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
AT7000 Mode S Transponder Installation Manual December 14, 2001 560-0405-00 Rev. -- Installation Manual AT7000 Mode S Transponder 2001 by UPS Aviation Technologies All rights reserved. Printed in the USA UPS Aviation Technologies CAGE Number 0XCJ6 No part of this document may be transmitted, reproduced, or copied in any form or by any means without the prior written consent of UPS Aviation Technologies. UPS Aviation Technologies and Aviation Technologies are registered trademarks of UPS Aviation Technologies UPS Aviation Technologies PO Box 13549 Salem, OR 97309 Phone: 503.581.8101 800.525.6726 Fax: 503.364.2138 2345 Turner Rd., SE Salem, OR 97302 USA In Canada: 800.654.3415 560-0405-00 Rev – December 14, 2001 Installation Manual AT7000 Mode S Transponder HISTORY OF REVISIONS Revision EN -- EN7149 Date Description Dec 14/01 Initial Release ORDERING INFORMATION To receive additional copies of this publication, order part # 560-0405-00, AT7000 Mode S Transponder Installation Manual. RELATED DOCUMENTS AT7000 Mode S Transponder Factory Service Manual 560-7016-000 560-0405-00 Rev – December 14, 2001 Installation Manual AT7000 Mode S Transponder NOTES 560-0405-00 Rev – December 14, 2001 Installation Manual AT7000 Mode S Transponder Record of Revisions For each revision, insert the revised pages into your manual and discard the replaced pages. On this record page, note the revision number and date, date pages were inserted into the manual, and the initials of the person inserting the pages. Revision Number Revision Date Date Inserted By Revision Number Revision Date 560-0405-00 Rev – December 14, 2001 Date Inserted By Page i © 2001 by UPS Aviation Technologies Inc. AT7000 Mode S Transponder Installation Manual List of Effective Pages Section and Page Revision Title 00 Copyright page 00 History of Revisions 00 List of Effective Pages 00 Table of Contents 00 Sec. 1. Introduction 00 Page 1 00 Page 2 00 Page 3 00 Page 4 00 Sec. 2. System Description 00 Page 5 00 Page 6 00 Page 7 00 Page 8 00 Page 9 00 Page 10 00 Page 11 00 Page 12 00 Sec. 3. Installation Page 13 00 Page 14 00 Page 15 00 Page 16 00 Page 17 00 Page 18 00 Page 19 00 Page 20 00 Page 22 00 Page 23 00 Page 24 00 Page 25 00 Page 26 00 Page 27 00 Page 28 00 Page 29 00 Page 30 00 Page 31 00 Page 32 00 Page 33 00 Page 34 00 Page 35 00 Page 36 00 Section and Page Revision Page 37 00 Sec. 4. Post-Install Checkout Page 38 00 Page 39 00 Sec. 5. Equipment Rem. and Rep. Page 40 00 Page 41 00 Sec. 6. Operation Page 42 00 Page 43 00 Sec. 7. Specifications Page 44 00 Page 45 00 Page 46 00 Page 47 00 Sec. 8. Limitations Page 48 00 Page 49 00 Sec. 9. Troubleshooting Page 50 00 Page 51 00 Page 52 00 Page 53 00 Page 54 00 Page 55 00 Page 56 00 Page 57 00 Page 58 00 Page 59 00 Page 60 00 Page 61 00 Page 62 00 Page 63 00 Page 64 00 Page 65 00 Page 66 00 Page 67 00 Sec. 10. Periodic Maintenance Page 68 00 Page 69 00 Sec. 11. Environmental Qualifications Page 70 00 Page 71 00 Page ii 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual AT7000 Mode S Transponder TABLE OF CONTENTS SECTION 1 - INTRODUCTION ................................................................................................................ 1 1.1 ABOUT THIS MANUAL .......................................................................................................................1 1.2 SYSTEM DESCRIPTION ........................................................................................................................1 1.2.1 System Overview ........................................................................................................................1 1.2.2 AT7000 Mode S Transponder ....................................................................................................2 1.2.3 Control Panel.............................................................................................................................2 1.2.4 Antenna ......................................................................................................................................2 1.2.5 Altitude Source...........................................................................................................................2 1.2.6 Data Link Processor ..................................................................................................................2 1.2.7 TCAS ..........................................................................................................................................2 1.3 FUNCTIONAL OPERATION...................................................................................................................3 1.4 REGULATORY COMPLIANCE ...............................................................................................................3 1.4.1 CFR 47, Part 87 (FCC)..............................................................................................................3 1.4.2 TSO C112...................................................................................................................................3 1.4.3 ARINC 718-4 and ARINC 718A .................................................................................................3 SECTION 2 - TRANSPONDER DESCRIPTION ..................................................................................... 5 2.1 GENERAL ...........................................................................................................................................5 2.2 OVERVIEW .........................................................................................................................................5 2.3 AT7000 PRODUCT SUMMARY............................................................................................................6 2.3.1 Gillham to A429 Serial Data Converter.....................................................................................7 2.3.2 Inputs to the AT7000 for Extended Squitter Position Reports....................................................7 2.4 DISPLAY / CONTROL ..........................................................................................................................8 2.5 DATA LOADER INTERFACE.................................................................................................................8 2.6 BUILT-IN TEST EQUIPMENT (BITE) AND DIAGNOSTICS .....................................................................8 2.6.1 Self-Tests ....................................................................................................................................8 2.6.2 Status Indicators.........................................................................................................................9 2.6.3 Maintenance and BITE Data......................................................................................................9 SECTION 3 - INSTALLATION................................................................................................................ 11 3.1 PRE-INSTALLATION INFORMATION ..................................................................................................11 3.2 EQUIPMENT REQUIRED.....................................................................................................................11 3.3 MECHANICAL INSTALLATION...........................................................................................................11 3.3.1 Location of LRUs .....................................................................................................................11 3.3.2 AT7000 Provisions...................................................................................................................11 3.3.3 Antenna Provisions ..................................................................................................................12 3.4 ELECTRICAL INSTALLATION .............................................................................................................13 3.4.1 Middle Plug..............................................................................................................................17 3.4.2 Bottom Plug..............................................................................................................................21 3.4.3 Program Pin Inputs..................................................................................................................23 3.4.4 SDI Program ............................................................................................................................23 3.4.5 Max Airspeed Program ............................................................................................................23 3.4.6 Antenna Delay Program ..........................................................................................................24 3.4.7 Antenna Program .....................................................................................................................25 3.4.8 Antenna BITE Program............................................................................................................25 3.4.9 Altitude Type Selection.............................................................................................................25 3.5 INTERFACE CONNECTIONS ...............................................................................................................25 3.5.1 Discrete I/O Levels...................................................................................................................25 3.5.2 Gillham Code Altitude Input ....................................................................................................26 3.5.3 Synchro Altitude Input..............................................................................................................26 