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1 | Manual | Users Manual | 710.11 KiB |
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 Avia-
tion Technologies UPS Aviation Technologies PO Box 13549 Salem, OR 97309 Phone:
503.581.8101 800.525.6726 Fax:
503.364.2138 In Canada: 800.654.3415 2345 Turner Rd., SE Salem, OR 97302 USA 560-0405-00 Rev December 14, 2001 Installation Manual AT7000 Mode S Transponder HISTORY OF REVISIONS Revision EN Date Description
EN7149 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 NOTES AT7000 Mode S Transponder 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 Revision Number Revision Number Date In-
serted Revision Inserted Date Date Date By By 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page i AT7000 Mode S Transponder Installation Manual List of Effective Pages Section and Page Revision Title Copyright page History of Revisions List of Effective Pages Table of Contents Sec. 1. Introduction Section and Page Revision Page 37 00 Sec. 4. Post-Install Checkout Page 38 Page 39 00 00 Sec. 5. Equipment Rem. and Rep. 00 00 Page 40 Page 41 Sec. 6. Operation Sec. 2. System Description Sec. 7. Specifications Sec. 3. Installation Sec. 8. Limitations Sec. 9. Troubleshooting 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 Page 1 Page 2 Page 3 Page 4 Page 5 Page 6 Page 7 Page 8 Page 9 Page 10 Page 11 Page 12 Page 13 Page 14 Page 15 Page 16 Page 17 Page 18 Page 19 Page 20 Page 22 Page 23 Page 24 Page 25 Page 26 Page 27 Page 28 Page 29 Page 30 Page 31 Page 32 Page 33 Page 34 Page 35 Page 36 Page 42 Page 43 Page 44 Page 45 Page 46 Page 47 Page 48 Page 49 Page 50 Page 51 Page 52 Page 53 Page 54 Page 55 Page 56 Page 57 Page 58 Page 59 Page 60 Page 61 Page 62 Page 63 Page 64 Page 65 Page 66 Page 67 Page 68 Page 69 Page 70 Page 71 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 Sec. 10. Periodic Maintenance Sec. 11. Environmental Qualifications Page ii 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual AT7000 Mode S Transponder TABLE OF CONTENTS SECTION 1 - INTRODUCTION ................................................................................................................ 1 1.1 ABOUT THIS MANUAL .......................................................................................................................1 SYSTEM DESCRIPTION........................................................................................................................1 1.2 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 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 3.5 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page iii 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 INSTALLATION .................................................................................................................................43 SECTION 9 - TROUBLESHOOTING ..................................................................................................... 45 INTRODUCTION AND OVERVIEW.......................................................................................................45 9.1.1 Introduction..............................................................................................................................45 9.1.2 Overview ..................................................................................................................................45 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 System Test...............................................................................................................................59 SECTION 10 - PERIODIC MAINTENANCE ...................................................................................... 61 10.1 MAINTENANCE.................................................................................................................................61 SECTION 11 - ENVIRONMENTAL QUALIFICATIONS ................................................................. 63 9.3.1 8.1 9.1 9.2 Page iv 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 2001 by UPS Aviation Technologies Inc. Page v AT7000 Mode S Transponder Installation Manual NOTES Page vi 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 Administra-
tion (FAA) to install avionics devices. It includes installation and checkout procedures for the UPS Aviation Technologies AT7000 Mode S Transponder. 1.2 System Description 1.2.1 System Overview Airborne Data Link Processor
(ADLP)*
*Optional TCAS*
*Optional Control Panel AT7000 Mode S Transponder Air Data Computer
(ADC) Central Maintenance Computer
(CMC)*
TCAS 1090 Receiver
