AVOID INJURY TO PERSONNEL OR DAMAGE TO EQUIPMENT, ENSURE ADEQUATE PRECAUTIONS ARE TAKEN WHILE PERFORMING ANY WORK IF THE ELECTRICAL POWER IS APPLIED TO THE LRU. CAUTION: TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFT POWER OFF BEFORE REMOVING OR INSTALLING LRU. Field lubrication or other maintenance procedures are not required. The design of the SDU and SCM is such that they do not require field maintenance to maintain airworthiness. If functional problems occur, the SDU Built-in Test Equipment (BITE) capability identifies the faulty LRU. The SDU and SCM maintenance is limited to replacement on verified failure. 6.2. EQUIPMENT AND MATERIALS CAUTION: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS MATERIAL SAFETY DATA SHEETS FOR SAFETY INFORMATION. SOME MATERIALS CAN BE DANGEROUS. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 6-1 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 6.3. PROCEDURE FOR THE SDU CAUTION: THE SDU IS ELECTROSTATIC DISCHARGE SENSITIVE EQUIPMENT. OBSERVE STANDARD ESD PROCEDURES WHEN HANDLING THE EQUIPMENT. A. Removal and Installation Procedure
(1) Remove the SDU a. b. c. Ensure that electrical supply to the SDU is switched off. 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. 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. SDU removal direction Hold Down Clamps Figure 6.1 SDU Removal from ARINC 600 Mounting Tray Tav_e_0000722_00 THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 6-2 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series
(2) Install the SDU a. b. Remove ESD protective cap from the SDU ARINC 600 back connector. 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 CLAMPS ARE FASTENED, AND THAT THE LRU IS SECURELY HELD IN PLACE. SDU installation direction Hold Down Clamps Figure 6.2 SDU Installation on to ARINC 600 Mounting Tray Tav_e_0000721_00 B. Adjustment Procedure Not Applicable. C. Repair Procedure Not Applicable. D. Return to Service Procedures Do the Post-Installation Test Procedures referenced in the Inspection and System Checkout Section of this manual. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 6-3 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 6.4. PROCEDURE FOR THE SCM CAUTION: THE SCM IS ELECTROSTATIC DISCHARGE SENSITIVE EQUIPMENT. OBSERVE STANDARD ESD PROCEDURES WHEN HANDLING THE EQUIPMENT. A. Removal and Installation Procedure
(1) Remove the SCM a. b. Ensure that electrical supply to the SCM is switched off (switch off the SDU). Loosen the two (2) screw locks that secure the 15-pin D Type connector to the SCM. Install an ESD protection cap on the SCM D Type connector. c. Disconnect the D connector. Bag and stow the cable as required. d. 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. Remove the SCM, and visually inspect it for any signs of damage f. Fixing Screws (4 off) Tav_e_0000719_00 Figure 6.3 SCM Removal
(2) Install the SCM a. Remove the ESD protection cap on the D Type connector. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 6-4 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series 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 tool CAUTION: ENSURE THAT THE FIXING SCREWS HAVE BEEN FASTENED, c. AND THAT THE LRU IS SECURELY HELD IN POSITION. 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. Fixing Screw
(1) Screw locks (2) D Type Connector (3) Tav_e_0000720_00 Figure 6.4 SCM Installation B. Adjustment Procedure Not Applicable. C. Repair Procedure Not Applicable. D. Return to Service Procedures Do the Post-Installation Test Procedures referenced in the Inspection and System Checkout Section of this manual. 6.5. CLEANING OF MECHANICAL PARTS CAUTION: MOISTURE AND DIRT CAN CAUSE DAMAGE TO EQUIPMENT Equipment chassis covers give the necessary protection to keep dust away from electronic circuits. If cleaning is required this has to be limited to the removal of particles THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 6-5 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series of dust, oil, grease, condensation, etc and only limited for those equipment accessible parts. Before any cleaning action is carried out ensure that the equipment is disconnected from all electrical power sources, and all the necessary ESD precautions are observed. For dust removal use a cleaning wipe, a silk paintbrush or low-pressure compressed air For removal of finger marks, grease, etc, clean the parts with a cleaning wipe and isopropyl alcohol, exercising care to not damage information labels. b. a. 6.6. PERIODIC CHECKS See Inspection/ Check procedure in Section 4.1. 6.7. CABLING AND CONNECTIONS Periodically check cable connectors (recommended) and if required, remove connector, inspect and re-connect connector to required torque values as specified by the cable manufacture. 6.8. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Maintenance requirements and instructions for continued airworthiness of the TFS SDU and SCM components are contained in the paragraphs that follow. Installation of SDU and SCM on an aircraft by an amendment to the Type Certificate
