Thales Avionics TFS-HPA82166A Topflight Flange Mount High Power Amplifier User Manual Tpage ATA

Thales Avionics Limited Topflight Flange Mount High Power Amplifier Tpage ATA

FMHPA IM manual

86, Bushey RoadRaynes Park, LondonSW20 0JWTel: +44 (0)20 8946 8011Fax: +44 (0)20 8946 75301Jul 2008Revision No. 00First Issue: Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval INSTALLATION AND MAINTENANCE MANUALFlange Mounted High Power Amplifier (FMHPA)82166 Series
Installation Maintenance ManualFMHPA 82166A302Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualFMHPA 82166iJul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Section 1 INTRODUCTION Page1.1. Purpose of Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11.2. Scope of Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21.3. Reference documents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21.4. Compliance to Regulations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2A. Federal Communication Commission . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2B. European Aviation Safety Agency. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3Section 2 DESCRIPTION Page2.1. FMHPA SYSTEM General Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1A. Hardware. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1(1) RF SRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1(2) Logic SRU. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2B. Software . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2C. General Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3(1) Functional Modes: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3D. HPA Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4E. PSM and CM Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4(1) PSM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5(2) CM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5F. Operating Environment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6(1) Normal operating temperature:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6(2) Cooling:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6(3) Heat dissipation: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6G. Environment Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7H. Weight and Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7I. FMHPA Performances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-112.2. Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11A. Aircraft Power Utility Service. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11B. Communication Interface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-122.3. FMHPA Interconnect Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12A. FMHPA Interconnection Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12B. FMHPA Connectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12(1) FMHPA Connectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12(2) Connector Designation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13(3) Connector J1 PIN Out. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13Section 3 INSTALLATION GUIDELINES Page3.1. Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13.2. Interchangeability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-13.3. FMHPA Location and Accessibility Guidelines . . . . . . . . . . . . . . . . . . . . . . . . . 3-13.4. Cooling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-23.5. Power Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-23.6. Bonding Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3
Installation Maintenance ManualFMHPA 82166iiJul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Section 4 INSPECTION AND SYSTEM CHECKOUT Page4.1. Inspection/Check Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1A. Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1B. FMHPA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-14.2. System checkout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-2A. Post-Installation Test. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-2Section 5 FAULT ISOLATION Page5.1. Bite Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-15.2. BITE Test. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1A. Self Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1B. Health Monitor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-25.3. SDU LED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2Section 6 MAINTENANCE Practices Page6.1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-16.2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-16.3. Procedure for the FMHPA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2A. Removal and Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2(1) Remove the FMHPA as follows: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2(2) Install the FMHPA as follows: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2B. Adjustment Procedure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4C. Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4D. Return to Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-46.4. Cleaning of Mechanical Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-56.5. Periodic Checks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-56.6. Cabling and Connections. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-56.7. Instructions for Continued Airworthiness . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-5
Installation Maintenance ManualFMHPA 82166iiiJul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval RECORD OF REVISIONSRevision No:Revision DateDate InsertedBy Revision No:Revision DateDate InsertedBy
Installation Maintenance ManualFMHPA 82166ivJul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualFMHPA 821661-1Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 110000INTRODUCTION1.1. PURPOSE OF MANUALThis manual sets forth installation and maintenance guidelines for the THALESTopFlight Satcom (TFS) Flange-mounted High Power Amplifier (FMHPA). TheFMHPA installation specific and general guidelines contained within this manual aresupported by mechanical and electrical interconnection drawings. Drawings should bereviewed by the installation organisation, and any requirements specific to a particularairframe should be assessed before installation is commenced.The Manual covers the following topics:a. Title Page.b. Table of Content.c. Record of Revisionsd. Introduction.e. Description.f. Installation Guidelines.g. Inspection and System Checkout.h. Fault Isolation.i. Maintenance Practices.NOTE: This manual does not cover aircraft system commissioning testprocedures.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.
