Garmin AT AT7000 Mode S Datalink Transponder User Manual 560 0405 00 AT7000 Installation Manual Rev

Garmin AT, Inc. Mode S Datalink Transponder 560 0405 00 AT7000 Installation Manual Rev

Manual

AT7000Mode S TransponderInstallation ManualDecember 14, 2001560-0405-00 Rev. --
Installation Manual AT7000 Mode S Transponder560-0405-00 Rev –December 14, 20012001 by UPS Aviation Technologies All rights reserved.Printed in the USAUPS Aviation Technologies CAGE Number 0XCJ6No part of this document may be transmitted, reproduced, or copied in any form or by any meanswithout the prior written consent of UPS Aviation Technologies.UPS Aviation Technologies and Aviation Technologies are registered trademarks of UPS Avia-tion TechnologiesUPS Aviation Technologies 2345 Turner Rd., SEPO Box 13549 Salem, OR 97302Salem, OR 97309 USAPhone: 503.581.8101800.525.6726Fax: 503.364.2138In Canada: 800.654.3415
Installation Manual AT7000 Mode S Transponder560-0405-00 Rev –December 14, 2001HISTORY OF REVISIONSRevision EN Date Description-- EN7149 Dec 14/01 Initial ReleaseORDERING INFORMATIONTo receive additional copies of this publication, order part # 560-0405-00, AT7000 Mode STransponder Installation Manual.RELATED DOCUMENTSAT7000 Mode S Transponder Factory Service Manual 560-7016-000
Installation Manual AT7000 Mode S Transponder560-0405-00 Rev –December 14, 2001NOTES
Installation Manual AT7000 Mode S Transponder560-0405-00 Rev –December 14, 2001 Page i© 2001 by UPS Aviation Technologies Inc.Record of RevisionsFor each revision, insert the revised pages into your manual and discard the replacedpages. On this record page, note the revision number and date, date pages were insertedinto the manual, and the initials of the person inserting the pages.RevisionNumber RevisionDate DateInserted By RevisionNumber RevisionDate Date In-serted By
AT7000 Mode S Transponder Installation ManualPage ii 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.List of Effective PagesSection and Page RevisionTitle 00Copyright page 00History of Revisions 00List of Effective Pages 00Table of Contents 00Sec. 1. Introduction 00Page 1 00Page 2 00Page 3 00Page 4 00Sec. 2. System Description 00Page 5 00Page 6 00Page 7 00Page 8 00Page 9 00Page 10 00Page 11 00Page 12 00Sec. 3. InstallationPage 13 00Page 14 00Page 15 00Page 16 00Page 17 00Page 18 00Page 19 00Page 20 00Page 22 00Page 23 00Page 24 00Page 25 00Page 26 00Page 27 00Page 28 00Page 29 00Page 30 00Page 31 00Page 32 00Page 33 00Page 34 00Page 35 00Page 36 00Section and Page RevisionPage 37 00Sec. 4. Post-Install CheckoutPage 38 00Page 39 00Sec. 5. Equipment Rem. and Rep.Page 40 00Page 41 00Sec. 6. OperationPage 42 00Page 43 00Sec. 7. SpecificationsPage 44 00Page 45 00Page 46 00Page 47 00Sec. 8. LimitationsPage 48 00Page 49 00Sec. 9. TroubleshootingPage 50 00Page 51 00Page 52 00Page 53 00Page 54 00Page 55 00Page 56 00Page 57 00Page 58 00Page 59 00Page 60 00Page 61 00Page 62 00Page 63 00Page 64 00Page 65 00Page 66 00Page 67 00Sec. 10. Periodic MaintenancePage 68 00Page 69 00Sec. 11. Environmental QualificationsPage 70 00Page 71 00
Installation Manual AT7000 Mode S Transponder560-0405-00 Rev –December 14, 2001 Page iii© 2001 by UPS Aviation Technologies Inc.TABLE OF CONTENTSSECTION 1 - INTRODUCTION ................................................................................................................ 11.1 ABOUT THIS MANUAL .......................................................................................................................11.2 SYSTEM DESCRIPTION........................................................................................................................11.2.1 System Overview ........................................................................................................................11.2.2 AT7000 Mode S Transponder ....................................................................................................21.2.3 Control Panel.............................................................................................................................21.2.4 Antenna ......................................................................................................................................21.2.5 Altitude Source...........................................................................................................................21.2.6 Data Link Processor ..................................................................................................................21.2.7 TCAS ..........................................................................................................................................21.3 FUNCTIONAL OPERATION...................................................................................................................31.4 REGULATORY COMPLIANCE...............................................................................................................31.4.1 CFR 47, Part 87 (FCC)..............................................................................................................31.4.2 TSO C112...................................................................................................................................31.4.3 ARINC 718-4 and ARINC 718A.................................................................................................3SECTION 2 - TRANSPONDER DESCRIPTION ..................................................................................... 52.1 GENERAL ...........................................................................................................................................52.2 OVERVIEW .........................................................................................................................................52.3 AT7000 PRODUCT SUMMARY............................................................................................................62.3.1 Gillham to A429 Serial Data Converter.....................................................................................72.3.2 Inputs to the AT7000 for Extended Squitter Position Reports....................................................72.4 DISPLAY / CONTROL ..........................................................................................................................82.5 DATA LOADER INTERFACE.................................................................................................................82.6 BUILT-IN TEST EQUIPMENT (BITE) AND DIAGNOSTICS.....................................................................82.6.1 Self-Tests ....................................................................................................................................82.6.2 Status Indicators.........................................................................................................................92.6.3 Maintenance and BITE Data......................................................................................................9SECTION 3 - INSTALLATION................................................................................................................ 113.1 PRE-INSTALLATION INFORMATION ..................................................................................................113.2 EQUIPMENT REQUIRED.....................................................................................................................113.3 MECHANICAL INSTALLATION...........................................................................................................113.3.1 Location of LRUs .....................................................................................................................113.3.2 AT7000 Provisions...................................................................................................................113.3.3 Antenna Provisions ..................................................................................................................123.4 ELECTRICAL INSTALLATION.............................................................................................................133.4.1 Middle Plug..............................................................................................................................173.4.2 Bottom Plug..............................................................................................................................213.4.3 Program Pin Inputs..................................................................................................................233.4.4 SDI Program............................................................................................................................233.4.5 Max Airspeed Program............................................................................................................233.4.6 Antenna Delay Program ..........................................................................................................243.4.7 Antenna Program.....................................................................................................................253.4.8 Antenna BITE Program............................................................................................................253.4.9 Altitude Type Selection.............................................................................................................253.5 INTERFACE CONNECTIONS ...............................................................................................................253.5.1 Discrete I/O Levels...................................................................................................................253.5.2 Gillham Code Altitude Input ....................................................................................................263.5.3 Synchro Altitude Input..............................................................................................................263.5.4 ARINC 706 Air Data Inputs .....................................................................................................263.5.5 Control Panel Input..................................................................................................................263.5.6 Standby Input ...........................................................................................................................273.5.7 Air/Ground Discrete Inputs......................................................................................................273.5.8 Functional Test Discrete Input.................................................................................................273.5.9 Altitude Input Selection............................................................................................................28
AT7000 Mode S Transponder Installation ManualPage iv 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.3.5.10 Altitude Compare .....................................................................................................................283.5.11 Transponder Fail Outputs........................................................................................................283.5.12 Flight ID Input .........................................................................................................................293.5.13 Data Link Interface ..................................................................................................................293.5.14 Downlinked Aircraft Parameters (DAPS)................................................................................293.5.15 TX / XT Coord TCAS Interface ................................................................................................293.6 DATA LOADER INTERFACE...............................................................................................................30SECTION 4 - POST-INSTALLATION CHECKOUT............................................................................ 334.1 KEY PIN ORIENTATION ....................................................................................................................33PRE-INSTALLATION CHECKOUT PROCEDURES...........................................................................................33SECTION 5 - EQUIPMENT REMOVAL AND REPLACEMENT....................................................... 355.1 REMOVAL.........................................................................................................................................355.1.1 Transponder.............................................................................................................................355.2 REPLACEMENT.................................................................................................................................355.2.1 Transponder.............................................................................................................................35SECTION 6 - OPERATION...................................................................................................................... 37SECTION 7 - SPECIFICATIONS ............................................................................................................ 397.1 ELECTRICAL.....................................................................................................................................397.2 PHYSICAL.........................................................................................................................................397.3 ENVIRONMENTAL.............................................................................................................................407.4 TRANSPONDER PERFORMANCE ........................................................................................................40SECTION 8 - LIMITATIONS................................................................................................................... 