(ADSB) ADSB ATC Radar Interrogator
*Optional (Not supported in initial release) Airborne System AT7000 System Block Diagram Figure 1 -- AT7000 System Block Diagram 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 1 AT7000 Mode S Transponder Introduction 1.2.2 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 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 Panel The 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 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 se-
lection between two onboard transponders. The control panel also input FID into the transponder. 1.2.4 Antenna When installing the transponder antennas, a TSOd 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, planes above, 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 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 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 that is an output from TCAS to the transponder. Page 2 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Introduction AT7000 Mode S Transponder 1.3 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 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 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 2001 by UPS Aviation Technologies Inc. Page 3 AT7000 Mode S Transponder Introduction NOTES Page 4 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 ca-
pable 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 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 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 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 for display 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 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 2001 by UPS Aviation Technologies Inc. Page 5 System Description Installation Manual XPDR PASS XPDR FAIL CTRL PNL TOP ANT BOT ANT ALT TEST DATA LOADER Weight 10.0 lbs. MAINTENANCE DISPLAY AT7000 Mode S Data Link Transponder Model: AT7000 Mode S Transponder Map/Database Software PN:
430-6091 - 00 - 00 C D E BA HW Mod ZYXWVUTSRPNM AC F G H J K L AB AD AE AF AGAH AJ AK AL AMAN AA C BA D E SW Mod ZYXWVUTSRPNM AC F G H J K L AB ADAE AFAGAH AJ AK AL AMAN AA barcode of serial number SN '1234567'
TSO-C112 Class 2A7, 121, 011 RTCA/DO-178B Software Level B RTCA/DO-160D Env. Cat. FCC ID xxxxxxx UPS Aviation Technologies, 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 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 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 the transponder. The minimum label set is as follows for airborne position squittering:
Description Minimal Necessary Labels Label #
110 (120) Latitude (Fine) 111 (121) Longitude (Fine) 150 140 Time Word Fractional Seconds
(should be last word of data block) HPL Equipment ID must be 142 130 377 Minimum Rate 5 Hz 5 Hz 5 Hz 5 Hz Alternate Labels 310 311 5 Hz 0.5 Hz 247 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 7 System Description Installation Manual Minimal Necessary Labels (Only Type 1&2 or Type 3&4 Required) Label #
174 Minimum Rate 5 Hz Description NS Velocity Type Code 1&2 166 320 210 EW Velocity Type Code 1&2 Magnetic Heading Type Code 3&4 True Airspeed Type Code 3&4 (from ADC) 5 Hz OR 5 Hz 5 Hz Alternate Labels 103 and 112
(or 311 and 312) 103 and 112
(or 311 and 312) 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 in-
terface 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 re-
lease. 2.6 Built-In Test Equipment (BITE) and Diagnostics The 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 The built-in tests include the following and are completed at power up of the transponder. Self-Tests a) power supply voltages b) memory checks c) transmitter (monitor replies) d) synthesizers e) transponder interfaces f) top and bottom antenna test Page 8 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual System Description 2.6.2 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 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/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 2001 by UPS Aviation Technologies Inc. Page 9 System Description NOTES Installation Manual Page 10 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 LRU AT7000 Table 1 - Equipment for Installation Mating Connector NSXN2P203X0105 Qty/System 1 3.3 Mechanical Installation 3.3.1 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 2001 by UPS Aviation Technologies Inc. Page 11 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) S65-5366-7L (Sensor Systems P/N) Or equivalent L-Band Antenna 20 from other L-band antennas in same range. Page 12 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Installation 3.4 Electrical Installation Reference Section Signal Name 3.5.2 Gillham Code Altitude Input #2 A1 A2 A4 B1 B2 B4 C1 C2 C4 D2 3.5.14