Installation Maintenance ManualFMHPA 821661-2Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval For any queries related to information contained within this Manual contact thefollowing: THALES TFS Project Manager86 Bushey RoadRaynes Park, LondonSW20 0JW, UKTel. +44 (0)20 8946 8011Fax. +44 (0)20 8946 75301.2. SCOPE OF MANUALThe Thales FMHPA comply with the design requirements set forward in the ARINC 781Characteristic. An ARINC 781 compliant system is intended to support one or more ofthe Inmarsat aeronautical services known as ‘Classic-Aero’, ‘Swift 64’, and‘SwiftBroadband’.This manual provides information specific for the FMHPA.1.3. REFERENCE DOCUMENTSThe following publications provide additional useful information:Table 1.1 Reference Documents1.4. COMPLIANCE TO REGULATIONSA. Federal Communication CommissionThe FMHPA is designed to be compliant with part 15 and part 87 of the FederalCommunication Commission (FCC) regulationsTHALES FMHPA Component Maintenance ManualTHALES SDU Component Maintenance Manual Airbus:44-35-32 Boeing: TBDEMS AMT-3800 High Gain Antenna Subsystem Installation Manual MN-1242-20047Mark 33 Digital Information Transfer System ARINC 429Air Transport Avionics Equipment Interfaces ARINC 600Mark III Aviation Satellite Communication (Satcom) System AvionicsARINC 781
Installation Maintenance ManualFMHPA 821661-3Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval B. European Aviation Safety AgencyThe installation must be compliant to the following European Aviation Safety Agency(EASA) regulations:• EASA/FAR 25.869 Fire protection systems• EASA 25X0899 Electrical bonding and protection against lightning and static electricity• EASA/FAR 25.1301 Equipment, general, function and installation• EASA/FAR 25.1309 Equipment, systems and installations• EASA 25X1316 System lightning protection• EASA/FAR 25.1353 Electrical equipment and installations• EASA/FAR 25.1357 Circuit protective devices• EASA 25X1360 Precautions against injury• EASA/FAR 25.1431 Electronic equipment• EASA 25.561 Emergency Landing.
Installation Maintenance ManualFMHPA 821661-4Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualFMHPA 821662-1Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 220000DESCRIPTION2.1. FMHPA SYSTEM GENERAL DESCRIPTIONThe FMHPA forms part of the airborne SATCOM system, used in conjunction with aSatellite Data Unit (SDU), a Diplexer/Low Noise Amplifier (DLNA) and a High GainAntenna (HGA) conforming to ARINC 781, with an internal Beam Steering Unit (BSU).The TopFlight Satcom (TFS) system conforms to the Aeronautical Radio Incorporated(ARINC) 781 Characteristic, and interfaces with onboard avionics and communicationequipment to provide the aircraft with a range of communication services bytransmitting and receiving L Band signals to and from the fourth generation ofINMARSAT satellites. For this purpose the INMARSAT satellite constellation isconnected to the ground backbone telecommunication network through Satellite AccessStations (SAS) operated by service providers.A. HardwareThe FMHPA contains two hardware Shop Replaceable Units (SRU):• The Radio Frequency (RF) SRU which contains the High Power Amplifier (HPA) and the RF Filter• The Logic SRU which contains the Power Supply Module (PSM) and the Communication Module (CM).The two SRUs have a heat-skin with cooling fins and a nozzle to dissipate thetemperature.(1) RF SRUThe RF SRU has two external connectors and two internal connectors:a. External connectors:• RF input (J2)• RF output (J3).b. Internal connectors, connecting the RF SRU to the Logic SRU:• Power Supplies• Communication signal.
Installation Maintenance ManualFMHPA 821662-2Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval (2) Logic SRUThe Logic SRU has one external connector and six internal connectors:a. External connector:The external connector (J1) is used to communicate with the SDU and for the powersupplies of the FMHPA.b. Internal connectors are used to:• Connect the PSM and the CM• Connect the RF SRU to the Logic SRU for power supplies and the communication signal.• Supply a test connector for testing and downloading.B. SoftwareThere is no software in the FMHPA.All FMHPA functions shall be allocated to hardware.Figure 2.1 FMHPA Internal Organisation.HPAPower Supply ConvertersCommand/StatusPowerSuppliesCommunication ModulePSM115VacARINC 429 I/O(J1)Test and MaintainabilityEMC FilterRF In (J2)RF Out (J3)AirflowTav_e_0000761_00RFFILTERSRU1:HPA+RF FilterSRU2:PSM+CM