3.5.4 ARINC 706 Air Data Inputs .....................................................................................................26 3.5.5 Control Panel Input..................................................................................................................26 3.5.6 Standby Input ...........................................................................................................................27 3.5.7 Air/Ground Discrete Inputs......................................................................................................27 3.5.8 Functional Test Discrete Input.................................................................................................27 3.5.9 Altitude Input Selection ............................................................................................................28 560-0405-00 Rev – December 14, 2001 Page iii © 2001 by UPS Aviation Technologies Inc. AT7000 Mode S Transponder Installation Manual 3.5.10 Altitude Compare .....................................................................................................................28 3.5.11 Transponder Fail Outputs........................................................................................................28 3.5.12 Flight ID Input .........................................................................................................................29 3.5.13 Data Link Interface ..................................................................................................................29 3.5.14 Downlinked Aircraft Parameters (DAPS) ................................................................................29 3.5.15 TX / XT Coord TCAS Interface ................................................................................................29 3.6 DATA LOADER INTERFACE...............................................................................................................30 SECTION 4 - POST-INSTALLATION CHECKOUT............................................................................ 33 4.1 KEY PIN ORIENTATION ....................................................................................................................33 PRE-INSTALLATION CHECKOUT PROCEDURES...........................................................................................33 SECTION 5 - EQUIPMENT REMOVAL AND REPLACEMENT....................................................... 35 5.1 REMOVAL.........................................................................................................................................35 5.1.1 Transponder .............................................................................................................................35 5.2 REPLACEMENT .................................................................................................................................35 5.2.1 Transponder .............................................................................................................................35 SECTION 6 - OPERATION ...................................................................................................................... 37 SECTION 7 - SPECIFICATIONS ............................................................................................................ 39 7.1 ELECTRICAL .....................................................................................................................................39 7.2 PHYSICAL .........................................................................................................................................39 7.3 ENVIRONMENTAL .............................................................................................................................40 7.4 TRANSPONDER PERFORMANCE ........................................................................................................40 SECTION 8 - LIMITATIONS................................................................................................................... 43 8.1 INSTALLATION .................................................................................................................................43 SECTION 9 - TROUBLESHOOTING ..................................................................................................... 45 9.1 INTRODUCTION AND OVERVIEW.......................................................................................................45 9.1.1 Introduction..............................................................................................................................45 9.1.2 Overview ..................................................................................................................................45 9.2 INTERFACES .....................................................................................................................................46 9.2.1 Buttons .....................................................................................................................................46 9.2.2 Test Status LEDs ......................................................................................................................46 9.2.3 Maintenance Display Pages.....................................................................................................46 9.2.4 Normal Mode ...........................................................................................................................51 9.2.5 Discrete Inputs .........................................................................................................................54 9.2.6 External Interfaces ...................................................................................................................55 9.3 TROUBLESHOOTING .........................................................................................................................59 9.3.1 System Test ...............................................................................................................................59 SECTION 10 - PERIODIC MAINTENANCE ...................................................................................... 61 10.1 MAINTENANCE .................................................................................................................................61 SECTION 11 - ENVIRONMENTAL QUALIFICATIONS ................................................................. 63 Page iv 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual AT7000 Mode S Transponder LIST OF ILLUSTRATIONS FIGURE 1 -- AT7000 SYSTEM BLOCK DIAGRAM ............................................................................................. 1 FIGURE 2 – FRONT PANEL OF AT7000 ............................................................................................................ 6 FIGURE 3 – POTENTIAL EQUIPMENT LOCATIONS........................................................................................... 11 FIGURE 4 - ARINC 600 4 MCU MOUNTING TRAY ....................................................................................... 12 FIGURE 5 – TOP PLUG INTERCONNECT DESCRIPTION (SHEET 1) ................................................................... 13 FIGURE 6 –TOP PLUG CONNECTOR LAYOUT ................................................................................................. 15 FIGURE 7 – MIDDLE PLUG INTERCONNECT DESCRIPTION (SHEET 1)............................................................. 17 FIGURE 8 – MIDDLE PLUG CONNECTOR LAYOUT ......................................................................................... 19 FIGURE 9 – BOTTOM PLUG INTERCONNECT DESCRIPTION ............................................................................ 21 FIGURE 10 – BOTTOM PLUG CONNECTOR LAYOUT ....................................................................................... 22 FIGURE 11 – DATA LOADER .......................................................................................................................... 32 FIGURE 12 – REMOVAL OF UNIT FROM TRAY................................................................................................ 35 FIGURE 13 – AT7000 DIMENSIONS ............................................................................................................... 40 FIGURE 14. AT7000 MODE S TRANSPONDER .............................................................................................. 45 FIGURE 15. MAINTENANCE DISPLAYS .......................................................................................................... 47 LIST OF TABLES TABLE 1 - EQUIPMENT FOR INSTALLATION ................................................................................................... 11 TABLE 2 - ANTENNA MINIMUM SPACING ...................................................................................................... 12 TABLE 3 - SDI PROGRAM PINS..................................................................................................................... 23 TABLE 4 - MAX AIRSPEED PROGRAM........................................................................................................... 24 TABLE 5 - ANTENNA DELAY PROGRAM ....................................................................................................... 24 TABLE 6 - ALTITUDE TYPE SELECTION ........................................................................................................ 25 TABLE 7 - DATA LOADER PLUG ................................................................................................................... 30 TABLE 8 - STATUS LEDS SUMMARY ............................................................................................................ 46 TABLE 9 - TROUBLESHOOTING GUIDE.......................................................................................................... 