*MSP Bus Input ARINC 429 A B DAPS Input ARINC 429 A B Hardware Provisioned Output ARINC 429 A B Reserved #1 Output ARINC 429 A B Reserved Discrete Input #1 Pin No. Equipment Connection TP 1A TP 1B TP 1C TP 1D TP 1E TP 1F TP 1G TP 1H TP 1J TP 1K TP 2A TP 2B TP 2C TP 2D TP 2E TP 2F TP 2G TP 2H TP 2J From Airborne Data Link Processor Unit (LDPU) 3.5.2 Gillham Code Altitude Input #2 D4 TP 2K From Encoding Altimeter #2 Reserved Discrete Output TP 3A 3.5.11.2 Transponder Fail Output #2 TP 3B To Mode S Control Panel J1-12 3.4.6 Antenna Cable Delay Program 3.4.4 SDI Program Top/Bot B A Common B A Common TP 3C TP 3D TP 3E TP 3F TP 3G TP 3H TP 3J 3.5.2 Gillham Code Altitude Input #2 Common TP 3K 3.5.3 Synchro Altitude Input #1 X course Y course Z course Ref H 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 From Air Data Computer #1
*Optional Figure 5 Top Plug Interconnect Description (Sheet 1) 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 13 Installation Reference Section Installation Manual Signal Name Pin No. Equipment Connection 3.4.5 Max Airspeed Program A B C COM 3.5.15 3.5.15 3.5.7 3.5.12 3.4.7 3.5.5 TX Coordination TCAS 429 A B XT Coordination TCAS 429 A B Air/Ground Discrete Inputs #2
#1 NAV Data/Flight ID 429 Input Bus A B Reserved A B Reserved A B Reserved Reserved A B Antenna Program Control Panel Input Bus #1 A B Reserved 3.5.5.1 Control Panel Data Port Select 3.5.5 3.5.6 3.5.4 Control Panel Input Bus #2 A B Standby Air Data #1 ARINC 429 Input A B Reserved TP 5A TP 5B TP 5C TP 5D TP 5E TP 5F TP 5G TP 5H TP 5J TP 5K TP 6A TP 6B TP 6C TP 6D TP 6E TP 6F TP 6G TP 6H TP 6J TP 6K TP 7A TP 7B TP 7C TP 7D TP 7E TP 7F TP 7G TP 7H TP 7J TP 7K To Pin 12D of TCAS Computer To Pin 12E of TCAS Computer To Pin 14F of TCAS Computer To Pin 14G of TCAS Computer To Air/Ground Relay From LDPU (ADLP) 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 To #1 Air Data Computer Figure 4 Top Plug Interconnect Description (Sheet 2) Page 14 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Installation TP A B A2 C A4 D B1 E F Gillham Altitude Input #2 B2 B4 G C1 H C2 Data Link Input
(429 ip) Comm C/D Input
(429 ip) B A B A
(429 op) B Comm C/D Output RSVD #1 Output A B
(429) B SDI A RSVD Output XPDR Fail
#2
(disc op)
(disc op) Antenna Delay Program Top/Btm B A com
----------------------- Course ------------------
Y Z Synchro Altitude #1 26VAC Ref C H
------------------------ Fine ---------------------
Y X B B Max Airspeed Program B B Flight ID / FMS
(429 ip) C A com ADL Input
(429 ip) B TX COORD
(429 ip) ADL Output
(429 op) A A XT COORD
(429 pp) A ADL IP Sel
(disc ip) Control Panel IP #1
(429 ip) B A RSVD IP #3 Cntl Pnl Select
(disc ip)
(disc ip) Control Panel IP #2 Standby
(429 ip) A B
(disc ip) A1 A X A A 1 2 3 4 5 6 7 J C4 RSVD IP #1
(disc ip) K D2 D4 com com Synchro Flag #1 RSVD IP #2
(disc ip)
(disc ip) Z B A A Air/Gnd
#2
(disc ip) Reserved B B Air Data #1 Input
(429 ip) Air/Gnd
#1
(disc ip) Antenna Program
(prgm ip) RSVD IP #4
(disc ip) Figure 6 Top Plug Connector Layout 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 15 Top Antenna 1-23-01 RAS Installation Installation Manual THIS PAGE INTENTIONALLY LEFT BLANK Page 16 560-0405-00 Rev 2001 by UPS Aviation Technologies Inc. December 14, 2001 Installation Manual Installation 3.4.1 Middle Plug Reference Section Signal Name Pin No. Equipment Connection 3.4.3.1 Reserved Mode S Address Address 1 Address 2 Address 3 Address 4 Address 5 Address 6 Address 7 Address 8 Address 9 Address 10 Address 11 Address 12 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 3.5.1.1 Functional Test Discrete Input 3.5.10.2 Altitude Compare Fail Output 3.5.11.1 XPDR Fail #1 Output 3.5.2 Gillham Code Altitude Input #1 3.5.4 Air Data #2 ARINC 429 Input Reserved Data Link 429 Output A B A1 A2 A4 B1 B2 B4 C1 C2 C4 D2 A B A B 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 MP 3H MP 3J MP 3K MP 4A MP 4B MP 4C MP 4D MP 4E MP 4F MP 4G MP 4H MP 4J MP 4K MP 5A MP 5B MP 5C MP 5D MP 5E MP 5F Reserved for mode control panel or other DAPS inputs. From Altimeter From #2 Air Data Computer Reserved for inputs for DAPS MSP Bus to LDPU Figure 7 Middle Plug Interconnect Description (Sheet 1) 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 17 Installation Installation Manual Reference Section 3.5.10.1 3.6 3.4.8 3.5.2 Signal Name Pin No. Equipment Connection Altitude Compare Input MP 5G To Pin 17 of Control Panel DL/DHL Program Pin MP 5H