Installation Maintenance ManualFMHPA 821662-3Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval C. General OperationThe FMHPA is a Linear Power Amplifier for embedded communication system (TFS).FMHPA supplies up to 35W RF power to the Aircraft Satcom antenna when the physicalseparation of the SDU and the antenna is such that the RF loss between the SDU and theantenna will be greater than that allowed in ARINC 781. Alternatively, the FMHPA maybe used in cases where more power is required than would be available from the HPAwithin the SDU, to provide the services offered.Its function is to amplify the modulated signals supplied by the SDU. The number ofsignals to be amplified depends on the communication traffic, from a single up to themaximum capability of the SDU. FMHPA also includes a constant and programmableRF gain, a high grade of self test (90% of failures are detected) and a high temperatureprotection function.(1) Functional Modes:The FMHPA operates in the following five modes:a. Nominal Mode (35W output)Nominal Mode (NM) is defined as the operating condition when power supplies areapplied. This mode is enabled by default at powerup, the power supply is defined at itsnominal Voltage (around +27V)b. Low Power mode (9W output)Low Power Mode is defined as the operating condition which can be enabled by SDU(or FMHPA in security case) when the temperature is high and in order to reduce thedissipated power (for example to save the internal temperature when there is a loss ofcooling). For this mode, the power supply is changed from Nominal Voltage (around+27V) to Low Voltage (around +17V). Cockpit only services available.With NM and LPM modes, the main characteristic of the modes is to maintain a constantgain whatever the temperature.c. Carriers Off/MUTE ModeThis mode switches off the RF gain, and puts the FMHPA in Standby (STBY) mode.d. STBY / On modeWith Standby mode, the main characteristic of the mode is to have the lowestconsumption.In this mode, the RF output power equals zero, and the thermal dissipation within theFMHPA is reduced to the minimum possible to permit temperature monitoring and
Installation Maintenance ManualFMHPA 821662-4Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval communication with the SDU to continue. This STBY mode can be obtained with fourconfigurations:• Command configuration: In this case, an input command, Carriers Off/Mute command from SDU, enable or disable the STBY mode• Auto-protection configuration: When FMHPA detect an internal failure (High level) and the SDU doesn’t answer within 2 seconds• With carriers Off/Mute, the main characteristic of the mode is to have a high isolation between FMHPA input and FMHPA output• After HPA Power-On Self Test (POST) or at the end of a self test.e. BITE MonitoringA monitoring Mode is defined in order to check if the FMHPA Status is OK or FAIL.A self test is carried out at Start-up and on request from the SDU.D. HPA ModuleThe HPA function is to amplify modulated signals from the SDU, up to 35 W.The HPA includes an amplification chain, a digital part for control and communicationand a RF filter.The output RF filter is a mechanical filter, without any electronic component, with a Nconnector output.E. PSM and CM ModuleThe PSM and CM SRU module contains two modules in the same housing:• Power Supply Module• Communication Module.
Installation Maintenance ManualFMHPA 821662-5Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval (1) PSM(2) CMIts function is to manage the interface with the ARINC 429, to send control signals to theHPA and the PSM and report FMHPA status.Figure 2.2 Power Supply ModuleJ1Lightening/EMCprotectionIsolated AC/DC350W PFCHold upcapacitors200ms forDigital partDC/DC HPAHL/LV voltage300WDC/DC+5,1V - 30WHPACMJ9J5DC/DC-15V - 1.5W+15V - 1.5W+5V - 0.1W+5.1V - 2.5WTemperaturesensorsVoltagesupervisionPower cutmanagementOutputdiscrets ControlsignalsNominal/LowVoltageselectionPSMP115VACN115VACARINC 429 InARINC 429Out33VDCJ6J8J7Tav_e_0000767_00
Installation Maintenance ManualFMHPA 821662-6Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval F. Operating Environment(1) Normal operating temperature:Between -15o C (5o F) and +70o C (158o F)(2) Cooling:Forced air type requiring Normal airflow rate of 2.6 lb/min (72 kg/hr). Nominal Mode(NM) inlet temperature +60o C (140o F) and Low Power Mode (LPM) inlet temperatureof +70o C (158o F).(3) Heat dissipation:265 W (assuming 100% duty cycles with HPA operating at 35 W output).Figure 2.3 Communiction ModuleInput LRUConnectorCommunication ModuleHPAPSMTest ConnectorTav_e_0000768_00A429 HighspeedA429 Lowspeed