60 TABLE 10 - ENVIRONMENTAL REQUIREMENTS ............................................................................................. 63 560-0405-00 Rev – December 14, 2001 Page v © 2001 by UPS Aviation Technologies Inc. AT7000 Mode S Transponder Installation Manual NOTES Page vi 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Introduction AT7000 Mode S Transponder Section 1 - Introduction The AT7000 is a Mode S Data Link Transponder that provides surveillance functions to ground-based and airborne interrogators. It responds to ATCRBS interrogations as well. 1.1 About This Manual This manual describes the installation of the UPS Aviation Technologies AT7000 Mode S 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 Administration (FAA) to install avionics devices. It includes installation and checkout procedures for the UPS Aviation Technologies AT7000 Mode S Transponder. 1.2 1.2.1 System Description System Overview TCAS* Airborne Data Link Processor (ADLP)* TCAS *Optional *Optional Control Panel AT7000 Mode S Transponder 1090 Receiver (ADSB) ADSB Air Data Computer (ADC) Central Maintenance Computer (CMC)* ATC Radar Interrogator *Optional (Not supported in initial release) AT7000 System Block Diagram Airborne System Figure 1 -- AT7000 System Block Diagram 560-0405-00 Rev – December 14, 2001 Page 1 © 2001 by UPS Aviation Technologies Inc. AT7000 Mode S Transponder 1.2.2 Introduction AT7000 Mode S Transponder The AT7000 transponder is packaged in a 4-MCU (Modular Concept Unit) outlined as defined in ARINC Characteristic 600-7. The basic mechanical chassis is constructed of lightweight aluminum alloy sheet metal. The unit uses forced air cooling per ARINC 404 or 600. ARINC standard LRU restraints are used as means of holding the transponder in the mounting rack or tray. The maximum weight of the transponder is 11.5 pounds (5.2 kilograms). The rear connector receptacle is a size 2-shell assembly with inserts and contacts as defined in ARINC Characteristic 718-4/718A. The unit features a fixed carrying handle, self-test switch with discrete LED STATUS annunciators, and a LCD display for system setup and verification. 1.2.3 Control Panel The control panel for the Mode S System provides for mode control of the ATC Transponders. Communication with the Mode S Transponders is accomplished via an ARINC 429 bus as defined in ARINC Characteristic 718. Control panel functions includes a 4096-ident code selection and display, altitude source and mode control switch, and selection between two onboard transponders. The control panel also input FID into the transponder. 1.2.4 Antenna When installing the transponder antennas, a TSO’d antenna should be selected. Two antennas are required. Having two antennas (one on top of the aircraft and one on the bottom) provides the best coverage for receiving interrogations from ground radar, planes above, and below. L-Band type recommended antennas are P/N S65-5366-7L, manufactured by Sensor Systems and P/N DM N150-2, manufactured by DM Antenna Technologies. 1.2.5 Altitude Source The transponder contains dual inputs for acceptable types of altitude sources. The pin configuration selection specifies which of the two inputs are used for obtaining altitude information. Altitude sources are ADC (429), Synchro, or Gillham. The input uses a ground/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 Processor Four high speed ARINC 429 busses are provided for interfacing to a Mode S Airborne Data Link Processor (ADLP). The Comm A/B input and Comm A/B output busses are used for transferring messages to and from the ADLP. 1.2.7 TCAS The AT7000 contains an interface that allows it to work with an onboard TCAS II system. The interface consists of two ARINC 429 high speed data busses, an XT Coordination bus that is an output from the transponder to TCAS, and a TX Coordination bus that is an output from TCAS to the transponder. Page 2 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Introduction 1.3 AT7000 Mode S Transponder Functional Operation Mode S System operation begins when aircraft power is applied. An initial self-test is performed automatically upon power-up and is completed in approximately one second. Self-testing of the transponder occurs continuously while powered on. If a transponder failure occurs, it is indicated on the control panel. Other failures are indicated via front panel mounted LEDs on the transponder, however, these failure indications are not available to the pilot. All failures, whether hard or intermittent, are recorded in the transponder maintenance memory for analysis by maintenance personnel. 1.4 Regulatory Compliance The following standards are described in relationship to the functioning and certification of the AT7000. 1.4.1 CFR 47, Part 87 (FCC) Aviation Services, Subpart D, Technical Requirements 1.4.2 TSO C112 The AT7000 complies with TSO C112, Air Traffic Control Radar Beacon System/Mode Select (ATCRBS/Mode S) Airborne Equipment. 1.4.3 ARINC 718-4 and ARINC 718A The AT7000 complies with ARINC Characteristic 718-4 and 718A, Mark 3 Air Traffic Control Transponder. The AT7000 meets the minimum subset of ARINC 718A and is software upgradeable for most DAPS parameters. See Transponder Description, Section 2. 560-0405-00 Rev – December 14, 2001 Page 3 © 2001 by UPS Aviation Technologies Inc. AT7000 Mode S Transponder Introduction NOTES Page 4 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual System Description Section 2 - Transponder Description 2.1 General This section defines the system functionality for the AT7000 Mode S transponder. It is a Level 2es transponder indicating that it performs basic Mode S functions, and is also capable of transmitting extended squitters with encoded aircraft information to support ADS-B functions. The unit is also upgradeable to ICAO Level 5 (Downlinked Aircraft Parameters, (DAPS)) capability through software upgrades. 2.2 Overview The AT7000 transponder is a full-featured Mode S transponder in an ARINC 600 form factor that has been designed with a built-in capability for future growth. This transponder 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 serves as an integral part of a complete ADS-B system. ADS-B is currently certified for use as a traffic 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 described in DO-181B and EUROCAE ED-73A. This also meets Eurocae elementary surveillance requirements including SI capability (six bit Mode S sensor interrogator codes) and flight ID transmission. Flight ID (FID) may be input to the AT7000 for extended squitter transmission by either external serial data interface or by using a Gables transponder control panel capable of accepting and transmitting FID information. TCAS is fully supported with antenna diversity (top and bottom) antenna ports. The AT7000 is designed to operate with all ARINC 718/735 and conforming TCAS II computers. 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 for display of descriptive messages allowing for far greater comprehensive testing and troubleshooting capabilities on aircraft. Software on board the AT7000 is certified to DO-178B Level B. Software updates can be completed via an RS232 serial data and will be upgraded to interface with an ARINC 615 data loader. The data loader port is located on the front panel of the unit. 560-0405-00 Rev – December 14, 2001 Page 5 © 2001 by UPS Aviation Technologies Inc. System Description Installation Manual XPDR PASS XPDR FAIL CTRL PNL TOP ANT MAINTENANCE DISPLAY BOT ANT ALT TEST AT7000 Mode S Data Link Transponder Model: AT7000 DATA LOADER Mode S Transponder Software PN: Map/Database 430-6091 - 00 - 00 HW Mod A B C D E F G H J K L M N P R S T U V W X Y Z AA AB AC AD AE AF AGAH AJ AK AL AMAN Weight 10.0 lbs. SW Mod A B C D E F G H J K L M N P R S T U V W X Y Z AA AB AC ADAE AF AG AH AJ AK AL AMAN barcode of serial number SN '1234567' UPS Aviation Technologies, TSO-C112 Class 2A7, 121, 011 RTCA/DO-178B Software Level B RTCA/DO-160D Env. Cat. FCC ID xxxxxxx Salem OR USA Figure 2 – Front Panel of AT7000 2.3 AT7000 Product Summary The 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 4 MCU size form factor • ATCRBS and Mode S operation • TSO-C112 certification • Includes Comm A and Comm B operation, (Comm C, Comm D, and DAPS capable.) • 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 diagnostics Page 6 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual System Description 2.3.1 Gillham to A429 Serial Data Converter The AT7000 includes a Gillham code to ARINC 429 serial data converter integral to the unit 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 Reports Some users of the AT7000 may not wish to install an ADLP concurrently with the transponder, but wish to output basic position reports to comply with future European requirements. This may be accomplished by inputting the required ARINC labels to the transponder. The minimum label set is as follows for airborne position squittering: Minimal Necessary Labels Label # Description Minimum Rate Alternate Labels 110 (120) Latitude (Fine) 5 Hz 310 111 (121) Longitude (Fine) 5 Hz 311 150 Time Word 5 Hz 140 Fractional Seconds (should be last word of data block) 5 Hz 130 HPL 5 Hz 377 Equipment ID – must be 142 0.5 Hz 560-0405-00 Rev – December 14, 2001 247 Page 7 © 2001 by UPS Aviation Technologies Inc. System Description Installation Manual Minimal Necessary Labels (Only Type 1&2 or Type 3&4 Required) Label # Description 174 NS Velocity – Type Code 5 Hz 1&2 103 and 112 EW Velocity – Type Code 1&2 103 and 112 166 Minimum Rate 5 Hz Alternate Labels (or 311 and 312) (or 311 and 312) OR 320 Magnetic Heading – Type 5 Hz Code 3&4 210 True Airspeed – Type Code 3&4 (from ADC) 5 Hz 206 2.4 Display / Control The transponder is designed to work with a standard transponder control panel. The control panel may output FID for transmissions. 