Antenna BITE Enable Program Program Pin MP 5J Gillham Code Altitude Input #1 D4 Maintenance Data 429 Input A B Maintenance Data 429 Output A B MP 5K MP 6A MP 6B MP 6C MP 6D Hardware Provisions Hardware Provisions 3.5.9 Altitude Input Source Selection MP 6E To Pin 16 of Control Panel 3.4.9 Altitude Type Selection Program B A COM MP 6F MP 6G MP 6H Reserved #2 ARINC 429 Input MP 6J Tied to MP 7K 3.5.2 Gillham Code Altitude Input #1 COM 3.5.3 Synchro Altitude Input #2 X Course Y Course Z Course Ref H Ref C X Fine Y Fine Z Fine Synchro #2 MP 6K MP 7A MP 7B MP 7C MP 7D MP 7E MP 7F MP 7G MP 7H MP 7J Discrete Input Reserved #2 IP 429 B MP 7K Tied to MP 6J Figure 6 Middle Plug Interconnect Description (Sheet 2) Page 18 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Installation MP 1 2 3 4 5 6 7 A 1 11 21 B 2 12 22 C 3 13 23 D 4 14 24 E F Mode S Address Input 5 15 6 16 Rsrvd #1 IP
(429 ip) com A Gillham Altitude Input #1 G 7 17 B H 8 J 9 18 19 K 10 20 Func Test Alt Cmpar Fail XPDR Fail #1
(disc ip)
(disc op)
(disc op) A1 A2 A4 B1 B2 B4 C1 C2 C4 D2 Air Data #2
(429 ip) Maint Data Input
(429 ip) A A B B Reserved A B A Data Link Output
(429 op) Maint Data Output
(429 op) B A Alt Src Select
(disc ip) B B Alt Cmpar En DL / DLP Ant BITE
(disc ip)
(prgm ip)
(prgrm ip) Altitude Type Select A com
---------------------- Course ---------------------
X Y Z Synchro Altitude #2 26VAC Ref H C
------------------------ Fine -----------------------
X Y Z Bottom Antenna Rsrvd #2 429 IP A Syncrho Flag #2
(disc ip) D4 com Rsrvd #2 429 IP B 1-23-01 RAS Figure 8 Middle Plug Connector Layout 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 19 Installation Installation Manual THIS PAGE INTENTIONALLY LEFT BLANK Page 20 560-0405-00 Rev 2001 by UPS Aviation Technologies Inc. December 14, 2001 Installation Manual 3.4.2 Bottom Plug Installation Signal Name 115 VAC Input HOT Future Spare 28 VDC Input Return Future Spare Future Spare Future Spare 115 VAC Input Return Signal Ground Future Spare 28 VDC Chassis Ground Suppression Suppression Pin No. Equipment Connection BP 1 BP 2 BP 3 BP 4 BP 5 BP 6 BP 7 BP 8 BP 9 BP 10 BP 11 BP 12 BP 13 Figure 9 Bottom Plug Interconnect Description 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 21 Installation Installation Manual Bottom Plug Not Used 4 Not Used 6 28 VDC Power Input 10
(+) 28VDC Power Input 3 Return
(-) Signal Ground 8 Not Used 2 7 115 vac Power
(Aircraft DC Ground) Input Return 115 v AC power input 1 Hot Not Used 5 Not Used 9 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 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Installation 3.4.3 Program Pin Inputs The 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 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:
Fax:
(405) 954-3116
(405) 954-3548 3.4.4 SDI Program The 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 (TP 3J) as follows:
Table 3 - SDI Program Pins Transponder #
SDI Prgm B SDI Prgm A Not Applicable 1 2 3 Common pin TP 3G Open Open Common Common TP 3J TP 3H Open Common Open Common 3.4.5 Max Airspeed Program The maximum (max) airspeed program pins are used to identify the aircrafts 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 2001 by UPS Aviation Technologies Inc. Page 23 Installation Installation Manual Table 4 - Max Airspeed Program Max airspeed connections Max Airspeed Not available Up to 75 knots 75 to 150 knots 150 to 300 knots 300 to 600 knots 600 to 1200 knots Above 1200 knots Not assigned Common pin Prgm C TP 5C Open Open Open Open Common Common Common Common TP 5D Prgm B TP 5B Open Open Common Common Open Open Common Common Prgm A TP 5A Open Common Open Common Open Common Open Common 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 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 Program Differential Delay (nsec) 0 to 50 51 to 150 151 to 250 251 to 350 TP 3C Delay Program Connections Delay B TP 3D Open Open Common Common Open Delay A TP 3E Open Common Open Common Common Add delay to top antenna Add delay to bottom antenna Programmed Delay
(nsec) 0 100 200 300 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 trans-
ponder and the antenna. Typical cable delay is 1.54 nsec/ft. Page 24 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 Open 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. enable antenna BITE test disable antenna BITE test Table 6 - Altitude Type Selection Program Pins Data Source 429 Data Synchro Data Gillham Data Common Pin MP 6F Open Open Common MP 6H MP 6G Open Common Common 3.5 Interface Connections 3.5.1 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 2001 by UPS Aviation Technologies Inc. Page 25 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 con-