Installation Maintenance ManualFMHPA 821662-7Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval G. Environment ConditionsThe FMHPA complies with the RTCA/DO-160. The environmental qualificationscategories complied with, are as per listed refer (Table 2.1).Table 2.1 Environmental Test categories for SDU and SCMH. Weight and DimensionsWeight and dimensions of the FMHPA are as follows:NOTE: Weights and measurements in this manual use both U.S (inches) and S.I.(metric: mm) values.Maximum Weight: 8.9 kg (19.8 lb)RTCA DO-160 Environmental CategoriesSection Condition Category4.0 Temperature/Altitude A25.0 Temp Var B6.0 Humidity A7.0 Shock/Crash E8.0 Vibration RVibration Curve C or C115.0 Magnetic Effect A16.0 Power Input AHarmonics H17.0 Voltage Spike A18.0 Conducted Audio Susceptibility K(CF), K(NF), K(WF)19.0 Induced Signal Susceptibility CC20.0 RF Susceptibility T21.0 RF Emissions T
Installation Maintenance ManualFMHPA 821662-8Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualFMHPA 821662-9Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.1 FMHPA Overall DimensionsR3.27 MAXI(0.13”) 50.9 MAXI(2”)54.61 MAXI(2.15”)R1.87 MAXI(0.07”)45.8 +/- 0.4(1.8) 6.35(0.25”)14 +/-0.5(0.551” +/-0.2”)85.4 +/-2(3.362” +/-0.079”)277 MAXI(10.906”)237 MAXI(9.331”)TOP118.5 +/-2(4.665” +/-0/079”)18 MINI(0.709”) 65 MAXI(2.559”)136.5 MAXI(5.374”)158 MAXI(6.22”)BOTTOM159 MAXI(6.26”)Drawn Air Flow284.2(11.189”)279.5 MAXI(11.004”)19.5 MINI(0.768”)59 MAXI(2.323”)16 MAXI(0.63”)79(3.11”)150(5.91”)30(1.18”)CENTER OF GRAVITY30 MAXI(1.181”)8 MINI(0.315”)13.5 MAXI(0.531”) 36 MAXI(1.417”)INTERFACE PC BOARD120 MAXI(4.724”)328.5 MAXI(12.933”)299 MAXI(11.772”) 279 MINI(10.984”)HPAPOWER SUPPLY70(2.76”)0.5 MINI(0.0197”)6.75 +/-).1(0.266” +/-0.004”)30 MINI(1.181”)162.58(6.4”)39 +/-10(1.54” +/-0.39”)5 +/-10(0.2” +/-0.39”)J2RF IN (50 ohms)INTERFACE SERIES TNC SOCKET CONTACT J3RF OUT (50 ohms)INTERFACE SERIES N SOCKETCONTACT116.8(4.598”)39.5(1.56”) DRAWN AIR FLOW AREA121.3(4.776”)54.25(2.136”)80 MAXI(3.15”)37.5(1.476”)MAJOR KEYJ155 MAXI(2.165”)56 MINI(2.2”)160(4.59”)NOTE: MAXIMUM PERMISSIBLE TIGHTENING TORQUE OF ATTACHMENT SCREWS = 5.3 N.m (3.9 lbf.ft)
Installation Maintenance ManualFMHPA 821662-10Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualFMHPA 821662-11Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval I. FMHPA Performances• Supply voltage: 100 to 122 Vrms, ac, Frequency Range 360 to 800 Hz• Power consumption: - 300 VA in NM mode- 150 VA in LPM- 50 VA in STBY mode.• RF Frequency: 1626.5 MHz to 1660.5 MHz• RF Power Rating: 35W for continuous operation• RF Gain adjustable in NM and LPM: 0.5 dB increments up to 15.5 dB dynamic.2.2. INTERFACESThe FMHPA interfaces are as follows:A. Aircraft Power Utility ServiceThe FMHPA interfaces with the aircraft primary power generator (refer Figure 2.5).Figure 2.5 FMHPA Power Distribution DiagramSDUAircraftPowersupply115 Vac Cold115 Vac HotChassis Ground115 Vac-7.5 AMP Circuit Breaker BP01BP05BP03Power Source 12 VDC SCM Power ReturnTav_e_0000766_00FMHPAXYJ
Installation Maintenance ManualFMHPA 821662-12Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval B. Communication InterfaceThe communication interfaces includes 2 ARINC 429 serial bus. One is an input at highspeed (100 kilobits/s) and the other is an output at low speed (12.5 kilobits/s).Table 2.2 ARINC 429 Nav Data Labels - Hybrid2.3. FMHPA INTERCONNECT DATAA. FMHPA Interconnection DiagramThe FMHPA interconnection diagrams (refer to Figure 2.6) illustrate all the necessaryconnections between the FMHPA and all the other interfaced equipment.B. FMHPA ConnectorsThe FMHPA has three external connectors and five internal connectors:(1) FMHPA ConnectorsTable 2.3 FMHPA ConnectorsPARAMETERS ARINC 429 LABELSFMHPA Command word (SDU to FMHPA) 143FMHPA Command Summary word (SDU to FMHPA) 227FMHPA Status word (FMHPA to SDU) 143FMHPA Maintenance word (FMHPA to SDU) 350FMHPA Additional Information word (FMHPA to SDU)356Name Function External InternalJ1 Power Supply and ARINC 429 bus XJ2 RF Input XJ3 RF Output XJ4 Test/Maintenance XJ5 Connection between CM and J9 XJ6 Connection between CM and PSM XJ7/P7 Connection between PSM and HPA XJ8 Connection between the PSM (EMC filter) and CMX