2.5 Data Loader Interface The transponder includes a front panel mounted data loader interface connector. The interface connector will include an RS-232 serial interface for use with a PC. An ARINC 615 input is provisioned, but not implemented in the software for the initial product release. 2.6 Built-In Test Equipment (BITE) and Diagnostics The transponder includes a built-in test and diagnostics to automatically test the transponder functions at system power up and monitor the operation performance during normal operation. 2.6.1 Self-Tests The built-in tests include the following and are completed at power up of the transponder. a) power supply voltages b) memory checks c) transmitter (monitor replies) d) synthesizers e) transponder interfaces f) top and bottom antenna test Page 8 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual 2.6.2 System Description Status Indicators The transponder includes status indicators on the front panel of the unit that can be easily viewed with the unit installed in its standard mounting. The purpose of the status indicators 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/fail b) control panel failure c) top antenna failure d) bottom antenna failure e) altitude compare failure The unit also has a LCD front panel display that allows for descriptive text messages to be displayed for the purpose of determining aircraft system faults, as well as transponder faults. 2.6.3 Maintenance and BITE Data The 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 count c. airframe cycle count (air/ground cycle count) d. fault identification (if applicable) 560-0405-00 Rev – December 14, 2001 Page 9 © 2001 by UPS Aviation Technologies Inc. System Description Installation Manual NOTES Page 10 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Installation Section 3 - Installation This section describes the installation of the AT7000 Mode S Transponder. 3.1 Pre-Installation Information The transponder can be mounted in any convenient location in the E/E bay; however, it should be mounted within 50 feet of the antenna unless a low-loss coaxial cable is used to maintain a worst case loss of 3 dB per ARINC 718-4/718A. Top and bottom coaxial run length differences can be compensated for by use of the antenna delay program pins. See Figure 4, TP3C through TP3F The unit can utilize external cooling air in accordance with ARINC 600, ARINC 404, or operate in convection cooled environments. However cooled, the airflow rate provided to the transponder should be 13 kg/hr and the pressure drop of the coolant air flow through the equipment should be 5 + 3mm of water. 3.2 Equipment Required Table 1 - Equipment for Installation 3.3 3.3.1 LRU Mating Connector Qty/System AT7000 NSXN2P203X0105 Mechanical Installation Location of LRUs The AT7000 is located in the E/E bay. The Control Panel is located in the cockpit. Figure 3 – Potential Equipment Locations 3.3.2 AT7000 Provisions The AT7000 is mounted in a 4 MCU mounting tray per ARINC 600. See Figure 3. 560-0405-00 Rev – December 14, 2001 Page 11 © 2001 by UPS Aviation Technologies Inc. Installation Installation Manual 3.3.2.1 Mounting Tray Figure 4 - ARINC 600 4 MCU Mounting Tray 3.3.3 Antenna Provisions Install antenna in accordance with manufacturer specifications. Sealant should be applied as required to the antenna base to prevent leakage of water and condensation while also preventing corrosion. Any sealant or aerodynamic smoother used around the edge of the antenna base must be applied only after the antenna has been bolted and secured to the aircraft. Each antenna should have a maximum of 2.5 milli-ohm ground bond resistance. Table 2 - Antenna Minimum Spacing Antenna Minimum Spacing DM-N150-2 (Dorne-Margolin P/N) 20” from other L-band antennas in same S65-5366-7L (Sensor Systems P/N) range. Or equivalent L-Band Antenna Page 12 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual 3.4 Installation Electrical Installation Reference Section 3.5.2 Signal Name A1 A2 A4 B1 B2 Gillham Code Altitude Input #2 B4 C1 C2 C4 D2 3.5.14 TP 2A TP 2B DAPS Input ARINC 429 TP 2C TP 2D Hardware Provisioned A Output ARINC 429 B TP 2E TP 2F TP 2G TP 2H Reserved Discrete Input #1 TP 2J Gillham Code Altitude Input #2 D4 TP 2K Reserved Discrete Output TP 3A Transponder Fail Output #2 TP 3B 3.5.11.2 Top/Bot Common TP 3C TP 3D TP 3E TP 3F 3.4.4 SDI Program A Common TP 3G TP 3H TP 3J 3.5.2 Gillham Code Altitude Input #2 Common TP 3K 3.5.3 X course Y course Z course Ref H Synchro Altitude Input #1 Ref C X fine Y fine Z fine flag TP 4A TP 4B TP 4C TP 4D TP 4E TP 4F TP 4G TP 4H TP 4J 3.4.6 Antenna Cable Delay Program Equipment Connection TP 1A TP 1B TP 1C TP 1D TP 1E TP 1F TP 1G TP 1H TP 1J TP 1K *MSP Bus Input ARINC 429 Reserved #1 Output ARINC 429 3.5.2 Pin No. From Airborne Data Link Processor Unit (LDPU) From Encoding Altimeter #2 To Mode S Control Panel J1-12 From Air Data Computer #1 *Optional Figure 5 – Top Plug Interconnect Description (Sheet 1) 560-0405-00 Rev – December 14, 2001 Page 13 © 2001 by UPS Aviation Technologies Inc. Installation Reference Section Installation Manual Signal Name TP 5A TP 5B TP 5C TP 5D TP 5E TP 5F To Pin 12D of TCAS Computer To Pin 12E of TCAS Computer XT Coordination TCAS 429 A TP 5G TP 5H To Pin 14F of TCAS Computer To Pin 14G of TCAS Computer TP 5J TP 5K To Air/Ground Relay NAV Data/Flight ID 429 Input Bus A TP 6A TP 6B From LDPU (ADLP) Reserved TP 6C TP 6D Reserved TP 6E TP 6F Max Airspeed Program 3.5.15 TX Coordination TCAS 429 3.5.15 3.5.12 Air/Ground Discrete Inputs #2 #1 Reserved Reserved 3.4.7 3.5.5 3.5.5.1 Equipment Connection COM 3.4.5 3.5.7 Pin No. TP 6G Antenna Program TP 6H TP 6J TP 6K Control Panel Input Bus #1 A TP 7A TP 7B Reserved TP 7C Control Panel Data Port Select TP 7D 3.5.5 Control Panel Input Bus #2 3.5.6 Standby 3.5.4 Air Data #1 ARINC 429 Input Reserved TP 7E TP 7F To Pin 22 of Control Panel (Optional) To Pin 23 of Control Panel (Optional) To Pin 22 of Control Panel To Pin 23 of Control Panel TP 7G TP 7H TP 7J To #1 Air Data Computer TP 7K Figure 4 – Top Plug Interconnect Description (Sheet 2) Page 14 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Installation TP C1 C2 C4 D2 Gillham Altitude Input #2 A1 A2 A4 Data Link Input (429 ip) XPDR Fail #2 (disc op) (disc op) (429 ip) Comm C/D Output Top/Btm 26VAC Ref (429 ip) (429) com (429 ip) RSVD IP #3 Cntl Pnl Select (disc ip) (disc ip) (disc ip) TX COORD XT COORD (429 ip) (429 pp) (429 op) (429 ip) ADL IP Sel (disc ip) Control Panel IP #2 ADL Output ------------------------ Fine ---------------------- ADL Input Control Panel IP #1 (429 ip) com RSVD IP #1 RSVD #1 Output D4 SDI Synchro Altitude #1 Flight ID / FMS (429 op) Max Airspeed Program B4 Antenna Delay Program ----------------------- Course --------------------X B2 Comm C/D Input RSVD Output B1 (disc ip) com Synchro Flag #1 RSVD IP #2 (disc ip) (disc ip) Air/Gnd #2 Air/Gnd #1 (disc ip) (disc ip) Antenna Program Reserved Standby com RSVD IP #4 Air Data #1 Input (429 ip) (prgm ip) (disc ip) Top Antenna 1-23-01 RAS Figure 6 –Top Plug Connector Layout 560-0405-00 Rev – December 14, 2001 Page 15 © 2001 by UPS Aviation Technologies Inc. Installation Installation Manual THIS PAGE INTENTIONALLY LEFT BLANK Page 16 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual 3.4.1 Reference Section 3.4.3.1 Installation Middle Plug Signal Name Pin No. Address 1 Address 2 Address 3 Address 4 Address 5 Address 6 Address 7 Address 8 Address 9 Address 10 Address 11 Address 12 Reserved Mode S Address Address 13 Address 14 Address 15 Address 16 Address 17 Address 18 Address 19 Address 20 Address 21 Address 22 Address 23 Address 24 Address Com Reserved #1 ARINC 429 Input MP 1A MP 1B MP 1C MP 1D MP 1E MP 1F MP 1G MP 1H MP 1J MP 1K MP 2A MP 2B MP 2C MP 2D MP 2E MP 2F MP 2G MP 2H MP 2J MP 2K MP 3A MP 3B MP 3C MP 3D MP 3E MP 3F MP 3G 3.5.1.1 Functional Test Discrete Input MP 3H 3.5.10.2 Altitude Compare Fail Output MP 3J 3.5.11.1 XPDR Fail #1 Output MP 3K 3.5.2 Gillham Code Altitude Input #1 A1 A2 A4 B1 B2 B4 C1 C2 C4 D2 3.5.4 Air Data #2 ARINC 429 Input Reserved Data Link 429 Output Equipment Connection Reserved for mode control panel or other DAPS inputs. MP 4A MP 4B MP 4C MP 4D MP 4E MP 4F MP 4G MP 4H MP 4J MP 4K From Altimeter MP 5A MP 5B From #2 Air Data Computer MP 5C MP 5D Reserved for inputs for DAPS MP 5E MP 5F MSP Bus to LDPU Figure 7 – Middle Plug Interconnect Description (Sheet 1) 560-0405-00 Rev – December 14, 2001 Page 17 © 2001 by UPS Aviation Technologies Inc. Installation Reference Section 3.5.10.1 3.6 Installation Manual Signal Name Pin No. Altitude Compare Input MP 5G DL/DHL Program Pin MP 5H 3.4.8 Antenna BITE Enable Program Program Pin MP 5J 3.5.2 Gillham Code Altitude Input #1 D4 MP 5K 3.5.9 3.4.9 3.5.2 3.5.3 Equipment Connection To Pin 17 of Control Panel Maintenance Data 429 Input MP 6A MP 6B Hardware Provisions Maintenance Data 429 Output MP 6C MP 6D Hardware Provisions MP 6E To Pin 16 of Control Panel Altitude Input Source Selection Altitude Type Selection Program A COM MP 6F MP 6G MP 6H Reserved #2 ARINC 429 Input MP 6J Gillham Code Altitude Input #1 COM MP 6K X Course Y Course Z Course Ref H Synchro Altitude Input #2 Ref C X Fine Y Fine Z Fine Synchro #2 Reserved #2 IP 429 B Tied to MP 7K MP 7A MP 7B MP 7C MP 7D MP 7E MP 7F MP 7G MP 7H MP 7J Discrete Input MP 7K Tied to MP 6J Figure 6 – Middle Plug Interconnect Description (Sheet 2) Page 18 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Installation MP Mode S Address Input 10 11 12 13 14 15 16 17 18 19 20 Func Test Alt Cmpar Fail XPDR Fail #1 (disc ip) (disc op) (disc op) C1 C2 C4 D2 Alt Cmpar En DL / DLP Ant BITE (disc ip) (prgm ip) (prgrm ip) Rsrvd #1 IP (429 ip) 21 22 23 24 com Gillham Altitude Input #1 A1 A2 A4 Air Data #2 B1 B2 