(TC), Supplemental Type Certificate (STC) or Form 337 obligates the aircraft operator to include the maintenance information supplied by this manual (and listed below) in the operator Aircraft Maintenance Manual and the operator Aircraft Scheduled Maintenance Program. a. Maintenance information for SDU and SCM, TFS LRU (system description, removal, installation, testing, etc.). 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. 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. b. d. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 6-6 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series e. f. g. The SCM equipment is subject to minimal preventative maintenance, which is specific to life limitations associated to the internal USIM cards. For further details refer to your Thales representative. If a system LRU is inoperative remove the specific unit, secure cables and wiring, collar applicable switches and circuit breakers, and placard them inoperative. Revise equipment list and weight and balance as applicable prior to flight and make a log book entry that the unit was removed (refer to section 91.213 of the FAR or the aircraft Minimum Equipment List (MEL)). 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. 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. i. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 6-7 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 6-8 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series SECTION 7 70000COMMISSIONING 7.1. GENERAL The purpose of the following tests is to confirm functionality of the services supported by the SDU and associated equipment, both to confirm the installation has been successful 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, so this 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 the capabilities fitted to the aircraft, as per the following table:
Capability Baseline SDU+SCM
+ Cockpit audio/avionics
+ Wifi AP or wired Ethernet Cabin ISDN
+ GSM Pico cell Table 7.1 Commissioning Tests Applicability F A No Yes B No C No D No E No Yes Yes Yes No No No Yes Yes Yes No No No No No No Yes Yes Yes No No No No No No G No No No Yes No H No No No Yes No I No No No No Yes A. Registration a. b. Power on the AGS (when fitted). Power on the TFS System and wait until the LEDs reach the following state (Refer to Table 7.2):
THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 7-1 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series LED SDU SCM Antenna DLNA FMHPA Ext. BSU Ext. Data Bus ORT/Config. Sat. Link #1 Sat. Link #2 Table 7.2 SDU LEDs SDU - 82155A GREEN GREEN GREEN GREEN SDU - 82155D GREEN GREEN GREEN GREEN OFF(see Note) OFF(see Note) OFF GREEN GREEN GREEN OFF OFF GREEN GREEN GREEN OFF NOTE:
Either:
Or:
c. d. e. Unless an FMHPA is installed, in which case should be GREEN. Connect a laptop to the Test port on the SDU. If an MCDU is present:
i ii iii iv v Enter the Satcom main menu. Both Sat-1 (and Sat-2 if Dual Channel) should be READY. Press Page Down. Select CHANNEL STATUS Sat Modem1 should be in SWIFT BB with status LOGGED ON If the cabin control panel is fitted:
vi If the Service is available LED is lit then the Satcom system is registered. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 7-2 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series B. Classic Packet Data Verification If Cockpit functionality is fitted:
a. Using any MCDU:
Press the Menu key to display the menu page. Select ACARS. i ii iii Via the MAINTENANCE, COMM CONTROL or equivalent ACARS page, verify that Satcom is AVAILABLE. Send and receive several FREE TEXT ACARS messages. Verify correct receipt of all messages. iv v C. Classic Cockpit Voice Calls If Cockpit functionality is fitted:
a. Using any MCDU:
Enter the Satcom main menu. Both Sat-1 (and Sat-2 if Dual Channel) should be READY . i ii 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. In each case, verify correct operation. iv D. SBB Cabin Wifi Data Connectivity (Background Context) If either a Wifi access point or a wired Ethernet to the cabin is fitted:
Start up a laptop (with Wifi capability if Wifi is to be used). Connect to the access point or wired Ethernet. a. b. 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 ii iii iv Type ping www.google.com -n 10 -w 10000. 10 replies should be received. Type ping www.google.com -1 1400 -n 10 -w 10000. 10 replies should be received. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 7-3 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series e. Go to Google homepage and search for a random string to check HTML f. connectivity. Start an FTP client:
i ii iii Connect to the Inmarsat FTP server. Change directory to a test directoryt. Put a file onto a server. The transfer should complete successfully. Get a file from the server. The transfer should complete successfully. Disconnect the FTP client. iv v 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:
Start up a laptop (with Wifi capability if Wifi is to be used). Connect to the access point or wired Ethernet. a. b. c. Open a browser window and follow the instructions to gain access to a guaranteed streaming connection -32k. 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. Open a command window (Start, Run, cmd). i ii iii Check that the traffic generated by this command went via the Type ping www.google.com -n 10 -w 10000. 10 replies should be received. Background context and not the Streaming connection. g. Go to Google homepage and search for a random string to check HTML d. f. h. connectivity. Start an FTP client:
i ii Connect to the Inmarsat FTP server. Change directory to a test directoryt. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 7-4 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series iii iv v vi Put a file onto a server. The transfer should complete successfully. The traffic should have gone via the streaming context and the data rate should have been comparable to the guaranteed rate. Get a file from the server. The transfer should complete successfully. 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. Disconnect the streaming connection. Disconnect from the access point or wired Ethernet. i. j. F. Cabin VoIP service If either a Wifi access point or wired Ethernet to the cabin is fitted:
Ensure that the SDU is powered on and connected. Connect a laptop with headset or VoIP phone to the Cabin Wireless Access Point. a. b. 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. Arrange a call back and hang up. When the phone rings, answer and have a short conversation. Audio quality should be good. ii G. Cabin ISDN Data service If ISDN to the cabin is fitted:
Connect an ISDN modem to the laptop. Connect an ISDN modem to the ISDN port. a. b. c. Dial a suitable ISDN number for a data connection to the internet:
i ii iii The modem should be able to receive the on hook status and dial a number. Arrange a call back and hang up. When the phone rings, answer and have a short conversation. Audio quality should be good. The connection should be set up over Satcom to the number dialed. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 7-5 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series iv v vi vii Type ping www.google.com -n 10 -w 10000. 10 replies should be received. Type ping www.google.com -1 1400 -n 10 -w 10000. 10 replies should be received. d. Go to the Google homepage and search for a random string to check e. HTML connectivity. Start an FTP client:
i ii iii Connect to the Inmarsat FTP server. Change directory to a test directoryt. Put a file onto a server. The transfer should complete successfully. The data rate should have been comparable to the expected 64kbit rate. Get a file from the server. The transfer should complete successfully. The data rate should have been comparable to the expected 64kbit rate. iv v vi vii Disconnect the FTP client. Disconnect the ISDN connection. f. H. Cabin ISDN Voice service If ISDN to the cabin is fitted:
Connect an ISDN phone to the ISDN port. a. 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. The connection should be set up over Satcom to the number dialed. ii 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. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 7-6 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series vii Hang up. Cabin GSM Call and SMS Service I. If a GSM Pico cell is fitted:
a. b. c. Ensure that the AGS is powered on and the call disable is off. Ensure that the SDU is powered on and connected. 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. iv iii Arrange a call back and hang up. when the phone rings, answer and have a short conversation. Audio quality should be good. Send an SMS message to a remote GSM phone, asking for a reply. The text message should reach recipient. The SMS reply should be received. Switch on the call disable. v vi 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. THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 7-7 Jun 30/2008 Installation Maintenance Manual SDU 82155 Series SCM 82158 Series THIS PAGE INTENTIONALLY BLANK THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the companys prior written approval 7-8 Jun 30/2008