438.1 INSTALLATION .................................................................................................................................43SECTION 9 - TROUBLESHOOTING..................................................................................................... 459.1 INTRODUCTION AND OVERVIEW.......................................................................................................459.1.1 Introduction..............................................................................................................................459.1.2 Overview ..................................................................................................................................459.2 INTERFACES .....................................................................................................................................469.2.1 Buttons .....................................................................................................................................469.2.2 Test Status LEDs ......................................................................................................................469.2.3 Maintenance Display Pages.....................................................................................................469.2.4 Normal Mode ...........................................................................................................................519.2.5 Discrete Inputs .........................................................................................................................549.2.6 External Interfaces...................................................................................................................559.3 TROUBLESHOOTING .........................................................................................................................599.3.1 System Test...............................................................................................................................59SECTION 10 - PERIODIC MAINTENANCE...................................................................................... 6110.1 MAINTENANCE.................................................................................................................................61SECTION 11 - ENVIRONMENTAL QUALIFICATIONS ................................................................. 63
Installation Manual AT7000 Mode S Transponder560-0405-00 Rev –December 14, 2001 Page v© 2001 by UPS Aviation Technologies Inc.LIST OF ILLUSTRATIONSFIGURE 1 -- AT7000 SYSTEM BLOCK DIAGRAM ............................................................................................. 1FIGURE 2 – FRONT PANEL OF AT7000............................................................................................................ 6FIGURE 3 – POTENTIAL EQUIPMENT LOCATIONS........................................................................................... 11FIGURE 4 - ARINC 600 4 MCU MOUNTING TRAY....................................................................................... 12FIGURE 5 – TOP PLUG INTERCONNECT DESCRIPTION (SHEET 1) ................................................................... 13FIGURE 6 –TOP PLUG CONNECTOR LAYOUT ................................................................................................. 15FIGURE 7 – MIDDLE PLUG INTERCONNECT DESCRIPTION (SHEET 1)............................................................. 17FIGURE 8 – MIDDLE PLUG CONNECTOR LAYOUT ......................................................................................... 19FIGURE 9 – BOTTOM PLUG INTERCONNECT DESCRIPTION ............................................................................ 21FIGURE 10 – BOTTOM PLUG CONNECTOR LAYOUT....................................................................................... 22FIGURE 11 – DATA LOADER.......................................................................................................................... 32FIGURE 12 – REMOVAL OF UNIT FROM TRAY................................................................................................ 35FIGURE 13 – AT7000 DIMENSIONS............................................................................................................... 40FIGURE 14. AT7000 MODE S TRANSPONDER .............................................................................................. 45FIGURE 15. MAINTENANCE DISPLAYS.......................................................................................................... 47LIST OF TABLESTABLE 1 - EQUIPMENT FOR INSTALLATION ................................................................................................... 11TABLE 2 - ANTENNA MINIMUM SPACING...................................................................................................... 12TABLE 3 - SDI PROGRAM PINS..................................................................................................................... 23TABLE 4 - MAX AIRSPEED PROGRAM........................................................................................................... 24TABLE 5 - ANTENNA DELAY PROGRAM ....................................................................................................... 24TABLE 6 - ALTITUDE TYPE SELECTION ........................................................................................................ 25TABLE 7 - DATA LOADER PLUG ................................................................................................................... 30TABLE 8 - STATUS LEDS SUMMARY............................................................................................................ 46TABLE 9 - TROUBLESHOOTING GUIDE.......................................................................................................... 60TABLE 10 - ENVIRONMENTAL REQUIREMENTS ............................................................................................. 63
AT7000 Mode S Transponder Installation ManualPage vi 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.NOTES
Introduction AT7000 Mode S Transponder560-0405-00 Rev –December 14, 2001 Page 1© 2001 by UPS Aviation Technologies Inc.Section 1 - IntroductionThe AT7000 is a Mode S Data Link Transponder that provides surveillance functions toground-based and airborne interrogators. It responds to ATCRBS interrogations as well.1.1 About This ManualThis manual describes the installation of the UPS Aviation Technologies AT7000 ModeS Transponder along with a description of the other units that connect to the transponder.This manual is intended for use by persons certified by the Federal Aviation Administra-tion (FAA) to install avionics devices. It includes installation and checkout proceduresfor the UPS Aviation Technologies AT7000 Mode S Transponder.1.2 System Description1.2.1 System OverviewFigure 1 -- AT7000 System Block DiagramAT7000 System Block DiagramAT7000Mode S TransponderTCASATC RadarInterrogatorControl PanelTCAS*CentralMaintenanceComputer(CMC)**Optional (Notsupported in initialrelease)*OptionalAirborne System1090 Receiver(ADSB)ADSBAirborne DataLink Processor(ADLP)**OptionalAir DataComputer(ADC)
AT7000 Mode S Transponder IntroductionPage 2560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.1.2.2 AT7000 Mode S TransponderThe AT7000 transponder is packaged in a 4-MCU (Modular Concept Unit) outlined asdefined in ARINC Characteristic 600-7. The basic mechanical chassis is constructed oflightweight aluminum alloy sheet metal. The unit uses forced air cooling per ARINC 404or 600. ARINC standard LRU restraints are used as means of holding the transponder inthe mounting rack or tray. The maximum weight of the transponder is 11.5 pounds (5.2kilograms). The rear connector receptacle is a size 2-shell assembly with inserts andcontacts as defined in ARINC Characteristic 718-4/718A. The unit features a fixed car-rying handle, self-test switch with discrete LED STATUS annunciators, and a LCD dis-play for system setup and verification.1.2.3 Control PanelThe control panel for the Mode S System provides for mode control of the ATC Trans-ponders. Communication with the Mode S Transponders is accomplished via an ARINC429 bus as defined in ARINC Characteristic 718. Control panel functions includes a4096-ident code selection and display, altitude source and mode control switch, and se-lection between two onboard transponders. The control panel also input FID into thetransponder.1.2.4 AntennaWhen installing the transponder antennas, a TSO’d antenna should be selected. Two an-tennas are required. Having two antennas (one on top of the aircraft and one on the bot-tom) provides the best coverage for receiving interrogations from ground radar, planesabove, and below. L-Band type recommended antennas are P/N S65-5366-7L, manu-factured by Sensor Systems and P/N DM N150-2, manufactured by DM Antenna Tech-nologies.1.2.5 Altitude SourceThe transponder contains dual inputs for acceptable types of altitude sources. The pinconfiguration selection specifies which of the two inputs are used for obtaining altitudeinformation. Altitude sources are ADC (429), Synchro, or Gillham. The input uses aground/open logic level, where a ‘ground’ logic level specifies altitude source #2, and an‘open’ logic level specifies altitude source #1.1.2.6 Data Link ProcessorFour high speed ARINC 429 busses are provided for interfacing to a Mode S AirborneData Link Processor (ADLP). The Comm A/B input and Comm A/B output busses areused for transferring messages to and from the ADLP.1.2.7 TCASThe AT7000 contains an interface that allows it to work with an onboard TCAS II sys-tem. The interface consists of two ARINC 429 high speed data busses, an XT Coordina-tion bus that is an output from the transponder to TCAS, and a TX Coordination bus thatis an output from TCAS to the transponder.
Introduction AT7000 Mode S Transponder560-0405-00 Rev –December 14, 2001 Page 3© 2001 by UPS Aviation Technologies Inc.1.3 Functional OperationMode S System operation begins when aircraft power is applied. An initial self-test isperformed automatically upon power-up and is completed in approximately one second.Self-testing of the transponder occurs continuously while powered on. If a transponderfailure occurs, it is indicated on the control panel. Other failures are indicated via frontpanel mounted LEDs on the transponder, however, these failure indications are not avail-able to the pilot. All failures, whether hard or intermittent, are recorded in the trans-ponder maintenance memory for analysis by maintenance personnel.1.4 Regulatory ComplianceThe following standards are described in relationship to the functioning and certificationof the AT7000.1.4.1 CFR 47, Part 87 (FCC)Aviation Services, Subpart D, Technical Requirements1.4.2 TSO C112The AT7000 complies with TSO C112, Air Traffic Control Radar Beacon System/ModeSelect (ATCRBS/Mode S) Airborne Equipment.1.4.3 ARINC 718-4 and ARINC 718AThe AT7000 complies with ARINC Characteristic 718-4 and 718A, Mark 3 Air TrafficControl Transponder. The AT7000 meets the minimum subset of ARINC 718A and issoftware upgradeable for most DAPS parameters. See Transponder Description, Section2.
AT7000 Mode S Transponder IntroductionPage 4560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.NOTES
Installation Manual System Description560-0405-00 Rev –December 14, 2001 Page 5© 2001 by UPS Aviation Technologies Inc.Section 2 - Transponder Description2.1 GeneralThis section defines the system functionality for the AT7000 Mode S transponder. It is aLevel 2es transponder indicating that it performs basic Mode S functions, and is also ca-pable of transmitting extended squitters with encoded aircraft information to supportADS-B functions. The unit is also upgradeable to ICAO Level 5 (Downlinked AircraftParameters, (DAPS)) capability through software upgrades.2.2 OverviewThe AT7000 transponder is a full-featured Mode S transponder in an ARINC 600 formfactor that has been designed with a built-in capability for future growth. This trans-ponder is compatible with Change 7 TCAS systems, as well as UPS AT ADS-B systems.When utilized with a UPS AT Link and Display Processing Unit (LDPU), the unit servesas an integral part of a complete ADS-B system. ADS-B is currently certified for use as atraffic surveillance system.The AT7000 responds to both the Air Traffic Control Radar Beacon System (ATCRBS),and Mode S (Mode Select) interrogations. The AT7000 meets all requirements describedin DO-181B and EUROCAE ED-73A. This also meets Eurocae elementary surveillancerequirements including SI capability (six bit Mode S sensor interrogator codes) and flightID transmission. Flight ID (FID) may be input to the AT7000 for extended squittertransmission by either external serial data interface or by using a Gables transpondercontrol panel capable of accepting and transmitting FID information.TCAS is fully supported with antenna diversity (top and bottom) antenna ports. TheAT7000 is designed to operate with all ARINC 718/735 and conforming TCAS II com-puters.To provide maximum reliability, the unit has extensive built in test and evaluation (BITE)capabilities. This is further augmented by a LCD display on the front panel allowing fordisplay of descriptive messages allowing for far greater comprehensive testing and trou-bleshooting capabilities on aircraft.Software on board the AT7000 is certified to DO-178B Level B. Software updates canbe completed via an RS232 serial data and will be upgraded to interface with an ARINC615 data loader. The data loader port is located on the front panel of the unit.