Installation Maintenance ManualFMHPA 821662-13Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval (2) Connector DesignationTable 2.4 Designation(3) Connector J1 PIN OutTable 2.5 PIN Out Connector J1J9 Connection between J5 and HPA XDesignation RequirementAccessibility of connectors J1,J2 and J3 Accessible from outsideTest connector (J4) Concealed behind an access dooorType of Power/Control connector (J1) MIL-C-38999 Series III Insert Arrange-ment 17-26Type of RF Input connector (J3) TNC FemaleType of RF Output connector (J3) N Type FemalePIN OUT of J1 See Table 2.5PIN No: Signal DescriptionA FMHPA BITE A ARINC 429 from FMHPAB FMHPA BITE B ARINC 429 from FMHPAC RS422 RXD A - Not Used Serial data to FMHPA +D RS422 RXD B- Not Used Serial data to FMHPA -E RS422 TXD A - Not Used Serial data from FMHPA +F RS422 TXD B- Not Used Serial data from FMHPA -GSPARE SPAREHSPARE SPAREJ Chassis Ground Chassis GroundKSPARE SPARELSPARE SPAREM Discrete BITE #1 - Not Used Discrete BITE #1 - Not UsedN Discrete BITE #2 - Not Used Discrete BITE #2 - Not UsedName Function External Internal
Installation Maintenance ManualFMHPA 821662-14Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval P Antenna control A ARINC 429 to FMHPAR Antenna control B ARINC 429 to FMHPAS Antenna control Shield SHLD for ARINC 429T FMHPA BITE Shield SHLD for ARINC 429U RS422 Shield (TBC) - Not Used RS422 ShieldVSPARE SPAREWSPARE SPAREX 115Vac Hot Aircraft AC powerY 115Vac Return Aircraft AC powerZSPARE SPAREa Discrete BITE #3 - Not Used Discrete BITE #3 - Not Usedb ATE Pin - Not Used Manufacturer specificcSPARE SPAREPIN No: Signal Description
Installation Maintenance ManualFMHPA 821662-15Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval Figure 2.4 FMHPA Interconnection Block Diagram SDUAntennaDLNAAntenna PortDLNA BITEBHDLNA Control911TP71SDU RF Output to FMHPASDU RF Input from DLNABP07AircraftPowerSupplyBP01BP05BP03115 Vac Cold115 Vac HotChassis Ground115V AC - 7.5 AMPCircuitBreaker 1918EF115 Vac Cold115 Vac HotJ10DLNA BITE Return3568MP08CMP08DBITE Input Top/Port BSU/Ant (B)BITE Input Top/Port BSU/Ant (A)Multi-Control Output (B)Multi-Control Output (A)MP01EMP01F74(Note 1)22ATX PortFMHPATX PortHPA RF Outputto DLNA(Note1) J2J3MP02EMP02FJ1-YJ1-XJ1-JJ1-AJ1-BJ1-PJ1-RJ1-TJ1-SBITE Input from HPA (A)BITE Input from HPA (B)TP03DTP03EConfig Pin 1Config Pin 2(Note 2)Tav_e_0000765_00RF Cable Losses RF Loss SDU to FMHPA Loss 8 to 18 dB D/LNA to Antenna Loss < 0.3 dB D/LNA to SDU < 6 dB Loss < 25 dB Note 1:Loss FMHPAToD/LNA < 1.4 dB (Note1) Note 2: Configuration link must be removed(Note1)
Installation Maintenance ManualFMHPA 821662-16Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualFMHPA 821663-1Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 330000INSTALLATION GUIDELINES3.1. INTRODUCTIONThe FMHPA should be installed in the aircraft in a manner consistent with acceptableworkmanship and engineering practices, and in accordance with the instructions setforth in this manual. To ensure that the system has been properly and safely installed in the aircraft theinstaller should make a through visual inspection and conduct an overall operationalcheck of the system on the ground prior to commissioning to the Customer and or aflight. NOTE: Before installing any components or cabling, read all notes containedwithin drawings.3.2. INTERCHANGEABILITYThe FMHPA will only operate when installed with a Thales SDU. Therefore, theFMHPA are interchangeable only with identical system components as covered in thismanual.The FMHPA and SDU are a Functional Doublet. This means that the interwiring and pinout definitions are interchangeable, but due to unique protocol implementations, thesupply and acquisition of these units are manufacturer specific. 3.3. FMHPA LOCATION AND ACCESSIBILITY GUIDELINESCAUTION: BEFORE EQUIPMENT INSTALLATION ENSURE THAT THEAIRCRAFT POWER SUPPLY TO THE SDU CIRCUIT BREAKERIS POSITIONED IN THE OFF CONDITION.The FMHPA will be installed in an RTCA DO160 Category A2 location on an aircraftwith forced air-cooling.The FMHPA must be installed in a pressurized and partially temperature controlledzone. The FMHPA requires external forced air-cooling.The FMHPA must have a minimum amount of free space around it, to facilitateconvective cooling in the absence of forced air cooling (refer Figure 3.1). As a guideline1” spacing in every direction.