nected 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 alti-
tude 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 trans-
ponder will use:
Ground ..................uses control panel port A Open......................used control panel port B Page 26 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 ac-
tive 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 trans-
ponder 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 interroga-
tions. 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 con-
nected to the air/ground switch. When on the ground, the transponder will inhibit re-
plies 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 2001 by UPS Aviation Technologies Inc. Page 27 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, syn-
chro, or ADC inputs, as selected. Ground .................. Open...................... altitude compare enabled 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 inva-
lid 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 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 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 Interface The 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 with both Collins and ACSS TCAS units. 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 29 Installation Installation Manual 3.6 Data Loader Interface Table 7 - Data Loader Plug Reference Section Signal Name Pin No. Equipment Connection 429 Input (Provisions Only) 429 Input (Provisions Only) Shield Ground 429 Output (Provisions Only) 429 Output (Provisions Only) Shield Ground 2.5 Portable Data Loader (PDL) ARINC 615 Input Bus A B Spare Spare Chassis Ground (429 Input Bus Shield) GND Spare Spare PDL ARINC 615 Output Bus A B Spare Spare Spare Spare Spare Spare Chassis Ground (429 Output Bus Shield) GND Spare Spare Spare 115 Volt AC Power Input HOT Chassis Ground GND 115 Volt AC Power Input COMMON Spare Spare Spare Spare Spare Spare Spare Spare Spare Spare Spare 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 Page 30 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Installation Table 7 - Data Loader Plug (Continued) Reference Section Signal Name Pin No. Equipment Connection Maintenance Data/Software Update Port Maintenance Data/Software Update Port Spare Spare Spare 28 Volt DC Power Input POS 28 Volt DC Power Return NEG Spare RS-232 Input RS-232 Output PDL CTS Input PDL RTS Output Spare Spare Spare Spare Chassis Ground GND Chassis Ground GND PDL Function Discrete #1 PDL Function Discrete #2 PDL Function Discrete #3 PDL Function Discrete #4 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 31 Installation Installation Manual VIEW OF MATING CONNECTOR ON AIRCRAFT VIEW OF CONNECTOR ON UNIT Figure 11 Data Loader Page 32 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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. Transponder Power Check 115 VAC 115 Return 28 VDC 28 Return Note: The unit is able to accept either 28 VDC or 115 VAC. BP1 (see note below) BP10 (see note below) BP7 BP 3 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 33 Post-Installation Checkout Installation Manual NOTES Page 34 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Equipment Removal and Replacement Section 5 - Equipment Removal and Re-
placement 5.1 Removal 5.1.1 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 2001 by UPS Aviation Technologies Inc. Page 35 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 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 trans-
ponder 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 con-
trol. 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 2001 by UPS Aviation Technologies Inc. Page 37 Specifications NOTES Installation Manual Page 38 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Specifications Section 7 - Specifications This section includes detailed electrical, physical, environmental, and performance speci-
fications 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 2001 by UPS Aviation Technologies Inc. Page 39 Specifications Installation Manual 5.04 7.64 14.107 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 65C 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 environ-
