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

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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
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© 2001 by UPS Aviation Technologies Inc.
AT7000 Mode S Transponder
Installation Manual
List of Effective Pages
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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
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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
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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
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AT7000 Mode S Transponder
Installation Manual
NOTES
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© 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
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© 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.
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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.
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© 2001 by UPS Aviation Technologies Inc.
AT7000 Mode S Transponder
Introduction
NOTES
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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.
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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
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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
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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
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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)
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© 2001 by UPS Aviation Technologies Inc.
System Description
Installation Manual
NOTES
Page 10
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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.
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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
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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)
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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)
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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
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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)
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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)
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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
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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
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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
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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:
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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.
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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
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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
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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.
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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
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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.
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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
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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
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VIEW OF MATING CONNECTOR ON AIRCRAFT
VIEW OF CONNECTOR ON UNIT
Figure 11 – Data Loader
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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.
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Post-Installation Checkout
Installation Manual
NOTES
Page 34
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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.
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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.
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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).
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Specifications
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NOTES
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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.
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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
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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.
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Specifications
Installation Manual
NOTES
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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.
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Limitations
Installation Manual
NOTES
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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
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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.
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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
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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
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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.
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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.
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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
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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
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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.
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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
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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)
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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
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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)
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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)
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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.
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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.
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Installation Manual
Periodic Maintenance
Section 10 - Periodic Maintenance
10.1
Maintenance
There are no internal manual adjustments needed.
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Periodic Maintenance
Installation Manual
NOTES
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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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