Reserved Data Link Output (429 ip) (429 op) Maint Data Input Maint Data Output (429 ip) (429 op) ---------------------- Course --------------------X B4 Alt Src Select (disc ip) Synchro Altitude #2 26VAC Ref Rsrvd #2 429 IP Altitude Type Select com ------------------------ Fine ----------------------X D4 com Syncrho Flag #2 Rsrvd #2 429 IP (disc ip) Bottom Antenna 1-23-01 RAS Figure 8 – Middle Plug Connector Layout 560-0405-00 Rev – December 14, 2001 Page 19 © 2001 by UPS Aviation Technologies Inc. Installation Installation Manual THIS PAGE INTENTIONALLY LEFT BLANK Page 20 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual 3.4.2 Installation Bottom Plug Signal Name Pin No. 115 VAC Input HOT BP 1 Future Spare BP 2 28 VDC Input Return BP 3 Future Spare BP 4 Future Spare BP 5 Future Spare BP 6 115 VAC Input Return BP 7 Signal Ground BP 8 Future Spare BP 9 28 VDC BP 10 Chassis Ground BP 11 Suppression BP 12 Suppression BP 13 Equipment Connection Figure 9 – Bottom Plug Interconnect Description 560-0405-00 Rev – December 14, 2001 Page 21 © 2001 by UPS Aviation Technologies Inc. Installation Installation Manual Bottom Plug Not Used 115 v AC power input 28VDC Power Input Return Not Used Hot (-) Not Used Not Used Signal Ground 28 VDC Power Input 115 vac Power (Aircraft DC Ground) Input Return Not Used 10 Chassis Ground (+) 11 (Aircraft DC Ground) Suppression Pulse Input 13 Suppression Pulse Input 12 (int. conx to pin 12) Figure 10 – Bottom Plug Connector Layout Page 22 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual 3.4.3 Installation Program Pin Inputs The transponder will require program pin connections defined by the particular installation. The transponder is programmed by connecting the appropriate input pins to common (ground) as defined in this section. 3.4.3.1 Mode S Address The 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 address input pins. For each “1” bit in the address, connect the corresponding address input to the address 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) is the LSB (least significant bit). The address is normally defined as an eight character octal code. In the United States, the Mode S address can be obtained from: Federal Aviation Administration FAA Aircraft Registry PO Box 25504 Oklahoma City, OK 73125 Telephone: (405) 954-3116 Fax: (405) 954-3548 3.4.4 SDI Program The SDI program inputs are used to identify the transponder system number. The transponder number is made by connecting the defined SDI inputs to the SDI common pin (TP 3J) as follows: Table 3 - SDI Program Pins Transponder # SDI Prgm B SDI Prgm A TP 3G TP 3H Not Applicable Open Open Open Common Common Open Common Common Common pin TP 3J 3.4.5 Max Airspeed Program The maximum (max) airspeed program pins are used to identify the aircraft’s maximum cruise airspeed capability. The maximum airspeed is programmed by connecting the maximum airspeed program pins to the common pin (TP 5D) as follows: 560-0405-00 Rev – December 14, 2001 Page 23 © 2001 by UPS Aviation Technologies Inc. Installation Installation Manual Table 4 - Max Airspeed Program Max airspeed connections Max Airspeed Prgm C Prgm B Prgm A TP 5C TP 5B TP 5A Not available Open Open Open Up to 75 knots Open Open Common 75 to 150 knots Open Common Open 150 to 300 knots Open Common Common 300 to 600 knots Common Open Open 600 to 1200 knots Common Open Common Above 1200 knots Common Common Open Not assigned Common Common Common Common pin TP 5D 3.4.6 Antenna Delay Program The antenna cables from the transponder to the top and bottom antennas may vary in length. The transponder must be programmed for the cable delay if the difference between the top and bottom antennas is greater than 50 nsec. This is accomplished by connecting the appropriate pins to the common pin as defined in the following table. Table 5 - Antenna Delay Program Delay Program Connections Programmed Delay (nsec) Differential Delay (nsec) Delay B TP 3D Delay A TP 3E 0 to 50 Open Open 51 to 150 Open Common 100 151 to 250 Common Open 200 251 to 350 Common Common 300 Open Common TP 3C Add delay to top antenna Add delay to bottom antenna Common Pin TP 3F 3.4.6.1 Antenna Delay Calculation The antenna cable delay is defined as the round trip propagation delay between the transponder and the antenna. Typical cable delay is 1.54 nsec/ft. Page 24 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Installation To compute the cable delay: 1. Calculate the difference in cable lengths between the top and bottom antennas in feet. 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 is longer than the bottom. 3.4.7 Antenna Program This program pin is used to identify installations in which only the bottom antenna is used. Ground single bottom mount antenna installation Open dual antenna installation 3.4.8 Antenna BITE Program This program pin is used to enable the antenna BITE test. Antennas capable of the BITE test will have a DC path to ground. If enabled, the transponder will perform a continuity test to verify the antenna is connected. Ground enable antenna BITE test Open disable antenna BITE test 3.4.9 Altitude Type Selection The transponder is capable of using altitude data from one of four types. The altitude type used is programmed by making the connections as defined in the following table. Table 6 - Altitude Type Selection Program Pins Data Source MP 6F MP 6G 429 Data Open Open Synchro Data Open Common Gillham Data Common Common Common Pin MP 6H 3.5 3.5.1 Interface Connections Discrete I/O Levels 3.5.1.1 Discrete Inputs The discrete inputs have the following logic level thresholds: Ground .................. < 3.5 volts DC or a resistance of < 10 ohms to ground Open...................... > 18 volts DC or a resistance of > 100K to ground 560-0405-00 Rev – December 14, 2001 Page 25 © 2001 by UPS Aviation Technologies Inc. Installation Installation Manual Series isolation diodes are included on all discrete inputs. 3.5.1.2 Discrete Outputs The 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 pulled high to 28 volts with 100K ohm). Active.................... pulled low to ground Inactive.................. open (100k pull-up) 3.5.1.3 Valid Flag Inputs The valid flag inputs are intended for connection to valid superflag outputs on connected equipment. The levels for these inputs are as follows: Valid...................... > 18 volts DC input relative to ground Invalid ................... < 3.5 volts DC input relative to ground 3.5.2 Gillham Code Altitude Input The transponder allows connection to an altitude source using the 11 wire Gillham code interface. Two inputs are provided, and the source can be selected with the altitude source discrete input, see 3.5.9. 3.5.3 Synchro Altitude Input The altitude information for the transponder may be obtained from an analog synchro altitude interface. 3.5.3.1 Synchro Valid Flag Input The synchro valid flag inputs are used to indicate the validity of the corresponding synchro input. The transponder will not use the synchro altitude if the valid flag input indicates an invalid condition. The synchro valid flag is a high level input. 3.5.4 ARINC 706 Air Data Inputs The altitude information for the transponder may be obtained from an ARINC 706 air data system via two low speed ARINC 429 data busses. 3.5.5 Control Panel Input The control panel data may be entered into the transponder on either of two low speed ARINC 429 data busses (Ports A and B). The port is selected by the control data port select discrete input. See paragraph 3.5.5.1. 3.5.5.1 Control Panel Port Selection The control port selection input is used to select which control panel port the transponder will use: Ground ..................uses control panel port A Open......................used control panel port B Page 26 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Installation This input is a discrete input as defined in 3.5.1.1. 3.5.6 Standby Input The standby discrete input is used to place the transponder in either the standby or active modes and is normally connected to the transponder control panel. In the standby mode, 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 transponder will respond to valid interrogations and generate squitters. Ground ..................standby Open......................active This input is a discrete input as defined in 3.5.1.1. 3.5.7 Air/Ground Discrete Inputs The air/ground discrete inputs are used by the transponder to determine air / ground status of the aircraft. This is used to control or inhibit replies and to indicate whether the aircraft is on the ground or airborne for Mode S replies. 3.5.7.1 Air/Ground #1 This input is used to not inhibit ATCRBS replies when on the ground, and is typically used for ramp test functions so that the transponder can reply to all types of interrogations. Ground ..................aircraft on the ground Open......................aircraft airborne This input is a discrete input as defined in 3.5.1.1. 3.5.7.2 Air/Ground #2 This input is used to indicate that the aircraft is on the ground, and is normally connected to the air/ground switch. When on the ground, the transponder will inhibit replies to ATCRBS interrogations. Ground ..................aircraft on the ground Open......................aircraft airborne This input is a discrete input as defined in 3.5.1.1. 3.5.8 Functional Test Discrete Input The functional test input is used to place the transponder in a functional test mode. Ground ..................enable functional test Open......................normal operation This input is a discrete input as defined in 3.5.1.1. 560-0405-00 Rev – December 14, 2001 Page 27 © 2001 by UPS Aviation Technologies Inc. Installation Installation Manual 3.5.9 Altitude Input Selection This input is used to select the active port used for the altitude data input. Ground ..................uses altitude input #2 Open......................uses altitude input #1 This input is a discrete input as defined in 3.5.1.1. 