System Description Installation ManualPage 6560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.Figure 2 – Front Panel of AT70002.3 AT7000 Product SummaryThe transponder is an ARINC 718-4/718A mode S transponder.General features of the transponder includes:• ARINC 718-4/718A compliant, ARINC 600 format and interconnect, with 4MCU size form factor• ATCRBS and Mode S operation• TSO-C112 certification• Includes Comm A and Comm B operation, (Comm C, Comm D, and DAPScapable.)• Includes extended squitter capability• Supports Mode S services• Operates from 115 volts AC, 400Hz, or 28 volts DC• Transmit power of 400 watts typical• Includes built-in self-test and diagnosticsMAINTENANCE DISPLAYXPDR PASSXPDR FAILCTRL PNLALTTOP ANTBOT ANTTESTDATA LOADERAT7000Mode S Data Link Transponderbarcode of serial numberSN '1234567'UPS Aviation Technologies, Salem OR USAModel:AT7000PN: 430-6091 - 00 - 00SW ModTSO-C112 Class 2A7, 121, 011RTCA/DO-178B Software Level BRTCA/DO-160D Env. Cat.FCC ID xxxxxxx Mode S TransponderCAADEABACBAFGHJKLZYXWVUTSRPNMADAEAFAGAHAJAKALAMANHW ModCAADEABACBA FGHJKLZYXWVUTSRPNMADAEAFAGAHAJAKALAMANSoftwareMap/DatabaseWeight10.0 lbs.
Installation Manual System Description560-0405-00 Rev –December 14, 2001 Page 7© 2001 by UPS Aviation Technologies Inc.2.3.1 Gillham to A429 Serial Data ConverterThe AT7000 includes a Gillham code to ARINC 429 serial data converter integral to theunit to support installation in non-ADC equipped aircraft needing serial altitude data.This is compliant to ARINC 706-4 output.2.3.2 Inputs to the AT7000 for Extended Squitter Position ReportsSome users of the AT7000 may not wish to install an ADLP concurrently with the trans-ponder, but wish to output basic position reports to comply with future European re-quirements. This may be accomplished by inputting the required ARINC labels to thetransponder. The minimum label set is as follows for airborne position squittering:Minimal Necessary LabelsLabel # Description Minimum Rate Alternate Labels110 (120) Latitude (Fine) 5 Hz 310111 (121) Longitude (Fine) 5 Hz 311150 Time Word 5 Hz140 Fractional Seconds(should be last word ofdata block)5 Hz130 HPL 5 Hz 247377 Equipment ID – must be142 0.5 Hz
System Description Installation ManualPage 8560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.Minimal Necessary Labels (Only Type 1&2 or Type 3&4 Required)Label # Description Minimum Rate Alternate Labels174 NS Velocity – Type Code1&2 5 Hz 103 and 112(or 311 and 312)166 EW Velocity – TypeCode 1&2 5 Hz 103 and 112(or 311 and 312)OR320 Magnetic Heading – TypeCode 3&4 5 Hz210 True Airspeed – TypeCode 3&4 (from ADC) 5 Hz 2062.4 Display / ControlThe transponder is designed to work with a standard transponder control panel. Thecontrol panel may output FID for transmissions.2.5 Data Loader InterfaceThe transponder includes a front panel mounted data loader interface connector. The in-terface connector will include an RS-232 serial interface for use with a PC. An ARINC615 input is provisioned, but not implemented in the software for the initial product re-lease.2.6 Built-In Test Equipment (BITE) and DiagnosticsThe transponder includes a built-in test and diagnostics to automatically test the trans-ponder functions at system power up and monitor the operation performance during nor-mal operation.2.6.1 Self-TestsThe built-in tests include the following and are completed at power up of the transponder.a) power supply voltagesb) memory checksc) transmitter (monitor replies)d) synthesizerse) transponder interfacesf) top and bottom antenna test
Installation Manual System Description560-0405-00 Rev –December 14, 2001 Page 9© 2001 by UPS Aviation Technologies Inc.2.6.2 Status IndicatorsThe transponder includes status indicators on the front panel of the unit that can be easilyviewed with the unit installed in its standard mounting. The purpose of the status indica-tors is to help determine the source of a potential failure to determine the fault condition.The status indicators includes status for the following conditions:a) transponder pass/failb) control panel failurec) top antenna failured) bottom antenna failuree) altitude compare failureThe unit also has a LCD front panel display that allows for descriptive text messages tobe displayed for the purpose of determining aircraft system faults, as well as transponderfaults.2.6.3 Maintenance and BITE DataThe transponder is capable of outputting maintenance data using the data loader interface.An RS-232 interface is supported.The transponder includes maintenance data that can be output on the test data interfaces.The data includes the following:a. aircraft system power On/Off times, aircraft Airborne/Ground times.b. power on cycle countc. airframe cycle count (air/ground cycle count)d. fault identification (if applicable)
System Description Installation ManualPage 10 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.NOTES
Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 11© 2001 by UPS Aviation Technologies Inc.Section 3 - InstallationThis section describes the installation of the AT7000 Mode S Transponder.3.1 Pre-Installation InformationThe transponder can be mounted in any convenient location in the E/E bay; however, itshould be mounted within 50 feet of the antenna unless a low-loss coaxial cable is used tomaintain a worst case loss of 3 dB per ARINC 718-4/718A. Top and bottom coaxial runlength differences can be compensated for by use of the antenna delay program pins. SeeFigure 4, TP3C through TP3F The unit can utilize external cooling air in accordancewith ARINC 600, ARINC 404, or operate in convection cooled environments. Howevercooled, the airflow rate provided to the transponder should be 13 kg/hr and the pressuredrop of the coolant air flow through the equipment should be 5 + 3mm of water.3.2 Equipment RequiredTable 1 - Equipment for InstallationLRU Mating Connector Qty/SystemAT7000 NSXN2P203X0105 13.3 Mechanical Installation3.3.1 Location of LRUsThe AT7000 is located in the E/E bay. The Control Panel is located in the cockpit.Figure 3 – Potential Equipment Locations3.3.2 AT7000 ProvisionsThe AT7000 is mounted in a 4 MCU mounting tray per ARINC 600. See Figure 3.
Installation Installation ManualPage 12 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.3.3.2.1 Mounting TrayFigure 4 - ARINC 600 4 MCU Mounting Tray3.3.3 Antenna ProvisionsInstall antenna in accordance with manufacturer specifications.Sealant should be applied as required to the antenna base to prevent leakage of water andcondensation while also preventing corrosion. Any sealant or aerodynamic smoother usedaround the edge of the antenna base must be applied only after the antenna has beenbolted and secured to the aircraft. Each antenna should have a maximum of 2.5 milli-ohmground bond resistance.Table 2 - Antenna Minimum SpacingAntenna Minimum SpacingDM-N150-2 (Dorne-Margolin P/N)S65-5366-7L (Sensor Systems P/N)Or equivalent L-Band Antenna20” from other L-band antennas in samerange.
Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 13© 2001 by UPS Aviation Technologies Inc.3.4 Electrical InstallationReferenceSection Signal Name Pin No. Equipment Connection3.5.2Gillham Code Altitude Input #2A1A2A4B1B2B4C1C2C4D2TP 1ATP 1BTP 1CTP 1DTP 1ETP 1FTP 1GTP 1HTP 1JTP 1K*MSP Bus Input ARINC 429ABTP 2ATP 2B From Airborne Data Link Processor Unit (LDPU)3.5.14DAPS Input ARINC 429ABTP 2CTP 2DHardware ProvisionedOutput ARINC 429ABTP 2ETP 2FReserved #1 Output ARINC 429ABTP 2GTP 2HReserved Discrete Input #1TP 2J3.5.2Gillham Code Altitude Input #2D4 TP 2K From Encoding Altimeter #2Reserved Discrete OutputTP 3A3.5.11.2Transponder Fail Output #2TP 3B To Mode S Control Panel J1-123.4.6Antenna Cable Delay ProgramTop/BotBACommonTP 3CTP 3DTP 3ETP 3F3.4.4SDI ProgramBACommonTP 3GTP 3HTP 3J3.5.2Gillham Code Altitude Input #2Common TP 3K3.5.3Synchro Altitude Input #1X courseY courseZ courseRef HRef CX fineY fineZ fineflagTP 4ATP 4BTP 4CTP 4DTP 4ETP 4FTP 4GTP 4HTP 4JFrom Air Data Computer #1*OptionalFigure 5 – Top Plug Interconnect Description (Sheet 1)
Installation Installation ManualPage 14 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.ReferenceSection Signal Name Pin No. Equipment Connection3.4.5Max Airspeed ProgramABCCOMTP 5ATP 5BTP 5CTP 5D3.5.15TX Coordination TCAS 429ABTP 5ETP 5FTo Pin 12D of TCAS ComputerTo Pin 12E of TCAS Computer3.5.15XT Coordination TCAS 429ABTP 5GTP 5HTo Pin 14F of TCAS ComputerTo Pin 14G of TCAS Computer3.5.7Air/Ground Discrete Inputs#2#1TP 5JTP 5KTo Air/Ground Relay3.5.12NAV Data/Flight ID 429 Input BusABTP 6ATP 6B From LDPU (ADLP)ReservedABTP 6CTP 6DReservedABTP 6ETP 6FReservedTP 6GReservedABTP 6HTP 6J3.4.7Antenna ProgramTP 6K3.5.5Control Panel Input Bus #1ABTP 7ATP 7BTo Pin 22 of Control Panel (Optional)To Pin 23 of Control Panel (Optional)ReservedTP 7C3.5.5.1Control Panel Data Port SelectTP 7D3.5.5Control Panel Input Bus #2ABTP 7ETP 7FTo Pin 22 of Control PanelTo Pin 23 of Control Panel3.5.6StandbyTP 7G3.5.4Air Data #1 ARINC 429 InputABTP 7HTP 7J To #1 Air Data ComputerReservedTP 7KFigure 4 – Top Plug Interconnect Description (Sheet 2)
Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 15© 2001 by UPS Aviation Technologies Inc.Figure 6 –Top Plug Connector LayoutSDIB AGillham Altitude Input #2A1 A2 A4 B1 B2 B4 C1 C2 C4 D2D4ABCDEFGHJK1234567comData Link InputA B(429 ip)RSVD #1 OutputA B(429)XPDR Fail#2(disc op)Antenna Delay ProgramcomB ATop/Btm comSynchro Altitude #1----------------------- Course ----------------------X Y Z------------------------ Fine -----------------------X Y ZH C26VACRefSynchroFlag #1(disc ip)RSVDIP #2(disc ip)Max Airspeed ProgramA B CcomTX COORDA B(429 ip)XT COORDA B(429 pp)Air/Gnd#2(disc ip)Air/Gnd#1(disc ip)Flight ID / FMSA B(429 ip)ADL InputA B(429 ip)ADL OutputA B(429 op)ADL IPSel(disc ip)ReservedA BAntennaProgram(prgm ip)Control Panel IP #1A B(429 ip)RSVDIP #3(disc ip)Cntl PnlSelect(disc ip)Control Panel IP #2A B(429 ip)Standby(disc ip)Air Data #1 InputA B(429 ip)RSVDIP #4(disc ip)Comm C/D InputA B(429 ip)Comm C/D OutputA B(429 op)RSVDIP #1(disc ip)RSVDOutput(disc op)Top Antenna1-23-01 RASTP
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Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 17© 2001 by UPS Aviation Technologies Inc.3.4.1 Middle PlugReferenceSection Signal Name Pin No. Equipment Connection3.4.3.1Reserved Mode S AddressAddress 1Address 2Address 3Address 4Address 5Address 6Address 7Address 8Address 9Address 10Address 11Address 12Address 13Address 14Address 15Address 16Address 17Address 18Address 19Address 20Address 21Address 22Address 23Address 24Address ComMP 1AMP 1BMP 1CMP 1DMP 1EMP 1FMP 1GMP 1HMP 1JMP 1KMP 2AMP 2BMP 2CMP 2DMP 2EMP 2FMP 2GMP 2HMP 2JMP 2KMP 3AMP 3BMP 3CMP 3DMP 3EReserved #1 ARINC 429 Input ABMP 3FMP 3GReserved for mode control panel or otherDAPS inputs.3.5.1.1 Functional Test Discrete Input MP 3H3.5.10.2 Altitude Compare Fail Output MP 3J3.5.11.1 XPDR Fail #1 Output MP 3K3.5.2 Gillham Code Altitude Input #1A1A2A4B1B2B4C1C2C4D2MP 4AMP 4BMP 4CMP 4DMP 4EMP 4FMP 4GMP 4HMP 4JMP 4KFrom Altimeter3.5.4 Air Data #2 ARINC 429 Input ABMP 5AMP 5B From #2 Air Data ComputerReserved MP 5CMP 5D Reserved for inputs for DAPSData Link 429 Output ABMP 5EMP 5F MSP Bus to LDPUFigure 7 – Middle Plug Interconnect Description (Sheet 1)
Installation Installation ManualPage 18 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.ReferenceSection Signal Name Pin No. Equipment Connection3.5.10.1Altitude Compare InputMP 5G To Pin 17 of Control Panel3.6DL/DHLProgram Pin MP 5H3.4.8Antenna BITE Enable ProgramProgram Pin MP 5J3.5.2Gillham Code Altitude Input #1D4 MP 5KMaintenance Data 429 InputABMP 6AMP 6B Hardware ProvisionsMaintenance Data 429 OutputABMP 6CMP 6D Hardware Provisions3.5.9Altitude Input Source SelectionMP 6E To Pin 16 of Control Panel3.4.9Altitude Type Selection ProgramBACOMMP 6FMP 6GMP 6HReserved #2 ARINC 429 InputMP 6J Tied to MP 7K3.5.2Gillham Code Altitude Input #1COM MP 6K3.5.3Synchro Altitude Input #2X CourseY CourseZ CourseRef HRef CX FineY FineZ FineSynchro #2MP 7AMP 7BMP 7CMP 7DMP 7EMP 7FMP 7GMP 7HMP 7J Discrete InputReserved #2 IP 429BMP 7K Tied to MP 6JFigure 6 – Middle Plug Interconnect Description (Sheet 2)
Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 19© 2001 by UPS Aviation Technologies Inc.Figure 8 – Middle Plug Connector LayoutMode S Address Input1234567891020A B C D EFGHJK1234567Gillham Altitude Input #1A1Data Link OutputA B(429 op)Ant BITE(prgrm ip)Maint Data InputA B(429 ip)Maint Data OutputA B(429 op)Synchro Altitude #2X Y CXBottom Antenna1-23-01 RASMP11 12 13 14 15 16 17 18 1921 22 23 24 comRsrvd #1 IPA B(429 ip)Func Test(disc ip)Alt CmparFail(disc op)XPDRFail #1(disc op)A2 A4 B1 B2 B4 C1 C2 C4 D2D4comAir Data #2A B(429 ip)ReservedA BAlt CmparEn(disc ip)DL / DLP(prgm ip)Alt SrcSelect(disc ip)Altitude Type SelectB A comRsrvd #2429 IPARsrvd #2429 IPBZHYZ26VACRef---------------------- Course --------------------- ------------------------ Fine -----------------------SyncrhoFlag #2(disc ip)
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Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 21© 2001 by UPS Aviation Technologies Inc.3.4.2 Bottom PlugSignal Name Pin No. Equipment Connection115 VAC Input HOT BP 1Future Spare BP 228 VDC Input Return BP 3Future Spare BP 4Future Spare BP 5Future Spare BP 6115 VAC Input Return BP 7Signal Ground BP 8Future Spare BP 928 VDC BP 10Chassis Ground BP 11Suppression BP 12Suppression BP 13Figure 9 – Bottom Plug Interconnect Description
Installation Installation ManualPage 22 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.Figure 10 – Bottom Plug Connector LayoutBottomPlug12SuppressionPulse Input13(int. conxto pin 12)SuppressionPulse Input11ChassisGround(Aircraft DCGround)9Not Used1115 v ACpower inputHot2Not Used328VDCPower InputReturn(-)7115 vacPowerInputReturn8SignalGround(Aircraft DCGround)6Not Used5Not Used4Not Used1028 VDCPower Input(+)
Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 23© 2001 by UPS Aviation Technologies Inc.3.4.3 Program Pin InputsThe transponder will require program pin connections defined by the particular installa-tion. The transponder is programmed by connecting the appropriate input pins to com-mon (ground) as defined in this section.3.4.3.1 Mode S AddressThe Mode S address is a unique 24-bit code assigned to each aircraft.The 24-bit address is programmed by making the appropriate connections to the addressinput pins. For each “1” bit in the address, connect the corresponding address input to theaddress common pin (MP 3E), leave the pin open for a “0” bit.Address 1 input (MP 1A) is the MSB (most significant bit) address, 24-input (MP 3D) isthe LSB (least significant bit). The address is normally defined as an eight character octalcode.In the United States, the Mode S address can be obtained from:Federal Aviation AdministrationFAA Aircraft RegistryPO Box 25504Oklahoma City, OK 73125Telephone: (405) 954-3116Fax: (405) 954-35483.4.4 SDI ProgramThe SDI program inputs are used to identify the transponder system number. The trans-ponder number is made by connecting the defined SDI inputs to the SDI common pin (TP3J) as follows:Table 3 - SDI Program PinsTransponder # SDI Prgm BTP 3GSDI Prgm ATP 3HNot Applicable Open Open1Open Common2Common Open3Common CommonCommon pin TP 3J3.4.5 Max Airspeed ProgramThe maximum (max) airspeed program pins are used to identify the aircraft’s maximumcruise airspeed capability. The maximum airspeed is programmed by connecting themaximum airspeed program pins to the common pin (TP 5D) as follows:
Installation Installation ManualPage 24 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.Table 4 - Max Airspeed ProgramMax airspeed connectionsMax Airspeed Prgm CTP 5CPrgm BTP 5BPrgm ATP 5ANot available Open Open OpenUp to 75 knots Open Open Common75 to 150 knots Open Common Open150 to 300 knots Open Common Common300 to 600 knots Common Open Open600 to 1200 knots Common Open CommonAbove 1200 knots Common Common OpenNot assigned Common Common CommonCommon pin TP 5D3.4.6 Antenna Delay ProgramThe antenna cables from the transponder to the top and bottom antennas may vary inlength. The transponder must be programmed for the cable delay if the difference be-tween the top and bottom antennas is greater than 50 nsec. This is accomplished by con-necting the appropriate pins to the common pin as defined in the following table.Table 5 - Antenna Delay ProgramDelay Program ConnectionsDifferential Delay (nsec) Delay BTP 3DDelay ATP 3EProgrammed Delay(nsec)0 to 50 Open Open 051 to 150 Open Common 100151 to 250 Common Open 200251 to 350 Common Common 300Open CommonTP 3C Add delay to topantenna Add delay tobottom antennaCommon Pin TP 3F3.4.6.1 Antenna Delay CalculationThe antenna cable delay is defined as the round trip propagation delay between the trans-ponder and the antenna. Typical cable delay is 1.54 nsec/ft.
Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 25© 2001 by UPS Aviation Technologies Inc.To compute the cable delay:1. Calculate the difference in cable lengths between the top and bottom antennas infeet.2. Determine the cable delay: difference in length x 2 x 1.54 nsec/ft.3. Select the coding and make the connections to the antenna delay program pins.4. Select the top or bottom code: connect TP 3C to common if the top antenna coax islonger than the bottom.3.4.7 Antenna ProgramThis program pin is used to identify installations in which only the bottom antenna isused.Ground single bottom mount antenna installationOpen dual antenna installation3.4.8 Antenna BITE ProgramThis program pin is used to enable the antenna BITE test. Antennas capable of the BITEtest will have a DC path to ground. If enabled, the transponder will perform a continuitytest to verify the antenna is connected.Ground enable antenna BITE testOpen disable antenna BITE test3.4.9 Altitude Type SelectionThe transponder is capable of using altitude data from one of four types. The altitude typeused is programmed by making the connections as defined in the following table.Table 6 - Altitude Type SelectionProgram PinsData Source MP 6F MP 6G429 Data Open OpenSynchro Data Open CommonGillham Data Common CommonCommon Pin MP 6H3.5 Interface Connections3.5.1 Discrete I/O Levels3.5.1.1 Discrete InputsThe discrete inputs have the following logic level thresholds:Ground .................. < 3.5 volts DC or a resistance of < 10 ohms to groundOpen...................... > 18 volts DC or a resistance of > 100K to ground
Installation Installation ManualPage 26 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.Series isolation diodes are included on all discrete inputs.3.5.1.2 Discrete OutputsThe discrete outputs, unless otherwise defined, are open drain outputs. When active,the output will be pulled low to ground. When inactive, the output be open (or pulledhigh to 28 volts with 100K ohm).Active.................... pulled low to groundInactive.................. open (100k pull-up)3.5.1.3 Valid Flag InputsThe valid flag inputs are intended for connection to valid superflag outputs on con-nected equipment. The levels for these inputs are as follows:Valid...................... > 18 volts DC input relative to groundInvalid ................... < 3.5 volts DC input relative to ground3.5.2 Gillham Code Altitude InputThe transponder allows connection to an altitude source using the 11 wire Gillhamcode interface. Two inputs are provided, and the source can be selected with the alti-tude source discrete input, see 3.5.9.3.5.3 Synchro Altitude InputThe altitude information for the transponder may be obtained from an analog synchroaltitude interface.3.5.3.1 Synchro Valid Flag InputThe synchro valid flag inputs are used to indicate the validity of the correspondingsynchro input. The transponder will not use the synchro altitude if the valid flag inputindicates an invalid condition. The synchro valid flag is a high level input.3.5.4 ARINC 706 Air Data InputsThe altitude information for the transponder may be obtained from an ARINC 706 airdata system via two low speed ARINC 429 data busses.3.5.5 Control Panel InputThe control panel data may be entered into the transponder on either of two low speedARINC 429 data busses (Ports A and B). The port is selected by the control data portselect discrete input. See paragraph 3.5.5.1.3.5.5.1 Control Panel Port SelectionThe control port selection input is used to select which control panel port the trans-ponder will use:Ground ..................uses control panel port AOpen......................used control panel port B
Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 27© 2001 by UPS Aviation Technologies Inc.This input is a discrete input as defined in 3.5.1.1.3.5.6 Standby InputThe standby discrete input is used to place the transponder in either the standby or ac-tive modes and is normally connected to the transponder control panel. In the standbymode, the transponder will not respond to any interrogations or generate squitters.BITE will continue to operate in the standby mode. In the active mode, the trans-ponder will respond to valid interrogations and generate squitters.Ground ..................standbyOpen......................activeThis input is a discrete input as defined in 3.5.1.1.3.5.7 Air/Ground Discrete InputsThe air/ground discrete inputs are used by the transponder to determine air / groundstatus of the aircraft. This is used to control or inhibit replies and to indicate whetherthe aircraft is on the ground or airborne for Mode S replies.3.5.7.1 Air/Ground #1This input is used to not inhibit ATCRBS replies when on the ground, and is typicallyused for ramp test functions so that the transponder can reply to all types of interroga-tions.Ground ..................aircraft on the groundOpen......................aircraft airborneThis input is a discrete input as defined in 3.5.1.1.3.5.7.2 Air/Ground #2This input is used to indicate that the aircraft is on the ground, and is normally con-nected to the air/ground switch. When on the ground, the transponder will inhibit re-plies to ATCRBS interrogations.Ground ..................aircraft on the groundOpen......................aircraft airborneThis input is a discrete input as defined in 3.5.1.1.3.5.8 Functional Test Discrete InputThe functional test input is used to place the transponder in a functional test mode.Ground ..................enable functional testOpen......................normal operationThis input is a discrete input as defined in 3.5.1.1.
Installation Installation ManualPage 28 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.3.5.9 Altitude Input SelectionThis input is used to select the active port used for the altitude data input.Ground ..................uses altitude input #2Open......................uses altitude input #1This input is a discrete input as defined in 3.5.1.1.3.5.10 Altitude Compare3.5.10.1 Altitude Compare EnableThe altitude compare enable discrete input is used to enable the altitude comparefunction. Both altitude inputs must be valid. This feature works with Gillham, syn-chro, or ADC inputs, as selected.Ground .................. altitude compare enabledOpen...................... altitude compare inhibitedThis input is a discrete input as defined in 3.5.1.1.3.5.10.2 Altitude Compare Fail OutputThe altitude fail discrete output is used to indicate invalid altitude input data, and isnormally connected to an indicator on the control panel.Ground ..................valid data, or altitude compare normalOpen......................invalid, or altitude compare failureThe function of the altitude fail output is dependent on the altitude source selected asfollows:Gillham data..........when the altitude compare is enabled, the output will indicatefailed when the two Gillham inputs are not within 500 feetARINC 429 data ...output will indicate failed when the ARINC 429 input is inva-lid or ADC altitude inputs differ by more than 200 feet.Synchro data..........output will indicate failed when the Synchro input is invalid3.5.11 Transponder Fail Outputs3.5.11.1 Transponder Fail Discrete Output #1This output will supply 5 volts DC (capable of 25 mA) when the transponder hasfailed, and will be open when the transponder is operating normally.3.5.11.2 Transponder Fail Discrete Output #2This output is open when the transponder has failed and is pulled low to ground whenthe transponder is operating normally.Valid...................... pulled low to groundFailed..................... open
Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 29© 2001 by UPS Aviation Technologies Inc.This output is a discrete output as defined in 3.5.1.2.3.5.12 Flight ID InputThe flight ID may be input to the transponder from multiple serial inputs, dependingupon installation requirements. The transponder will accept flight identification from anyof these inputs, which is contained within four ARINC 429 data words.3.5.13 Data Link InterfaceFour high speed ARINC 429 busses are provided for interfacing to a Mode S AirborneData Link Processor (ADLP). The input and output busses are used for transferring mes-sages to and from the ADLP.3.5.14 Downlinked Aircraft Parameters (DAPS)The DAPS input busses and DAPS output busses are used for transferring aircraft spe-cific parameters to the requesting ground station. Enabling this feature requires a soft-ware upgrade. See ARINC 718A.3.5.15 TX / XT Coord TCAS InterfaceThe TCAS/Transponder interface consists of two high-speed ARINC 429 busses. Inter-face standards are listed in ARINC 735 and DO-185b. The transponder is operable withboth Collins and ACSS TCAS units.