Installation Maintenance ManualFMHPA 821663-2Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval A minimum gap of 0.5” is required from the bottom of the insulation blanket to the upperside of the FMHPA.3.4. COOLINGThe FMHPA is designed in accordance with ARINC 781, requiring Normal airflow rateof 2.6 lb/min (72 kg/hr). Nominal Mode (NM) inlet temperature +60o C (140o F) andLow Power Mode (LPM) inlet temperature of +70o C (158o F) . The cooling air willenter the equipment chassis at the front and drawn though from the rear forced aircooling.3.5. POWER REQUIREMENTSIt is the responsibility of the installer to select the appropriate gauge of wire for powerconnections, and to ensure that the required safety and voltage drop requirements arecomplied with.For FMHPA power supply specifications refer to:a. Paragraph 2.1.: FMHPA Performancesb. Figure 2.5: Aircraft Power Distributionc. Figures 2.6: FMHPA Interconnection Diagram.Figure 3.1 Typical FMHPA Installation162.56(6.4”)235.46(9.27”)145.22(5.72”)12.7 (0.5”)Minimum Distance from bottom ofInsulation Blanket to upper side of FMHPA149.9(5.90”)0139.7(5.50”)349(13.74”)26144.5(1.75”)188.8(7.43”)Tav_e_0000769_00
Installation Maintenance ManualFMHPA 821663-3Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 3.6. BONDING REQUIREMENTSThe bonding of all LRUs to the airframe must not exceed 20 milliohms. However someaircraft manufacturers or design/installation organisation may require a lower value thanthe recommended 20 milliohms.
Installation Maintenance ManualFMHPA 821663-4Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualFMHPA 821664-1Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 440000INSPECTION AND SYSTEM CHECKOUT4.1. INSPECTION/CHECK PROCEDUREThe visual check procedures that follow should be performed during or after the FMHPAinstallation, or as a periodic maintenance inspection check of the installation:A. Wiringa. Ensure that a continuity check of all the installation wiring harness had been carried out, and that all the sources are correctly rated on the correct pins.b. Check that none of the cables have been damaged, and cannot be damaged by components that are installed later.c. Clean Co-axial connections with isopropyl alcohol and torque tighten to connector manufacturers recommendations. d. Verify that the various RF cables are within their minimum radius of curvature tolerances.e. Check that the cable runs are spaced away from any moving or hot part that could damage cables when in use.B. FMHPAa. Examine the assembly for external condition (absences of fractures, dents, deformations, cracks, and/or any other abnormal damage).b. Check that the unit is properly installed and that screws are firmly tightened.c. Check screws and nuts general condition.d. Check that the contact resistance between the FMHPA and a point on the aircraft structure close to the component does not exceed 20 milliohms.e. Check that the correct air cooling and air flow is provided to the FMHPA.
Installation Maintenance ManualFMHPA 821664-2Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 4.2. SYSTEM CHECKOUTAt this stage of the installation it is assumed that a continuity check of the wiring hasbeen made, a visual check of the installation harness has been performed, and that theinspection/check procedure has been carried out.A. Post-Installation TestWARNING: THE RF POWER RADIATED BY THE TFS SYSTEM ANTENNACAN CAUSE BODILY HARM. DURING SATCOM OPERATIONTHE SAFETY DISTANCE FROM THE ANTENNA MUST BE NOLESS THAN 3.5M OR 12 FEET. SINCE THERE ARE VARIOUSPOSSIBLE ANTENNA LOCATIONS, IT IS THERESPONSIBILITY OF THE OPERATOR TO DETERMINE THEAREA OF HAZARD FOR THEIR TFS SYSTEMCONFIGURATION AND TO TRAIN PERSONNEL IN GROUNDSAFETY PROCEDURES.WARNING: DURING ANTENNA OPERATION (TRANSMISSION), MAKESURE PERSONNEL ARE NOT EXPOSED TO ANYREFLECTED, SCATTERED, OR DIRECT BEAMS. ENSUREPERSONNEL ARE OUTSIDE THE MINIMUM DISTANCESPECIFIED.CAUTION: WHEN TESTING THE COMPLETE TFS SYSTEM (ANTENNASYSTEM INCLUDED) REFER TO THE APPLICABLE ANTENNAIMM FOR FURTHER SAFETY REQUIREMENTS ANDSPECIFICATIONS. THE SDU MUST NOT BE POWEREDWITHOUT AN ANTENNA OR SUITABLE LOAD CONNECTEDON THE HIGH POWER TRANSMIT OUTPUT PORT.CAUTION: NEVER CONNECT OR DISCONNECT A SATCOM LRU WHENPOWER IS APPLIED.CAUTION: NEVER APPLY HIGH-LEVEL RF SIGNAL TO A POWERED-DOWN LRU.CAUTION: NEVER DISCONNECT RF CABLES WHEN SYSTEMOPERATING.
Installation Maintenance ManualFMHPA 821664-3Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval CAUTION: NEVER POWER-UP ANY LRU UNTIL ALL CONNECTIONS INTHE SYSTEM ARE MADE.CAUTION: ENSURE THAT THE APPROPRIATE ORT SOFTWARE ISINSTALLED IN THE SCM AND/OR SDU BEFORE PERFORMINGSYSTEM OPERATIONS.This test requires that all the Satcom system LRUs (SDU, SCM, FMHPA, DLNA,Antenna and cables) be connected and operating properly, with a means of displayingany system faults detected by the LRU during the Built-In Test Equipment (BITE) test.The results of the test are indicated on the SDU front panel LED. If no system faults are indicated by the BITE test, then the subsystem installation shouldbe considered acceptable. If any subsystem LRU fails the test, it must be returned to thevendor (refer to your vendor customer support).Refer to the Testing and Fault Isolation section for information on the FMHPA faultdetection capabilities.