3.5.10 Altitude Compare 3.5.10.1 Altitude Compare Enable The altitude compare enable discrete input is used to enable the altitude compare function. Both altitude inputs must be valid. This feature works with Gillham, synchro, or ADC inputs, as selected. Ground .................. altitude compare enabled Open...................... altitude compare inhibited This input is a discrete input as defined in 3.5.1.1. 3.5.10.2 Altitude Compare Fail Output The altitude fail discrete output is used to indicate invalid altitude input data, and is normally connected to an indicator on the control panel. Ground ..................valid data, or altitude compare normal Open......................invalid, or altitude compare failure The function of the altitude fail output is dependent on the altitude source selected as follows: Gillham data..........when the altitude compare is enabled, the output will indicate failed when the two Gillham inputs are not within 500 feet ARINC 429 data ...output will indicate failed when the ARINC 429 input is invalid or ADC altitude inputs differ by more than 200 feet. Synchro data..........output will indicate failed when the Synchro input is invalid 3.5.11 Transponder Fail Outputs 3.5.11.1 Transponder Fail Discrete Output #1 This output will supply 5 volts DC (capable of 25 mA) when the transponder has failed, and will be open when the transponder is operating normally. 3.5.11.2 Transponder Fail Discrete Output #2 This output is open when the transponder has failed and is pulled low to ground when the transponder is operating normally. Valid...................... pulled low to ground Failed..................... open Page 28 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Installation This output is a discrete output as defined in 3.5.1.2. 3.5.12 Flight ID Input The flight ID may be input to the transponder from multiple serial inputs, depending upon installation requirements. The transponder will accept flight identification from any of these inputs, which is contained within four ARINC 429 data words. 3.5.13 Data Link Interface Four high speed ARINC 429 busses are provided for interfacing to a Mode S Airborne Data Link Processor (ADLP). The input and output busses are used for transferring messages 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 specific parameters to the requesting ground station. Enabling this feature requires a software upgrade. See ARINC 718A. 3.5.15 TX / XT Coord TCAS Interface The TCAS/Transponder interface consists of two high-speed ARINC 429 busses. Interface standards are listed in ARINC 735 and DO-185b. The transponder is operable with both Collins and ACSS TCAS units. 560-0405-00 Rev – December 14, 2001 Page 29 © 2001 by UPS Aviation Technologies Inc. Installation Installation Manual 3.6 Data Loader Interface Table 7 - Data Loader Plug Reference Section 2.5 Signal Name Portable Data Loader (PDL) ARINC 615 Input Bus Pin No. Equipment Connection 429 Input (Provisions Only) 429 Input (Provisions Only) Spare Spare Chassis Ground (429 Input Bus Shield) GND Spare Spare PDL ARINC 615 Output Bus Spare 10 Spare 11 Spare 12 Spare 13 Spare 14 Spare 15 Chassis Ground (429 Output Bus Shield) GND 16 Spare 17 Spare 18 Spare 19 115 Volt AC Power Input HOT 20 Chassis Ground GND Shield Ground 429 Output (Provisions Only) 429 Output (Provisions Only) Shield Ground 21 115 Volt AC Power Input COMMON 22 Spare 23 Spare 24 Spare 25 Spare 26 Spare 27 Spare 28 Spare 29 Spare 30 Spare 31 Spare 32 Spare 33 Page 30 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Installation Table 7 - Data Loader Plug (Continued) Reference Section Pin No. Signal Name Spare 34 Spare 35 Spare 36 28 Volt DC Power Input POS 37 28 Volt DC Power Return NEG 38 Equipment Connection Spare 39 RS-232 Input 40 Maintenance Data/Software Update Port RS-232 Output 41 Maintenance Data/Software Update Port PDL CTS Input 42 PDL RTS Output 43 Spare 44 Spare 45 Spare 46 Spare 47 Chassis Ground GND 48 Chassis Ground GND 49 PDL Function Discrete #1 50 PDL Function Discrete #2 51 PDL Function Discrete #3 52 PDL Function Discrete #4 53 560-0405-00 Rev – December 14, 2001 Page 31 © 2001 by UPS Aviation Technologies Inc. Installation Installation Manual VIEW OF MATING CONNECTOR ON AIRCRAFT VIEW OF CONNECTOR ON UNIT Figure 11 – Data Loader Page 32 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Post-Installation Checkout Section 4 - Post-Installation Checkout The Post Installation System Checkout verifies the wiring in the aircraft after installation. The AT7000 includes Built-In Test Equipment (BITE) software functions. The BITE software is used in the post-installation wiring checkout. The actual tests conducted will be determined by the selected installation options. 4.1 Key Pin Orientation Verify 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 from the back of the unit, and the dark areas are the solid part of the key. This is specifically keyed for a Mark 3 transponder. 4.2 Pre-Installation Checkout Procedures Prior to installing the equipment, perform power check as outlined below. Power Check Transponder 115 VAC BP1 (see note below) 115 Return BP7 28 VDC BP10 (see note below) 28 Return BP 3 Note: The unit is able to accept either 28 VDC or 115 VAC. 560-0405-00 Rev – December 14, 2001 Page 33 © 2001 by UPS Aviation Technologies Inc. Post-Installation Checkout Installation Manual NOTES Page 34 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Equipment Removal and Replacement Section 5 - Equipment Removal and Replacement 5.1 5.1.1 Removal Transponder Remove the transponder from the tray with ARINC 600 hold-downs as follows: 1. Loosen unit hold-down knobs. Figure 12 – Removal of Unit from Tray 2. 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. Transponder is now free to be removed from mounting tray. Place electrostatic protective covers over transponder connector and aircraft mating electrical connector. 5.2 Replacement 5.2.1 Transponder Replace the transponder in mounting tray as follows: 1. Remove protective plastic covers from aircraft connectors. Remove electrostatic protective covers from transponder connectors. 2. Slide transponder into mounting tray. CAUTION: DO NOT FORCE FIT. IF MATING IS DIFFICULT, REMOVE THE TRANSPONDER AND CHECK FOR CONNECTOR PINS THAT MAY BE BENT OR OUT OF ALIGNMENT. ALSO, CHECK THE ALIGNMENT OF THE RECEPTACLE IN MOUNTING TRAY. 560-0405-00 Rev – December 14, 2001 Page 35 © 2001 by UPS Aviation Technologies Inc. Equipment Removal and Replacement Installation Manual 3. Carefully apply firm pressure until transponder connector is mated with connector receptacle on mounting tray. 4. Pull knobs of mounting tray over hooks on the component and tighten unit hold-down knobs, ensuring proper engagement is made. Page 36 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Specifications Section 6 - Operation The Mode S Data Link System can be configured in the following ways: two Mode S Transponders or one Mode S Transponder and one ATCRBS Transponder. Single transponder installations are acceptable. The function of the Mode S System is to provide air traffic information to Mode S and ATCRBS ground stations to aid in the air traffic control. The Mode S System receives ATCRBS interrogations (ground to air) and transmits ATCRBS replies (air to ground); receives Mode S interrogations (ground to air) and transmits Mode S replies (air to ground); receives TCAS interrogations (air to air) and transmits Mode S replies (air to air). 560-0405-00 Rev – December 14, 2001 Page 37 © 2001 by UPS Aviation Technologies Inc. Specifications Installation Manual NOTES Page 38 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Specifications Section 7 - Specifications This section includes detailed electrical, physical, environmental, and performance specifications for the AT7000. 7.1 Electrical Power Requirements (28VDC) Operating Voltage ....................18 to 32.2VDC; 28 VDC typical Power Consumption: Standby Mode ..........................................20 Watts Active Mode (typical load) ......................30 Watts Active Mode (maximum load ..................60 Watts Power Requirements (115V, 400 Hz): Operating Voltage .....................90 to 135VAC, 400 Hz; 115VAC, 400 Hz typical Power Consumption: Standby Mode ..........................................24 Watts Active Mode (typical load) ......................36 Watts Active Mode (maximum load ..................65 Watts 7.2 Physical ARINC 600 4MCU Type 2 Connector; (Polarization code “05”) Height ...................................................7.64" Width....................................................5.04" Depth ....................................................14.107" AT7000 Weight ...................................9.6 lbs. 560-0405-00 Rev – December 14, 2001 Page 39 © 2001 by UPS Aviation Technologies Inc. Specifications Installation Manual 5.04” 14.107” 7.64” Figure 13 – AT7000 Dimensions 7.3 Environmental The AT7000 Mode S Transponder is designed and tested to meet appropriate categories of RTCA/DO-xxx. The Environmental Qualification Form is included in Section 10. Operating temperature...............................-20°C to +70°C Storage temperature ..................................-55°C to +85°C Temperature variation ...............................5°C per minute (minimum) Humidity ...................................................95% RH at 65°C for 6 hours (10 day cycle) Maximum altitude .....................................55,000 feet Cooling......................................................The unit can utilize external cooling air in accordance with ARINC 600, ARINC 404 or operate in convection cooled environments. 