Installation Installation ManualPage 30 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.3.6 Data Loader InterfaceTable 7 - Data Loader PlugReferenceSection Signal Name Pin No. Equipment Connection2.5Portable Data Loader (PDL) ARINC 615 Input BusAB12429 Input (Provisions Only)429 Input (Provisions Only)Spare3Spare4Chassis Ground (429 Input Bus Shield)GND 5Shield GroundSpare6Spare7PDL ARINC 615 Output BusAB89429 Output (Provisions Only)429 Output (Provisions Only)Spare10Spare11Spare12Spare13Spare14Spare15Chassis Ground (429 Output Bus Shield)GND 16 Shield GroundSpare17Spare18Spare19115 Volt AC Power Input HOT20Chassis GroundGND 21115 Volt AC Power Input COMMON22Spare23Spare24Spare25Spare26Spare27Spare28Spare29Spare30Spare31Spare32Spare33
Installation Manual Installation560-0405-00 Rev –December 14, 2001 Page 31© 2001 by UPS Aviation Technologies Inc.Table 7 - Data Loader Plug (Continued)ReferenceSection Signal Name PinNo. Equipment ConnectionSpare34Spare35Spare3628 Volt DC Power InputPOS 3728 Volt DC Power ReturnNEG 38Spare39RS-232 Input40 Maintenance Data/Software Update PortRS-232 Output41 Maintenance Data/Software Update PortPDL CTS Input42PDL RTS Output43Spare44Spare45Spare46Spare47Chassis GroundGND 48Chassis GroundGND 49PDL Function Discrete#1 50PDL Function Discrete#2 51PDL Function Discrete#3 52PDL Function Discrete#4 53
Installation Installation ManualPage 32 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.VIEW OF MATING CONNECTOR ON AIRCRAFTVIEW OF CONNECTOR ON UNITFigure 11 – Data Loader
Installation Manual Post-Installation Checkout560-0405-00 Rev –December 14, 2001 Page 33© 2001 by UPS Aviation Technologies Inc.Section 4 - Post-Installation CheckoutThe Post Installation System Checkout verifies the wiring in the aircraft after installation.The AT7000 includes Built-In Test Equipment (BITE) software functions. The BITEsoftware is used in the post-installation wiring checkout. The actual tests conducted willbe determined by the selected installation options.4.1 Key Pin OrientationVerify the key pin orientation on the ARINC connector is correct in the mounting tray.Pin orientation is ARINC polarization index code 5. The view of the figure below is fromthe back of the unit, and the dark areas are the solid part of the key. This is specificallykeyed for a Mark 3 transponder.4.2 Pre-Installation Checkout ProceduresPrior to installing the equipment, perform power check as outlined below.Power Check Transponder115 VAC BP1 (see note below)115 Return BP728 VDC BP10 (see note below)28 Return BP 3Note: The unit is able to accept either 28 VDC or 115 VAC.
Post-Installation Checkout Installation ManualPage 34 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.NOTES
Installation Manual Equipment Removal and Replacement560-0405-00 Rev –December 14, 2001 Page 35© 2001 by UPS Aviation Technologies Inc.Section 5 - Equipment Removal and Re-placement5.1 Removal5.1.1 TransponderRemove the transponder from the tray with ARINC 600 hold-downs as follows:1. Loosen unit hold-down knobs.Figure 12 – Removal of Unit from Tray2. Pull out and down to release the knob from the hook of component.3. Slowly pull forward on unit handle to separate unit and tray connectors. Transponderis now free to be removed from mounting tray. Place electrostatic protective coversover transponder connector and aircraft mating electrical connector.5.2 Replacement5.2.1 TransponderReplace the transponder in mounting tray as follows:1. Remove protective plastic covers from aircraft connectors. Remove electrostaticprotective covers from transponder connectors.2. Slide transponder into mounting tray.CAUTION: DO NOT FORCE FIT. IF MATING IS DIFFICULT, REMOVE THETRANSPONDER AND CHECK FOR CONNECTOR PINS THATMAY BE BENT OR OUT OF ALIGNMENT. ALSO, CHECK THEALIGNMENT OF THE RECEPTACLE IN MOUNTING TRAY.
Equipment Removal and Replacement Installation ManualPage 36 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.3. Carefully apply firm pressure until transponder connector is mated with connectorreceptacle on mounting tray.4. Pull knobs of mounting tray over hooks on the component and tighten unit hold-downknobs, ensuring proper engagement is made.
Installation Manual Specifications560-0405-00 Rev –December 14, 2001 Page 37© 2001 by UPS Aviation Technologies Inc.Section 6 - OperationThe Mode S Data Link System can be configured in the following ways: two Mode STransponders or one Mode S Transponder and one ATCRBS Transponder. Single trans-ponder installations are acceptable. The function of the Mode S System is to provide airtraffic information to Mode S and ATCRBS ground stations to aid in the air traffic con-trol. The Mode S System receives ATCRBS interrogations (ground to air) and transmitsATCRBS replies (air to ground); receives Mode S interrogations (ground to air) andtransmits Mode S replies (air to ground); receives TCAS interrogations (air to air) andtransmits Mode S replies (air to air).
Specifications Installation ManualPage 38 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.NOTES
Installation Manual Specifications560-0405-00 Rev –December 14, 2001 Page 39© 2001 by UPS Aviation Technologies Inc.Section 7 - SpecificationsThis section includes detailed electrical, physical, environmental, and performance speci-fications for the AT7000.7.1 ElectricalPower Requirements (28VDC)Operating Voltage ....................18 to 32.2VDC; 28 VDC typicalPower Consumption:Standby Mode..........................................20 WattsActive Mode (typical load)......................30 WattsActive Mode (maximum load..................60 WattsPower Requirements (115V, 400 Hz):Operating Voltage.....................90 to 135VAC, 400 Hz; 115VAC, 400 Hz typicalPower Consumption:Standby Mode..........................................24 WattsActive Mode (typical load)......................36 WattsActive Mode (maximum load..................65 Watts7.2 PhysicalARINC 600 4MCU Type 2 Connector; (Polarization code “05”)Height...................................................7.64"Width....................................................5.04"Depth ....................................................14.107"AT7000 Weight ...................................9.6 lbs.
Specifications Installation ManualPage 40 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.14.107”5.04”7.64”Figure 13 – AT7000 Dimensions7.3 EnvironmentalThe AT7000 Mode S Transponder is designed and tested to meet appropriate categoriesof RTCA/DO-xxx. The Environmental Qualification Form is included in Section 10.Operating temperature...............................-20°C to +70°CStorage temperature ..................................-55°C to +85°CTemperature variation...............................5°C per minute (minimum)Humidity ...................................................95% RH at 65°C for 6 hours (10 day cycle)Maximum altitude.....................................55,000 feetCooling......................................................The unit can utilize external cooling air inaccordance with ARINC 600, ARINC 404or operate in convection cooled environ-ments.7.4 Transponder PerformanceTSO................................................................TSO-C112TSO Class ......................................................CL 2A7, 121, 011Warm-up ........................................................None requiredReceiver Frequency........................................1030 MHzSensitivity (MTL) ..........................................-72 dBm +/- 1 dBDynamic Range..............................................>50 dBSide Lobe Suppression...................................2 pulse (P1, P2), -60 dBmTransmitter Frequency...................................1090 MHz +/- 120 kHz
Installation Manual Specifications560-0405-00 Rev –December 14, 2001 Page 41© 2001 by UPS Aviation Technologies Inc.Transmitter Power..........................................250 watts minimum, 400 watts typical, 600watts maximumMode A Capability.........................................4096 codes plus SPI ident pulseMode C Capability.........................................-1000 to 126,700 feet, 100 foot increments.Mode S Capability .........................................-1000 to 126,700 feet, 25 foot increments.
Specifications Installation ManualPage 42 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.NOTES
Installation Manual Limitations560-0405-00 Rev –December 14, 2001 Page 43© 2001 by UPS Aviation Technologies Inc.Section 8 - Limitations8.1 InstallationInstallations are to be made in accordance with all appropriate FAA approved guidelinesfor each given installation. It is the responsibility of the installer to ensure that aircraftinstallation conditions meet the appropriate standards for the specific type and class andoperation of aircraft involved.
Limitations Installation ManualPage 44 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.NOTES
Installation Manual Troubleshooting560-0405-00 Rev –December 14, 2001 Page 45© 2001 by UPS Aviation Technologies Inc.Section 9 - Troubleshooting9.1 Introduction and Overview9.1.1 IntroductionThe AT7000 includes a status display located on the unit front panel which provides ad-ditional information from the status LEDs. The display is used to display the mainte-nance information. The four buttons located below the display are used to scroll throughthe available display information.The maintenance display includes an LED backlight. The backlight turns on when a but-ton is pushed and remains on for five minutes after the last button is pressed.9.1.2 OverviewThe AT7000 consists of the following interfaces for the user. On the front panel is a fourline by 16-character LCD display with backlight, five push buttons, and six status LEDs.These interfaces are used to provide information useful for unit diagnostics, installationcheckout and verifying of aircraft interface inputs.The maintenance display provides information about the unit, including: software versionnumber, system failure information, configuration pin inputs, discrete inputs, externalinterfaces, and receiver/transmitter enable status.Figure 14. AT7000 Mode S TransponderMAINTENANCE DISPLAYXPDR PASSXPDR FAILCTRL PNLALTTOP ANTBOT ANTTESTDATA LOADERAT7000Mode S Data Link Transponderbarcode of serial numberSN '1234567'UPS Aviation Technologies, Salem OR USAModel:AT7000PN: 430-6091 - 00 - 00SW ModTSO-C112 Class 2A7, 121, 011RTCA/DO-178B Software Level BRTCA/DO-160D Env. Cat.FCC ID xxxxxxx Mode S TransponderCAADEABACBAFGHJKLZYXWVUTSRPNMADAEAFAGAHAJAKALAMANHW ModCAADEABACBA FGHJKLZYXWVUTSRPNMADAEAFAGAHAJAKALAMANSoftwareMap/DatabaseWeight10.0 lbs.