ments. 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 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 2001 by UPS Aviation Technologies Inc. Page 41 Specifications NOTES Installation Manual Page 42 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 2001 by UPS Aviation Technologies Inc. Page 43 Limitations NOTES Installation Manual Page 44 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Troubleshooting Introduction Section 9 - Troubleshooting 9.1 Introduction and Overview 9.1.1 The 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 through the 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 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 BOT ANT ALT TEST DATA LOADER Weight 10.0 lbs. MAINTENANCE DISPLAY AT7000 Mode S Data Link Transponder Model: AT7000 Mode S Transponder Map/Database Software PN:
430-6091 - 00 - 00 C D E BA HW Mod ZYXWVUTSRPNM AC F G H J K L AB ADAE AF AGAH AJ AK ALAMAN AA C D E BA SW Mod ZYXWVUTSRPNM AC F G H J K L AB ADAE AFAG AH AJ AK ALAMAN AA barcode of serial number SN '1234567'
TSO-C112 Class 2A7, 121, 011 RTCA/DO-178B Software Level B RTCA/DO-160D Env. Cat. FCC ID xxxxxxx UPS Aviation Technologies, Salem OR USA Figure 14. AT7000 Mode S Transponder 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 45 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 fol-
lows:
and
) or next (
These buttons are used to select the column. When pressing one of these buttons, the top page of either the previous (
) group will be displayed. 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. The pages wrap around. The display is used only for displaying trans-
ponder information. No configuration or data can be input using the front panel display and buttons. and Note:
Test Status LEDs 9.2.2 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 but-
ton will illuminate the failure for 30 seconds. LED XPDR PASS XPDR FAIL CTRL PNL TOP ANT BOT ANT ALT Color Green Red Red Red Red Red Table 8 - Status LEDs Summary 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 con-
trol 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). 9.2.3 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 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Troubleshooting Power Up Startup Display SW Version Self Test Mode AT7000 Self Test Running Self Test Status Transponder Fail Status Control Panel Fail Status Top Antenna Fail Status Bottom Antenna Fail Status Altitude Fail Status Normal Mode UPS Aviation Technologies PROGRAM INPUTS DISCRETE INPUTS EXTERNAL INTERFACES Mode S Address Control Panel SDI Program Altitude Select Max Airspeed Air/Ground Altitude Type Antenna Delay ADC (429) Altitude Inputs*
(x2)
*Program Pin Dependent OR Gillham Altitude
(x2) Inputs*
*Program Pin Dependent OR Synchro Altitude Inputs*
(x2)
*Program Pin Dependent Control Panel Inputs
(x2) Antenna BITE Flight ID Input Antenna Program DataLink Interface 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 2001 by UPS Aviation Technologies Inc. Page 47 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 soft-
ware 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 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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. ICAO Address b. Internal component of Transponder c. Top Transmitter d. Bottom Transmitter e. Tx Synth Lock f. Rx Synth Lock g. Top Receiver h. Bottom Receiver i. 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 2001 by UPS Aviation Technologies Inc. Page 49 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 oc-
curred for each while they were selected. Page 50 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Troubleshooting 9.2.4 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 TECH-
NOLOGIES AT7000 Mode S or TEST PRESS 9.2.4.2 Program Inputs The program inputs group is used to display the settings of each of the transponders 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 hexadeci-
mal. Mode S Address:
OCT HEX 12345670 053977 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 51 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 is not available) 0) invalid 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:
0) ADC (429) 1) Synchro Page 52 Altitude Type:
ADC (429) ARINC 429 air data input 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 2001 by UPS Aviation Technologies Inc. Page 53 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:
Func Test:
A Standby 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:
Sync #1:
Sync #2:
1 on Valid Invalid Page 54 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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/Gnd #2:
air 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 in-
puts, such as the altitude and control panel inputs. EXTERNAL INTER-