7.4 Transponder Performance TSO ................................................................TSO-C112 TSO Class ......................................................CL 2A7, 121, 011 Warm-up ........................................................None required Receiver Frequency........................................1030 MHz Sensitivity (MTL) ..........................................-72 dBm +/- 1 dB Dynamic Range..............................................>50 dB Side Lobe Suppression...................................2 pulse (P1, P2), -60 dBm Transmitter Frequency...................................1090 MHz +/- 120 kHz Page 40 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Specifications Transmitter Power..........................................250 watts minimum, 400 watts typical, 600 watts maximum Mode A Capability.........................................4096 codes plus SPI ident pulse Mode C Capability.........................................-1000 to 126,700 feet, 100 foot increments. Mode S Capability .........................................-1000 to 126,700 feet, 25 foot increments. 560-0405-00 Rev – December 14, 2001 Page 41 © 2001 by UPS Aviation Technologies Inc. Specifications Installation Manual NOTES Page 42 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Limitations Section 8 - Limitations 8.1 Installation Installations are to be made in accordance with all appropriate FAA approved guidelines for each given installation. It is the responsibility of the installer to ensure that aircraft installation conditions meet the appropriate standards for the specific type and class and operation of aircraft involved. 560-0405-00 Rev – December 14, 2001 Page 43 © 2001 by UPS Aviation Technologies Inc. Limitations Installation Manual NOTES Page 44 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Troubleshooting Section 9 - Troubleshooting 9.1 9.1.1 Introduction and Overview Introduction The AT7000 includes a status display located on the unit front panel which provides additional information from the status LEDs. The display is used to display the maintenance information. The four buttons located below the display are used to scroll through the available display information. The maintenance display includes an LED backlight. The backlight turns on when a button is pushed and remains on for five minutes after the last button is pressed. 9.1.2 Overview The AT7000 consists of the following interfaces for the user. On the front panel is a four line 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, installation checkout and verifying of aircraft interface inputs. The maintenance display provides information about the unit, including: software version number, system failure information, configuration pin inputs, discrete inputs, external interfaces, and receiver/transmitter enable status. XPDR PASS XPDR FAIL CTRL PNL TOP ANT MAINTENANCE DISPLAY BOT ANT ALT TEST AT7000 Mode S Data Link Transponder Model: AT7000 DATA LOADER Mode S Transponder Software PN: Map/Database 430-6091 - 00 - 00 HW Mod A B C D E F G H J K L M N P R S T U V W X Y Z AA AB AC ADAE AF AGAH AJ AK AL AMAN Weight 10.0 lbs. SW Mod A B C D E F G H J K L M N P R S T U V W X Y Z AA AB AC ADAE AF AG AH AJ AK AL AMAN barcode of serial number SN '1234567' UPS Aviation Technologies, TSO-C112 Class 2A7, 121, 011 RTCA/DO-178B Software Level B RTCA/DO-160D Env. Cat. FCC ID xxxxxxx Salem OR USA Figure 14. AT7000 Mode S Transponder 560-0405-00 Rev – December 14, 2001 Page 45 © 2001 by UPS Aviation Technologies Inc. Troubleshooting Installation Manual 9.2 Interfaces 9.2.1 Buttons The 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 follows: ← and → These buttons are used to select the column. When pressing one of these buttons, the top page of either the previous (←) or next (→) group will be displayed. ↑ and ↓ These buttons are used to scroll through the pages within a column. Pressing the ↑ button will move the previous page, the ↓ button will move to the next page. Note: The pages wrap around. The display is used only for displaying transponder information. No configuration or data can be input using the front panel display and buttons. 9.2.2 Test Status LEDs The AT7000 includes six test status LEDs on the front panel. These LEDs are used to provide transponder test results and are generally used by aircraft mechanics. Failure lights will stay illuminated for 3 seconds after powering up. Once in the self test mode the fail light will stay illuminated for 10 seconds. When in this mode, pressing any button will illuminate the failure for 30 seconds. Table 8 - Status LEDs Summary LED XPDR PASS Color Green XPDR FAIL Red CTRL PNL Red TOP ANT BOT ANT ALT Red Red Red 9.2.3 Description Transponder pass, turned on if B.I.T.E. passes and the transponder is able to operate. Transponder fail, turned on if B.I.T.E. fails and the transponder is not able to receive interrogations or generate replies. Control panel fail, turned on if the transponder is not receiving valid control information on the selected control panel ARINC 429 input port. Top antenna fail, turned on if the top antenna B.I.T.E. test fails. Bottom antenna fail, turned on if the bottom antenna B.I.T.E. test fails. Altitude fail, turned on if a valid altitude is not available from the selected altitude input or if the altitude compare fails (when enabled). Maintenance Display Pages The diagram on the next page illustrates the operating modes and access matrix. The software version page is displayed only once at power up and is only displayed until the self-test starts. Page 46 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Troubleshooting Power Up Startup Display SW Version Normal Mode Self Test Mode AT7000 Self Test Running UPS Aviation Technologies PROGRAM INPUTS DISCRETE INPUTS EXTERNAL INTERFACES Mode S Address Control Panel ADC (429) Altitude Inputs* (x2) Self Test Status *Program Pin Dependent SDI Program OR Altitude Select Transponder Fail Status Gillham Altitude Inputs* (x2) Max Airspeed Air/Ground *Program Pin Dependent Control Panel Fail Status OR Synchro Altitude Inputs* (x2) Altitude Type Top Antenna Fail Status *Program Pin Dependent Antenna Delay Control Panel Inputs (x2) Bottom Antenna Fail Status Antenna BITE Flight ID Input Antenna Program DataLink Interface Altitude Fail Status TCAS Interface Figure 15. Maintenance Displays 9.2.3.1 Page Descriptions 9.2.3.2 Display Functions The front panel status display is used to display information useful for: a. aircraft installation checkout b. isolating aircraft system/wiring problems c. displaying B.I.T.E. test results d. transponder maintenance 560-0405-00 Rev – December 14, 2001 Page 47 © 2001 by UPS Aviation Technologies Inc. Troubleshooting Installation Manual 9.2.3.3 Startup Page When the transponder is turned on, the following page is displayed for a moment (during boot 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 software version. UPS AVIATION TECHNOLOGIES AT7000 Mode S SW Ver: 1.XX 9.2.3.4 Self Test Running Page The AT7000 Self Test page is displayed for three seconds every time ‘Self Test’ mode is initiated. AT7000 Self Test Running 9.2.3.5 Self Test Status Pages The ‘Self Test Status’ page displays the number of currently active fault types. Self Test Result 0 Faults Press TEST to View Legs Info 9.2.3.6 Flight Legs Fault Status Page The ‘Flight Legs Fault Status’ page displays the number fault types for the leg defined as current 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 Status The Transponder Fail Status page is used to display the failure status of the transponder when the transponder fail LED is turned on. Trnspndr Failure 1) ICAO Address 2) Transmitter 3) Top Rcvr Page 48 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Troubleshooting If internal failures are detected (causing the XPDR FAIL LED to illuminate), then the cause of the failure will be displayed. Only one page will be displayed, with the three most significant internal failures displayed. a. b. c. d. e. f. g. h. i. ICAO Address Internal component of Transponder Top Transmitter Bottom Transmitter Tx Synth Lock Rx Synth Lock Top Receiver Bottom Receiver Squitter Mon 9.2.3.8 Control Panel Fail Status This display is used to display the failure status of the selected control panel input if a failure is detected and the control panel fail LED is illuminated. Control Panel A No Data The first line is used to display which of the control panels is selected, either A or B. The failure 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 second line. Both Control Panel A and B pages can be displayed if failures occurred on each while they were selected. 560-0405-00 Rev – December 14, 2001 Page 49 © 2001 by UPS Aviation Technologies Inc. Troubleshooting Installation Manual 9.2.3.9 Top Antenna Fail Status This display is used to display the top antenna BITE failure if a failure is detected and the top antenna fail LED is illuminated. Top Antenna BITE Test Fail 9.2.3.10 Bottom Antenna Fail Status This display is used to display the bottom antenna BITE failure if a failure is detected and the bottom antenna fail LED is illuminated. Bottom Antenna BITE Test Fail 9.2.3.11 Altitude Fail Status This display is used to display the altitude failure. The failure displayed is dependent upon the selection of the altitude type program input. Altitude SRC #1 Type: ADC (429) Invalid 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 reference input 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 second line. Both Altitude Source 1 and Altitude Source 2 pages can be displayed if failures occurred for each while they were selected. Page 50 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual 9.2.4 Troubleshooting Normal Mode In normal mode the pages are intended for system checkout or fault isolation when the aircraft is on the ground. 