Troubleshooting Installation ManualPage 46 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.9.2 Interfaces9.2.1 ButtonsThe TEST button located under the front panel fault status LEDs is pushed to initiate the‘Self Test’ and ‘Leg Fault’ status information.The front panel buttons under the display are used for navigating display pages as fol-lows:← and → These buttons are used to select the column. When pressing one of thesebuttons, the top page of either the previous (←) or next (→) group will bedisplayed.↑ and ↓These buttons are used to scroll through the pages within a column.Pressing the ↑ button will move the previous page, the ↓ button will moveto the next page.Note: The pages wrap around. The display is used only for displaying trans-ponder information. No configuration or data can be input using the frontpanel display and buttons.9.2.2 Test Status LEDsThe AT7000 includes six test status LEDs on the front panel. These LEDs are used toprovide transponder test results and are generally used by aircraft mechanics. Failurelights will stay illuminated for 3 seconds after powering up. Once in the self test modethe fail light will stay illuminated for 10 seconds. When in this mode, pressing any but-ton will illuminate the failure for 30 seconds.Table 8 - Status LEDs SummaryLED Color DescriptionXPDR PASS Green Transponder pass, turned on if B.I.T.E. passes and the transponder is ableto operate.XPDR FAIL Red Transponder fail, turned on if B.I.T.E. fails and the transponder is not ableto receive interrogations or generate replies.CTRL PNL Red Control panel fail, turned on if the transponder is not receiving valid con-trol information on the selected control panel ARINC 429 input port.TOP ANT Red Top antenna fail, turned on if the top antenna B.I.T.E. test fails.BOT ANT Red Bottom antenna fail, turned on if the bottom antenna B.I.T.E. test fails.ALT Red Altitude fail, turned on if a valid altitude is not available from the selectedaltitude input or if the altitude compare fails (when enabled).9.2.3 Maintenance Display PagesThe diagram on the next page illustrates the operating modes and access matrix. Thesoftware version page is displayed only once at power up and is only displayed until theself-test starts.
Installation Manual Troubleshooting560-0405-00 Rev –December 14, 2001 Page 47© 2001 by UPS Aviation Technologies Inc.Startup DisplaySW VersionSelf Test StatusPROGRAMINPUTSEXTERNALINTERFACESMode S AddressSDI ProgramMax AirspeedAltitude TypeAntenna DelayAntenna BITEAntenna ProgramSelf Test Mode Normal ModeGillham AltitudeInputs*SynchroAltitude Inputs*ADC (429)Altitude Inputs*Control PanelInputsFlight ID InputDataLinkInterfaceTCAS InterfaceControl PanelTransponderFail StatusControl PanelFail StatusTop AntennaFail StatusBottom AntennaFail StatusAltitudeFail Status(x2)(x2)(x2)(x2)UPS AviationTechnologiesPower UpDISCRETEINPUTSAT7000 SelfTestRunningAltitude SelectAir/GroundOROR*Program Pin Dependent*Program Pin Dependent*Program Pin DependentFigure 15. Maintenance Displays9.2.3.1 Page Descriptions9.2.3.2 Display FunctionsThe front panel status display is used to display information useful for:a. aircraft installation checkoutb. isolating aircraft system/wiring problemsc. displaying B.I.T.E. test resultsd. transponder maintenance
Troubleshooting Installation ManualPage 48 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.9.2.3.3 Startup PageWhen the transponder is turned on, the following page is displayed for a moment (duringboot up), then the display changes to the ‘AT7000 Self Test Running’ display.The start up display is used to display the unit model number and main application soft-ware version.9.2.3.4 Self Test Running PageThe AT7000 Self Test page is displayed for three seconds every time ‘Self Test’ mode isinitiated.9.2.3.5 Self Test Status PagesThe ‘Self Test Status’ page displays the number of currently active fault types.9.2.3.6 Flight Legs Fault Status PageThe ‘Flight Legs Fault Status’ page displays the number fault types for the leg defined ascurrent leg – 0 to 9. '0' being the current leg and '9' being nine legs prior to the current.In the event an EEPROM log failure occurs, LOG FAILURE appears on the second line.The log failure only pertains to the leg attempting to be viewed.9.2.3.7 Transponder Fail StatusThe Transponder Fail Status page is used to display the failure status of the transponderwhen the transponder fail LED is turned on.Trnspndr Failure1) ICAO Address2) Transmitter3) Top RcvrUPS AVIATIONTECHNOLOGIESAT7000 Mode SSW Ver: 1.XXAT7000 Self TestRunningSelf Test Result0 FaultsPress TEST toView Legs Info
Installation Manual Troubleshooting560-0405-00 Rev –December 14, 2001 Page 49© 2001 by UPS Aviation Technologies Inc.If internal failures are detected (causing the XPDR FAIL LED to illuminate), then thecause of the failure will be displayed. Only one page will be displayed, with the threemost significant internal failures displayed.a. ICAO Addressb. Internal component of Transponderc. Top Transmitterd. Bottom Transmittere. Tx Synth Lockf. Rx Synth Lockg. Top Receiverh. Bottom Receiveri. Squitter Mon9.2.3.8 Control Panel Fail StatusThis display is used to display the failure status of the selected control panel input if afailure is detected and the control panel fail LED is illuminated.The first line is used to display which of the control panels is selected, either A or B. Thefailure is displayed on the second line, either “Invalid”, “Rate Failed”, or “No Data”.For flight leg results all three faults can be displayed one per line starting on the secondline. Both Control Panel A and B pages can be displayed if failures occurred on eachwhile they were selected.Control Panel ANo Data
Troubleshooting Installation ManualPage 50 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.9.2.3.9 Top Antenna Fail StatusThis display is used to display the top antenna BITE failure if a failure is detected and thetop antenna fail LED is illuminated.9.2.3.10 Bottom Antenna Fail StatusThis display is used to display the bottom antenna BITE failure if a failure is detected andthe bottom antenna fail LED is illuminated.9.2.3.11 Altitude Fail StatusThis display is used to display the altitude failure. The failure displayed is dependentupon the selection of the altitude type program input. The altitude source, either 1 or 2, is displayed on the first line.The altitude type is displayed on the second line: ADC (429), Gillham, or Synchro.The failure is displayed on the third line, depending on the type.If ADC (429) is selected, then the failures will be “Invalid” or “No data”.If Gillham is selected, then the failure will be “Invalid” if an invalid code is input, or“Compare Fail” if the altitude compare is enabled and the compare fails.If synchro is selected, then the failures will be “Invalid” if an invalid synchro or referenceinput is detected or “Flagged” if the synchro flag input indicates an invalid condition.For flight leg results all two faults can be displayed one per line starting on the secondline. Both Altitude Source 1 and Altitude Source 2 pages can be displayed if failures oc-curred for each while they were selected.Top AntennaBITE Test FailBottom AntennaBITE Test FailAltitude SRC #1Type: ADC (429)Invalid
Installation Manual Troubleshooting560-0405-00 Rev –December 14, 2001 Page 51© 2001 by UPS Aviation Technologies Inc.9.2.4 Normal ModeIn normal mode the pages are intended for system checkout or fault isolation when theaircraft is on the ground.9.2.4.1 Default PageThe transponder will always return to the default page. This occurs when test mode timesout, or if any other page is displayed in Normal Mode and a button has not been pressedin five minutes.9.2.4.2 Program InputsThe program inputs group is used to display the settings of each of the transponder’s rearpanel program inputs.9.2.4.3 Mode S AddressThis display is for decoding the 24-bit mode S address, displayed in octal and hexadeci-mal.PROGRAM INPUTSPRESS ←→↑↓ TESTUPS AVIATION TECH-NOLOGIESAT7000 Mode SPRESS ←→ or TESTMode S Address:OCT 12345670HEX 053977
Troubleshooting Installation ManualPage 52 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.9.2.4.4 SDI Program InputThis display is SDI program input as 2 bits binary.Possible numbers are 00, 01, 10 and 11.If 00 is displayed, then also display “Invalid” on the bottom line.9.2.4.5 Max Airspeed ProgramThis display is for the max airspeed program input.The airspeed displays are:0) invalid (0 is not available)1) up to 75 knots2) 75 to 150 knots3) 150 to 300 knots4) 300 to 600 knots5) 600 to 1200 knots6) above 1200 knots7) invalid (7 is not assigned)9.2.4.6 Altitude Type ProgramThis is used to display the current altitude input type selected by the program pin inputs.The altitude selection displays are:0) ADC (429) ARINC 429 air data input1) SynchroSDI Program:00InvalidAltitude Type:ADC (429)Max Airspeed:150 to 300 knots
Installation Manual Troubleshooting560-0405-00 Rev –December 14, 2001 Page 53© 2001 by UPS Aviation Technologies Inc.2) Gillham3) Invalid9.2.4.7 Antenna Delay ProgramThis display is for the antenna delay program input.The delay selection displays are:0) 0 to 50 nsec1) 51 to 150 nsec2) 151 to 250 nsec3) 251 to 350 nsecThe antenna is either the bottom or top.9.2.4.8 Antenna BITE ProgramThis page is for the antenna BITE program input.The possible displayed antenna BITE selections are:0) Disabled1) Enabled9.2.4.9 Antenna ProgramThis page displays the antenna program input.Antenna Delay:Delay:51 to 150 nsecAnt: bottomAntenna BITE:Enabled