FACES 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 No data (no 429 altitude input data) Invalid (invalid status on 429 input data) 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 55 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 Compare Fail (if the altitude compare is enabled and the compare fails) Invalid (for an invalid Gillham code input) 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:
Flag:
Valid 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 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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:
Mode:
A 1200ident 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 No data (no 429 control panel data) Invalid (invalid status on the 429 input 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 No data (no input data) Invalid (invalid status on the input data) 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 57 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 No data (no input data) Invalid (invalid status on the 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 No data (no input data) Invalid (invalid status on the input data) Page 58 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 Installation Manual Troubleshooting 9.3 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. 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 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 2001 by UPS Aviation Technologies Inc. Page 59 Troubleshooting Installation Manual Table 9 - Troubleshooting Guide Cause Normal operation. 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. Top antenna not connected correctly. Bottom antenna not connected correctly. Corrective Action No action necessary. Check wiring. Re-
place faulty control panel. Problem XPDR PASS LED is illumi-
nated. XPDR FAIL LED is illumi-
nated. CTRL PNL failure light is il-
luminated and the Control Panel Fail Status page reads Invalid, Rate Failed or No Data. TOP ANT failure light is illu-
minated and Top Antenna page reads BITE Test Fail. BOT ANT failure light is il-
luminated and Bottom An-
tenna page reads BITE Test Fail. ALT SIG failure light is illu-
minated. The Altitude Fail Status will read Invalid or No Data if the type of alti-
tude 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 In-
valid or Flagged. Page 60 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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 2001 by UPS Aviation Technologies Inc. Page 61 Periodic Maintenance NOTES Installation Manual Page 62 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001 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. Nomenclature: AT7000 Part No.: 430-6091-100 TSO No.: TSO C112 Table 10 - Environmental Requirements Manufacturer:
UPS Aviation Technologies 2345 Turner Road SE Salem, Oregon 97302 Environment Temperature and Altitude Section Category 4 A2 Temperature Variation Humidity Operational Shocks and Crash Safety Vibration Explosion Proofness Waterproofness Fluids Susceptibility Sand and Dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Conducted Sus-
ceptibility - Power Inputs Induced Signal Susceptibility Radio Frequency Susceptibility
(Radiated and Conducted) Emission of Radio Frequency En-
ergy Lightning Induced Transient Sus-
ceptibility Lightning Direct Effects Icing Electrostatic Discharge (ESD) 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 B B B S & T X X X X X X Z A & E A A & E C V M A3 C2 E2 X X A Comment 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 Minimum 5 C per minute Severe humidity environment. Tested for operational shock and crash safety. Aircraft type 5, test type R S (curves B and M), T (curves B, B1 and R) Not applicable, no test required Not applicable, no test required Not applicable, no test required Not applicable, no test required Not applicable, no test required Not applicable, no test required
< 0.3 meter 28 volt DC and 115 volt 400 Hz AC Z is minimum requirement, C is the goal U is minimum requirement, V is the goal Pin injection Unshielded cables Shielded cables Not applicable, no test required Not applicable, no test required 560-0405-00 Rev December 14, 2001 2001 by UPS Aviation Technologies Inc. Page 63 Environmental Qualifications Installation Manual NOTES Page 64 2001 by UPS Aviation Technologies Inc. 560-0405-00 Rev December 14, 2001
frequency | equipment class | purpose | ||
---|---|---|---|---|
1 | 2002-01-23 | 1090 ~ 1090 | TNB - Licensed Non-Broadcast Station Transmitter | Original Equipment |
app s | Applicant Information | |||||
---|---|---|---|---|---|---|
1 | Effective |
2002-01-23
|
||||
1 | Applicant's complete, legal business name |
Garmin AT, Inc.