9.2.4.1 Default Page The transponder will always return to the default page. This occurs when test mode times out, or if any other page is displayed in Normal Mode and a button has not been pressed in five minutes. UPS AVIATION TECHNOLOGIES AT7000 Mode S PRESS ←→ or TEST 9.2.4.2 Program Inputs The program inputs group is used to display the settings of each of the transponder’s rear panel program inputs. PROGRAM INPUTS PRESS ←→↑↓ TEST 9.2.4.3 Mode S Address This display is for decoding the 24-bit mode S address, displayed in octal and hexadecimal. Mode S Address: OCT 12345670 HEX 053977 560-0405-00 Rev – December 14, 2001 Page 51 © 2001 by UPS Aviation Technologies Inc. Troubleshooting Installation Manual 9.2.4.4 SDI Program Input This display is SDI program input as 2 bits binary. SDI Program: 00 Invalid 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 Program This display is for the max airspeed program input. The airspeed displays are: Max Airspeed: 150 to 300 knots 0) invalid (0 is not available) 1) up to 75 knots 2) 75 to 150 knots 3) 150 to 300 knots 4) 300 to 600 knots 5) 600 to 1200 knots 6) above 1200 knots 7) invalid (7 is not assigned) 9.2.4.6 Altitude Type Program This is used to display the current altitude input type selected by the program pin inputs. The altitude selection displays are: Altitude Type: ADC (429) 0) ADC (429) ARINC 429 air data input 1) Synchro Page 52 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Troubleshooting 2) Gillham 3) Invalid 9.2.4.7 Antenna Delay Program This display is for the antenna delay program input. Antenna Delay: Delay: 51 to 150 nsec Ant: bottom The delay selection displays are: 0) 0 to 50 nsec 1) 51 to 150 nsec 2) 151 to 250 nsec 3) 251 to 350 nsec The antenna is either the bottom or top. 9.2.4.8 Antenna BITE Program This page is for the antenna BITE program input. Antenna BITE: Enabled The possible displayed antenna BITE selections are: 0) Disabled 1) Enabled 9.2.4.9 Antenna Program This page displays the antenna program input. 560-0405-00 Rev – December 14, 2001 Page 53 © 2001 by UPS Aviation Technologies Inc. Troubleshooting Installation Manual Antenna Program: Dual Antenna The antenna program selections are: 0) Dual antenna 1) Bottom only 9.2.5 Discrete Inputs The Discrete Input group is used to display the status of the rear panel discrete inputs, such as the altitude select and control panel select. DISCRETE INPUTS Press ←→↑↓ TEST These displays are used to display the state of each of the discrete inputs, grouped in the following pages. Discrete Inputs Page 1: Cntrl Panel: Mode: Standby Func Test: Test 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. Alt Select: Alt Compare: on Sync #1: Valid Sync #2: Invalid Page 54 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Troubleshooting 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: Air/Gnd #1: air Air/Gnd #2: gnd 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 Interfaces The external interfaces group is used to display the status of the rear panel interface inputs, such as the altitude and control panel inputs. EXTERNAL INTERFACES Press ←→↑↓ TEST 9.2.6.1 ADC Altitude Inputs This page is used to display the altitude and status from the air data computer inputs. 429 Alt #1 15,475 feet Valid 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) 560-0405-00 Rev – December 14, 2001 Page 55 © 2001 by UPS Aviation Technologies Inc. Troubleshooting Installation Manual Note: During aircraft ground maintenance operation, only the selected altitude input needs to be displayed. During bench maintenance operation, all four altitude inputs will be displayed. 9.2.6.2 Gillham Altitude Inputs This page is used to display the altitude from the two Gillham altitude inputs. Gillham Alt #1 15,500 feet Valid 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 Inputs This page is used to display the altitude and status from the two synchro altitude inputs Synchro Alt #1 15,475 feet Input: Valid Flag: Valid The 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 • Invalid Page 56 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Troubleshooting 9.2.6.4 Control Panel Inputs These pages are used to display the info and status from the two control panel inputs. Control Panel Ident: 1200ident Mode: Active Valid 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) • NotSelected The 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 Input This page is used to display the status of the flight ID input. Flight ID Input Flight ID Valid 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) 560-0405-00 Rev – December 14, 2001 Page 57 © 2001 by UPS Aviation Technologies Inc. Troubleshooting Installation Manual 9.2.6.6 DataLink Interface This page is used to display the status of the ARINC 429 data link interface. Datalink Interface Valid 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 Interface This page is used to display the status of the ARINC 429 TCAS interface. TCAS Interface Mode: Status: Standby Valid 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) Page 58 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual 9.3 Troubleshooting Troubleshooting The transponder has several system checks that can assist in troubleshooting. A self-test can be conducted from the transponder front panel and from the control panel. 9.3.1 System Test Before 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 closed The table on the following page offers some troubleshooting information. The screens are accessed in the ‘Self Test Mode’. To enter the ‘Self Test Mode’, at power up, press the test button on the front panel. The start of ‘Self Test Mode’ turns all six front panel lights 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. Pressing 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 ten flight legs. At the end of the ‘Self Test Mode’, the lamps all turn off and the user interface changes to the normal mode. 560-0405-00 Rev – December 14, 2001 Page 59 © 2001 by UPS Aviation Technologies Inc. Troubleshooting Problem Installation Manual Table 9 - Troubleshooting Guide Cause XPDR PASS LED is illuminated. XPDR FAIL LED is illuminated. Normal operation. CTRL PNL failure light is illuminated and the ‘Control Panel Fail Status’ page reads ‘Invalid’, ‘Rate Failed’ or ‘No Data’. TOP ANT failure light is illuminated and ‘Top Antenna’ page reads ‘BITE Test Fail’. BOT ANT failure light is illuminated and ‘Bottom Antenna’ page reads ‘BITE Test Fail’. ALT SIG failure light is illuminated. The ‘Altitude Fail Status’ will read ‘Invalid’ or ‘No Data’ if the type of altitude source is ADC (429). If Gillham is selected as the source the display will read ‘Invalid’ or ‘Compare Fail’. If Synchro is selected as the source, the failures will be ‘Invalid’ or ‘Flagged’. The ‘Trnspndr Failure’ page will show up to three most significant failures: 1. ICAO Address 2. Internal component of Transponder 3. Top Transmitter 4. Bottom Transmitter 5. Tx Synth Lock 6. Rx Synth Lock 7. Top Receiver 8. Bottom Receiver 9. Squitter Mon Control panel not connected. Corrective Action No action necessary. Check wiring. Replace faulty control panel. Top antenna not connected correctly. Bottom antenna not connected correctly. Page 60 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Periodic Maintenance Section 10 - Periodic Maintenance 10.1 Maintenance There are no internal manual adjustments needed. 560-0405-00 Rev – December 14, 2001 Page 61 © 2001 by UPS Aviation Technologies Inc. Periodic Maintenance Installation Manual NOTES Page 62 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc. Installation Manual Environmental Qualifications Section 11 - Environmental Qualifications The AT7000 has been tested to the following environmental categories per procedures defined in RTCA/DO-160D. Table 10 - Environmental Requirements Nomenclature: AT7000 Part No.: 430-6091-100 TSO No.: TSO C112 Manufacturer: UPS Aviation Technologies 2345 Turner Road SE Salem, Oregon 97302 Environment Section Category Comment Temperature and Altitude A2 Operating Temp ............ -20°C to +70°C Short Time Hi Temp ..... to +70°C Cooling ......................... Required Ground survival temp ... -55°C to +85°C Altitude ......................... 55,000 feet Overpressure ................. –15,000 feet Decompression ............. 55,000 feet Temperature Variation Minimum 5°C per minute Humidity Severe humidity environment. Operational Shocks and Crash Tested for operational shock and crash safety. Safety Aircraft type 5, test type R Vibration S&T S (curves B and M), T (curves B, B1 and R) Explosion Proofness Not applicable, no test required Waterproofness 10 Not applicable, no test required Fluids Susceptibility 11 Not applicable, no test required Sand and Dust 12 Not applicable, no test required Fungus Resistance 13 Not applicable, no test required Salt Spray 14 Not applicable, no test required Magnetic Effect 15 < 0.3 meter Power Input 16 A&E 28 volt DC and 115 volt 400 Hz AC Voltage Spike 17 Audio Frequency Conducted Sus- 18 A&E ceptibility - Power Inputs Induced Signal Susceptibility 19 Z is minimum requirement, C is the goal Radio Frequency Susceptibility 20 U is minimum requirement, V is the goal (Radiated and Conducted) Emission of Radio Frequency En- 21 ergy Lightning Induced Transient Sus- 22 A3 Pin injection ceptibility C2 Unshielded cables E2 Shielded cables Lightning Direct Effects 23 Not applicable, no test required Icing 24 Not applicable, no test required Electrostatic Discharge (ESD) 25 560-0405-00 Rev – December 14, 2001 Page 63 © 2001 by UPS Aviation Technologies Inc. Environmental Qualifications Installation Manual NOTES Page 64 560-0405-00 Rev – December 14, 2001 © 2001 by UPS Aviation Technologies Inc.
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