Installation Maintenance ManualFMHPA 821664-4Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval THIS PAGE INTENTIONALLY BLANK
Installation Maintenance ManualFMHPA 821665-1Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 550000FAULT ISOLATION5.1. BITE FUNCTIONThe FMHPA include :• A Monitoring mode is defined in order to check if the FMHPA status is OK or FAIL• A self test is carried out at start up and on request of SDU.BITE/Monitoring function is available from the ARINC 429 serial output bus whileoperating in any of the “RF operational modes” of NM, LPM, Carriers Off/Mute, STBYmode. FMHPA BITE/Monitoring status is requested from the ARINC 429 serial inputbus. The FMHPA will continously monitor its internal health and in the event of a detectedfailure will report this to the SDU through the serial interface. Such monitoring does notinterrupt normal operations.The FMHPA is equipped with an internal power detector able to provide measurementof the following:• The RF Output power• The RF reflected power (used to detect antenna failure/ mismatch)• The RF Input sensor.A number of temperature sensors are located within the FMHPA enclosure atappropriate locations in support of BITE.5.2. BITE TESTAny failure of the BITE monitoring circuitry will not directly degrade the operationalFMHPA performance.A. Self TestThe FMHPA will perform a self test function after power-on, and on reciept of therelevant command from the SDU via the ARINC 429 interface.
Installation Maintenance ManualFMHPA 821665-2Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval B. Health MonitorThe FMHPA will continuously monitor its internal serviceability and in the event of adetected failure will report this to the SDU via the ARINC 429 status word.5.3. SDU LEDThe FMHPA also displays serviceabilty via the SDU front panel Ext HPA LED (refer tothe SDU/SCM IMM).
Installation Maintenance ManualFMHPA 821666-1Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval SECTION 660000MAINTENANCE PRACTICES6.1. GENERALThis section provides instructions for the removing, reinstalling and adjusting of theFMHPA that has been previously installed by the aircraft manufacturer or completioncenter.CAUTION: TO AVOID INJURY TO PERSONNEL OR DAMAGE TOEQUIPMENT, ENSURE ADEQUATE PRECAUTIONS ARETAKEN WHILE PERFORMING ANY WORK IF THE ELECTRICALPOWER IS APPLIED TO THE LRU.CAUTION: TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFTPOWER OFF INCLUDING SDU BEFORE REMOVING ORINSTALLING FMHPA.Field lubrication or other maintenance procedures are not required. The design of theFMHPA is such that they do not require field maintenance to maintain airworthiness. Iffunctional problems occur, the SDU Built-in Test Equipment (BITE) capabilityidentifies the faulty LRU. The FMHPA maintenance is limited to replacement onverified failure.6.2. EQUIPMENT AND MATERIALSCAUTION: BEFORE YOU USE A MATERIAL, REFER TO THEMANUFACTURERS‚ MATERIAL SAFETY DATA SHEETS FORSAFETY INFORMATION. SOME MATERIALS CAN BEDANGEROUS.
Installation Maintenance ManualFMHPA 821666-2Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 6.3. PROCEDURE FOR THE FMHPAWARNING: CARE TO BE TAKEN WHEN HANDLING THE FMHPA THECOOLING FINS ARE SHARP AND MAY CAUSE HARM TOPERSONNEL.CAUTION: THE FMHPA COOLING FINS ARE DELICATE. HANDLE WITHCARE AS NOT TO CAUSE DAMAGE.CAUTION: THE FMHPA IS ELECTROSTATIC DISCHARGE SENSITIVEEQUIPMENT. OBSERVE STANDARD ESD PROCEDURESWHEN HANDLING THE EQUIPMENT.A. Removal and Installation Procedure(1) Remove the FMHPA as follows:a. Ensure that electrical supply to the SDU is switched off.b. Remove forced drawn air cooling pipe from rear of FMHPA (Refer Figure 6.1 item 1). c. Disconnect DataBus/Power cable from connector J1 (5) on front of FMHPA. d. Disconnect RF IN cable from connector J2 (3) on front of FMHPA. e. Disconnect RF OUT cable from connector J3 (4) on front of FMHPA.f. Assuming that the mounting fixture is equipped with anchor nuts, loosen and remove the four fixings screws (2) that retain the FMHPA to its mounting fixture while supporting the FMHPA. Retain the screws for future installation.WARNING: CARE TO BE TAKEN WHEN HANDLING THE FMHPA THECOOLING FINS ARE SHARP AND MAY CAUSE HARM TOPERSONNEL.CAUTION: THE FMHPA COOLING FINS ARE DELICATE. HANDLE WITHCARE AS NOT TO CAUSE DAMAGE.g. Remove the FMHPA, and visually inspect it for any signs of damage. h. Install an ESD protection cap on the FMHPA connectors.i. Bag and stow the cables as required.(2) Install the FMHPA as follows:a. Un-stow and remove the bags from the cables as required.b. Remove ESD protective caps from the FMHPA connectors.