|
||||
1 | FCC Registration Number (FRN) |
0001549476
|
||||
1 | Physical Address |
2345 Turner Road SE
|
||||
1 |
Salem, Oregon 97302
|
|||||
1 |
United States
|
|||||
app s | TCB Information | |||||
1 | TCB Application Email Address |
d******@ckccertification.com
|
||||
1 | TCB Scope |
B3: Maritime & Aviation Radio Services equipment in 47 CFR parts 80 & 87
|
||||
app s | FCC ID | |||||
1 | Grantee Code |
EOJ
|
||||
1 | Equipment Product Code |
AT7000
|
||||
app s | Person at the applicant's address to receive grant or for contact | |||||
1 | Name |
G******** C********
|
||||
1 | Title |
RF Engineering Manager
|
||||
1 | Telephone Number |
503-3********
|
||||
1 | Fax Number |
503-3********
|
||||
1 |
g******@garmin.com
|
|||||
app s | Technical Contact | |||||
1 | Firm Name |
CKC Laboratories, Inc.
|
||||
1 | Name |
J**** W****
|
||||
1 | Physical Address |
5473A Clouds Rest
|
||||
1 |
Mariposa, California 95338
|
|||||
1 |
United States
|
|||||
1 | Telephone Number |
1-800******** Extension:
|
||||
1 | Fax Number |
209-9********
|
||||
1 |
s******@ckc.com
|
|||||
app s | Non Technical Contact | |||||
1 | Firm Name |
CKC Laboratories, Inc.
|
||||
1 | Name |
J******** W****
|
||||
1 | Physical Address |
5473A Clouds Rest
|
||||
1 |
Mariposa, California 95338
|
|||||
1 |
United States
|
|||||
1 | Telephone Number |
1-800******** Extension:
|
||||
1 | Fax Number |
209-9********
|
||||
1 |
s******@ckc.com
|
|||||
app s | Confidentiality (long or short term) | |||||
1 | Does this application include a request for confidentiality for any portion(s) of the data contained in this application pursuant to 47 CFR § 0.459 of the Commission Rules?: | Yes | ||||
1 | Long-Term Confidentiality Does this application include a request for confidentiality for any portion(s) of the data contained in this application pursuant to 47 CFR § 0.459 of the Commission Rules?: | No | ||||
if no date is supplied, the release date will be set to 45 calendar days past the date of grant. | ||||||
app s | Cognitive Radio & Software Defined Radio, Class, etc | |||||
1 | Is this application for software defined/cognitive radio authorization? | No | ||||
1 | Equipment Class | TNB - Licensed Non-Broadcast Station Transmitter | ||||
1 | Description of product as it is marketed: (NOTE: This text will appear below the equipment class on the grant) | Mode S Datalink Transponder | ||||
1 | Related OET KnowledgeDataBase Inquiry: Is there a KDB inquiry associated with this application? | No | ||||
1 | Modular Equipment Type | Does not apply | ||||
1 | Purpose / Application is for | Original Equipment | ||||
1 | Composite Equipment: Is the equipment in this application a composite device subject to an additional equipment authorization? | No | ||||
1 | Related Equipment: Is the equipment in this application part of a system that operates with, or is marketed with, another device that requires an equipment authorization? | No | ||||
1 | Is there an equipment authorization waiver associated with this application? | No | ||||
1 | If there is an equipment authorization waiver associated with this application, has the associated waiver been approved and all information uploaded? | No | ||||
app s | Test Firm Name and Contact Information | |||||
1 | Firm Name |
CKC Laboratories, Inc.
|
||||
1 | Name |
S****** B********
|
||||
1 | Telephone Number |
209-9******** Extension:
|
||||
1 | Fax Number |
866-7********
|
||||
1 |
r******@ckc.com
|
|||||
Equipment Specifications | |||||||||||||||||||||||||||||||||||||||||
---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
Line | Rule Parts | Grant Notes | Lower Frequency | Upper Frequency | Power Output | Tolerance | Emission Designator | Microprocessor Number | |||||||||||||||||||||||||||||||||
1 | 1 | 87 | 1090.00000000 | 1090.00000000 | 500.0000000 | 0.0110000000 % | 14M0M1D |
some individual PII (Personally Identifiable Information) available on the public forms may be redacted, original source may include additional details
This product uses the FCC Data API but is not endorsed or certified by the FCC