Troubleshooting Installation ManualPage 54 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.The antenna program selections are:0) Dual antenna1) Bottom only9.2.5 Discrete InputsThe Discrete Input group is used to display the status of the rear panel discrete inputs,such as the altitude select and control panel select.These displays are used to display the state of each of the discrete inputs, grouped in thefollowing pages.Discrete Inputs Page 1:The top line is used to display the control panel selected, either A or B.The second line is used to display the current mode of the standby input, either “Standby”or “Active”.The third line is used to display the state of the functional test input, either “Test” or“Norm”Discrete Inputs Page 2:The top line is used to display the altitude source selection, either 1 or 2.Antenna Program:Dual AntennaDISCRETE INPUTSPress ←→↑↓ TESTCntrl Panel:AMode: StandbyFunc Test: TestAlt Select:1Alt Compare: onSync #1: ValidSync #2: Invalid
Installation Manual Troubleshooting560-0405-00 Rev –December 14, 2001 Page 55© 2001 by UPS Aviation Technologies Inc.The second line is used to display the state of the altitude compare input, either “on” or“off”.The third line is used to display the state of the synchro #1 valid flag input, either “valid”or “Invalid”.The fourth line is used to display the state of the synchro #2 valid flag input, either“valid” or “Invalid”.Discrete Inputs Page 3:The top line is used to display the state of the air/ground #1 input, either “air” or “gnd”.The second line is used to display the state of the air/ground #2 input, either “air” or“gnd”.9.2.6 External InterfacesThe external interfaces group is used to display the status of the rear panel interface in-puts, such as the altitude and control panel inputs.9.2.6.1 ADC Altitude InputsThis page is used to display the altitude and status from the air data computer inputs.The data is displayed for both the #1 and #2 inputs.The altitude is displayed in feet, with 1 foot resolution.The status of the input is displayed on the bottom line as:• Valid• Invalid (invalid status on 429 input data)• No data (no 429 altitude input data)Air/Gnd #1:airAir/Gnd #2: gndEXTERNAL INTER-FACESPress ←→↑↓ TEST429 Alt #115,475 feetValid
Troubleshooting Installation ManualPage 56 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.Note: During aircraft ground maintenance operation, only the selected altitude inputneeds to be displayed. During bench maintenance operation, all four altitude inputs willbe displayed.9.2.6.2 Gillham Altitude InputsThis page is used to display the altitude from the two Gillham altitude inputs.The data is displayed for both the #1 and #2 inputs.The altitude is displayed in feet, with a 100 foot resolution.The status of the input is displayed on the bottom line as:• Valid• Invalid (for an invalid Gillham code input)• Compare Fail (if the altitude compare is enabled and the compare fails)9.2.6.3 Synchro Altitude InputsThis page is used to display the altitude and status from the two synchro altitude inputsThe data is displayed for both the #1 and #2 inputs.The altitude is displayed in feet, with a 1 foot resolution.The status of the input is displayed on the 3rd line as:• Valid• Bad Ref (reference out of tolerance)• Bad Input (XYZ inputs out of tolerance… sig level, …)The status of the corresponding valid flag input is displayed on the bottom line as:• Valid• InvalidGillham Alt #115,500 feetValidSynchro Alt #115,475 feetInput: ValidFlag: Valid
Installation Manual Troubleshooting560-0405-00 Rev –December 14, 2001 Page 57© 2001 by UPS Aviation Technologies Inc.9.2.6.4 Control Panel InputsThese pages are used to display the info and status from the two control panel inputs.The data is displayed for both A and B control panel inputs.On the second line, the ident code displayed as four character octal, followed by “ident”if SPI is enabled.The operation mode is displayed on the third line as follows:• Standby• AltOff (active, altitude reporting is off)• Active (active, altitude reporting is enabled)• NotSelectedThe status of the input is displayed on the bottom line as:• Valid• Invalid (invalid status on the 429 input data)• No data (no 429 control panel data)9.2.6.5 Flight ID InputThis page is used to display the status of the flight ID input.The third line is used to display the current setting of the input:• Flight ID (if the input is set to the flight ID function)• Nav Data (if the input is set to the Nav data input function)The status of the input is displayed on the bottom line as:• Valid• Invalid (invalid status on the input data)• No data (no input data)Control PanelAIdent: 1200identMode: ActiveValidFlight ID InputFlight IDValid
Troubleshooting Installation ManualPage 58 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.9.2.6.6 DataLink InterfaceThis page is used to display the status of the ARINC 429 data link interface.The status of the input is displayed on the bottom line as:• Valid• Invalid (invalid status on the input data)• No data (no input data)9.2.6.7 TCAS InterfaceThis page is used to display the status of the ARINC 429 TCAS interface.The third line is used to display the current setting of the input:• Standby• TA Only• TA/RA• TCAS IV• (BLANK when No Data)The status of the input is displayed on the bottom line as:• Valid• Invalid (invalid status on the input data)• No data (no input data)DatalinkInterfaceValidTCAS InterfaceMode: StandbyStatus: Valid
Installation Manual Troubleshooting560-0405-00 Rev –December 14, 2001 Page 59© 2001 by UPS Aviation Technologies Inc.9.3 TroubleshootingThe transponder has several system checks that can assist in troubleshooting. A self-testcan be conducted from the transponder front panel and from the control panel.9.3.1 System TestBefore conducting this test, verify the following:• Air data computer breaker(s) are closed and the unit(s) function• Mode S transponder breaker is closed• Transponder control panel breaker is closedThe table on the following page offers some troubleshooting information. The screensare accessed in the ‘Self Test Mode’. To enter the ‘Self Test Mode’, at power up, pressthe test button on the front panel. The start of ‘Self Test Mode’ turns all six front panellights ON for 3 seconds and displays the ‘Self Test Running’ page.The panel lamps and display indicates the current faults until the test mode ends. Press-ing the test button while in test mode displays faults beginning with current flight leg.Subsequent presses of the test button cycles through the flight leg faults for up to tenflight legs.At the end of the ‘Self Test Mode’, the lamps all turn off and the user interface changesto the normal mode.
Troubleshooting Installation ManualPage 60 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.Table 9 - Troubleshooting GuideProblem Cause Corrective ActionXPDR PASS LED is illumi-nated. Normal operation. No action necessary.XPDR FAIL LED is illumi-nated. The ‘Trnspndr Failure’ page will showup to three most significant failures:1. ICAO Address2. Internal component of Transponder3. Top Transmitter4. Bottom Transmitter5. Tx Synth Lock6. Rx Synth Lock7. Top Receiver8. Bottom Receiver9. Squitter MonCTRL PNL failure light is il-luminated and the ‘ControlPanel Fail Status’ page reads‘Invalid’, ‘Rate Failed’ or ‘NoData’.Control panel not connected. Check wiring. Re-place faulty controlpanel.TOP ANT failure light is illu-minated and ‘Top Antenna’page reads ‘BITE Test Fail’.Top antenna not connected correctly.BOT ANT failure light is il-luminated and ‘Bottom An-tenna’ page reads ‘BITE TestFail’.Bottom antenna not connected correctly.ALT SIG failure light is illu-minated. The ‘Altitude FailStatus’ will read ‘Invalid’ or‘No Data’ if the type of alti-tude source is ADC (429). IfGillham is selected as thesource the display will read‘Invalid’ or ‘Compare Fail’. IfSynchro is selected as thesource, the failures will be ‘In-valid’ or ‘Flagged’.
Installation Manual Periodic Maintenance560-0405-00 Rev –December 14, 2001 Page 61© 2001 by UPS Aviation Technologies Inc.Section 10 - Periodic Maintenance10.1 MaintenanceThere are no internal manual adjustments needed.
Periodic Maintenance Installation ManualPage 62 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.NOTES
Installation Manual Environmental Qualifications560-0405-00 Rev –December 14, 2001 Page 63© 2001 by UPS Aviation Technologies Inc.Section 11 - Environmental QualificationsThe AT7000 has been tested to the following environmental categories per proceduresdefined in RTCA/DO-160D.Table 10 - Environmental RequirementsNomenclature: AT7000Part No.: 430-6091-100TSO No.: TSO C112Manufacturer:UPS Aviation Technologies2345 Turner Road SESalem, Oregon 97302Environment Section Category CommentTemperature and Altitude 4A2 Operating Temp ............ -20°C to +70°CShort Time Hi Temp ..... to +70°CCooling .........................RequiredGround survival temp ... -55°C to +85°CAltitude ......................... 55,000 feetOverpressure ................. –15,000 feetDecompression ............. 55,000 feetTemperature Variation 5BMinimum 5°C per minuteHumidity 6BSevere humidity environment.Operational Shocks and CrashSafety 7BTested for operational shock and crash safety.Aircraft type 5, test type RVibration 8S & T S (curves B and M), T (curves B, B1 and R)Explosion Proofness 9XNot applicable, no test requiredWaterproofness 10 XNot applicable, no test requiredFluids Susceptibility 11 XNot applicable, no test requiredSand and Dust 12 XNot applicable, no test requiredFungus Resistance 13 XNot applicable, no test requiredSalt Spray 14 XNot applicable, no test requiredMagnetic Effect 15 Z< 0.3 meterPower Input 16 A & E 28 volt DC and 115 volt 400 Hz ACVoltage Spike 17 AAudio Frequency Conducted Sus-ceptibility - Power Inputs 18 A & EInduced Signal Susceptibility 19 CZ is minimum requirement, C is the goalRadio Frequency Susceptibility(Radiated and Conducted) 20 VU is minimum requirement, V is the goalEmission of Radio Frequency En-ergy 21 MLightning Induced Transient Sus-ceptibility 22 A3C2E2Pin injectionUnshielded cablesShielded cablesLightning Direct Effects 23 XNot applicable, no test requiredIcing 24 XNot applicable, no test requiredElectrostatic Discharge (ESD) 25 A
Environmental Qualifications Installation ManualPage 64 560-0405-00 Rev –December 14, 2001© 2001 by UPS Aviation Technologies Inc.NOTES

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