| frequency | equipment class | purpose | ||
|---|---|---|---|---|
| 1 | 2009-02-20 | 1626.5 ~ 1660.5 | TNB - Licensed Non-Broadcast Station Transmitter | Original Equipment |
| app s | Applicant Information | |||||
|---|---|---|---|---|---|---|
| 1 | Effective |
2009-02-20
|
||||
| 1 | Applicant's complete, legal business name |
Thales Avionics Limited
|
||||
| 1 | FCC Registration Number (FRN) |
0016284283
|
||||
| 1 | Physical Address |
86 Bushey Road
|
||||
| 1 |
London, N/A SW20 0JW
|
|||||
| 1 |
United Kingdom
|
|||||
| app s | TCB Information | |||||
| n/a | ||||||
| app s | FCC ID | |||||
| 1 | Grantee Code |
KV6
|
||||
| 1 | Equipment Product Code |
TFS-SDU82155A1
|
||||
| app s | Person at the applicant's address to receive grant or for contact | |||||
| 1 | Name |
I******** F******
|
||||
| 1 | Title |
Mr
|
||||
| 1 | Telephone Number |
44208********
|
||||
| 1 | Fax Number |
44208********
|
||||
| 1 |
i******@uk.thalesgroup.com
|
|||||
| app s | Technical Contact | |||||
| 1 | Firm Name |
Thales
|
||||
| 1 | Name |
P******** G****
|
||||
| 1 | Physical Address |
86 Bushey Road
|
||||
| 1 |
London, SW19 0JW
|
|||||
| 1 |
United Kingdom
|
|||||
| 1 |
P******@uk.thalesgroup.com
|
|||||
| app s | Non Technical Contact | |||||
| 1 | Firm Name |
Thales Avionics
|
||||
| 1 | Name |
J****** L******
|
||||
| 1 | Physical Address |
86 Bushey Road
|
||||
| 1 |
London, SW19 0JW
|
|||||
| 1 |
United Kingdom
|
|||||
| 1 |
j******@uk.thalesgroup.com
|
|||||
| app s | Confidentiality (long or short term) | |||||
| 1 | Does this application include a request for confidentiality for any portion(s) of the data contained in this application pursuant to 47 CFR § 0.459 of the Commission Rules?: | Yes | ||||
| 1 | Long-Term Confidentiality Does this application include a request for confidentiality for any portion(s) of the data contained in this application pursuant to 47 CFR § 0.459 of the Commission Rules?: | No | ||||
| if no date is supplied, the release date will be set to 45 calendar days past the date of grant. | ||||||
| app s | Cognitive Radio & Software Defined Radio, Class, etc | |||||
| 1 | Is this application for software defined/cognitive radio authorization? | Yes | ||||
| 1 | Equipment Class | TNB - Licensed Non-Broadcast Station Transmitter | ||||
| 1 | Description of product as it is marketed: (NOTE: This text will appear below the equipment class on the grant) | Topflight SATCOM Satellite Data unit | ||||
| 1 | Related OET KnowledgeDataBase Inquiry: Is there a KDB inquiry associated with this application? | No | ||||
| 1 | Modular Equipment Type | Does not apply | ||||
| 1 | Purpose / Application is for | Original Equipment | ||||
| 1 | Composite Equipment: Is the equipment in this application a composite device subject to an additional equipment authorization? | No | ||||
| 1 | Related Equipment: Is the equipment in this application part of a system that operates with, or is marketed with, another device that requires an equipment authorization? | No | ||||
| 1 | Grant Comments | 16-QAM | ||||
| 1 | Is there an equipment authorization waiver associated with this application? | Yes | ||||
| 1 | If there is an equipment authorization waiver associated with this application, has the associated waiver been approved and all information uploaded? | Yes | ||||
| app s | Test Firm Name and Contact Information | |||||
| 1 | Firm Name |
TUV SUD Product Service
|
||||
| 1 | Name |
M**** J****
|
||||
| 1 | Telephone Number |
00-44********
|
||||
| 1 | Fax Number |
00-44********
|
||||
| 1 |
m******@tuv-sud.co.uk
|
|||||
| Equipment Specifications | |||||||||||||||||||||||||||||||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Line | Rule Parts | Grant Notes | Lower Frequency | Upper Frequency | Power Output | Tolerance | Emission Designator | Microprocessor Number | |||||||||||||||||||||||||||||||||
| 1 | 1 | 87 | 1626.5 | 1660.5 | 21 | 160 Hz | 25K0G1W | ||||||||||||||||||||||||||||||||||
| 1 | 2 | 87 | 1626.5 | 1660.5 | 21 | 160 Hz | 50K0G1W | ||||||||||||||||||||||||||||||||||
| 1 | 3 | 87 | 1626.5 | 1660.5 | 21 | 160 Hz | 100KG1W | ||||||||||||||||||||||||||||||||||
| 1 | 4 | 87 | 1626.5 | 1660.5 | 21 | 160 Hz | 200KG1W | ||||||||||||||||||||||||||||||||||
| 1 | 5 | 87 | 1626.5 | 1660.5 | 21 | 160 Hz | 50K0D1W | ||||||||||||||||||||||||||||||||||
| 1 | 6 | 87 | 1626.5 | 1660.5 | 21 | 160 Hz | 100KD1W | ||||||||||||||||||||||||||||||||||
| 1 | 7 | 87 | 1626.5 | 1660.5 | 21 | 160 Hz | 200KD1W | ||||||||||||||||||||||||||||||||||
some individual PII (Personally Identifiable Information) available on the public forms may be redacted, original source may include additional details
This product uses the FCC Data API but is not endorsed or certified by the FCC