Installation Maintenance ManualFMHPA 821666-3Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval WARNING: CARE TO BE TAKEN WHEN HANDLING THE FMHPA THECOOLING FINS ARE SHARP AND MAY CAUSE HARM TOPERSONNEL.CAUTION: THE FMHPA COOLING FINS ARE DELICATE. HANDLE WITHCARE AS NOT TO CAUSE DAMAGE.c. Place the FMHPA to the dedicated mounting fixture and insert the four fixing screws. After all four fixing screw have been inserted torque tighten the screws to 5.3Nm with an appropriate tool.CAUTION: ENSURE THAT THE FIXING SCREWS HAVE BEEN FASTENED,AND THAT THE LRU IS SECURELY HELD IN POSITION.CAUTION: ENSURE THE RF CONNECTORS ARE TORQUE TIGHTENEDTO THE MANUFACTURERS RECOMMENDATIONS.d. Inspect connectors and clean.e. Connect RF OUT cable to connector J3 (4) on front of FMHPA and torque tighten to manufacturers recomendations.f. Connect RF IN cable to connector J2 (3) on front of FMHPA and torque tighten to manufacturers recomendations.g. Connect DataBus/Power cable to connector J1 (5) on front of FMHPA.h. Connect forced drawn air cooling pipe to rear of (1) FMHPA and secure.
Installation Maintenance ManualFMHPA 821666-4Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval B. Adjustment ProcedureNot Applicable.C. Repair ProcedureNot Applicable.D. Return to Service ProceduresDo the Post-Installation Test Procedures referenced in the Inspection and SystemCheckout Section of this manual.Figure 6.1 FMHPA Remove/Install
Installation Maintenance ManualFMHPA 821666-5Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval 6.4. CLEANING OF MECHANICAL PARTSCAUTION: MOISTURE AND DIRT CAN CAUSE DAMAGE TO EQUIPMENTEquipment chassis covers give the necessary protection to keep dust away fromelectronic circuits. If cleaning is required this has to be limited to the removal of particlesof dust, oil, grease, condensation, etc and only limited for those equipment accessibleparts. Before any cleaning action is carried out ensure that the equipment is disconnectedfrom all electrical power sources, and all the necessary ESD precautions are observed.a. For dust removal use a cleaning wipe, a silk paintbrush or low-pressure compressed airb. For removal of finger marks, grease, etc, clean the parts with a cleaning wipe and isopropyl alcohol, exercising care to not damage information labels.6.5. PERIODIC CHECKSSee Inspection/ Check procedure in Para 4.1.6.6. CABLING AND CONNECTIONSCAUTION: ENSURE THE RF CONNECTORS ARE TORQUE TIGHTENEDTO THE MANUFACTURERS RECOMMENDATIONS.Periodically check cable connectors (recommended) and if cable connectors are loose,remove connector, inspect for damage and cleanliness. Refit connector and tighten to therequired torque value specified by the cable manufacturer.6.7. INSTRUCTIONS FOR CONTINUED AIRWORTHINESSMaintenance requirements and instructions for continued airworthiness of the TFSFMHPA components are contained in the paragraphs that follow.Installation of FMHPA on an aircraft by an amendment to the Type Certificate (TC),Supplemental Type Certificate (STC) or Form 337 obligates the aircraft operator toinclude the maintenance information supplied by this manual (and listed below) in theoperator‚ Aircraft Maintenance Manual and the operator‚ Aircraft ScheduledMaintenance Program.a. Maintenance information for FMHPA, TFS LRU (system description, removal, installation, testing, etc.).
Installation Maintenance ManualFMHPA 821666-6Jul 2008 © THALES AVIONICS Ltd. This document and any information included are the property of Thales Avionics. They cannot be reproduced, disclosed or utilized without the company’s prior written approval b. The part numbers (see section 2) of the LRU being installed (FMHPA) should be placed into the aircraft operator‚ appropriate aircraft Illustrated Parts Catalogue (IPC).c. Wiring connection information contained in this manual (see sections 2 and 3) should be placed into the aircraft operator‚ appropriate Wiring Diagram Manual.d. The FMHPA 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.e. 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).f. FMHPA can be repaired by an Approved Maintenance Organization or an appropriately rated FAA Part 145 repair station.g. 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 FAR Part 145 Section 43.9.h. 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 145 Section 43.9.

Navigation menu