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Installation Manual

Environmental Qualifications

560-0405-00 Rev –
December 14, 2001

Page 63

© 2001 by UPS Aviation Technologies Inc.

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

4

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

5

B

Minimum 5

°

C per minute

Humidity

6

B

Severe humidity environment.

Operational Shocks and Crash
Safety

7

B

Tested for operational shock and crash safety.
Aircraft type 5, test type R

Vibration

8

S & T

S (curves B and M), T (curves B, B1 and R)

Explosion Proofness

9

X

Not applicable, no test required

Waterproofness

10

X

Not applicable, no test required

Fluids Susceptibility

11

X

Not applicable, no test required

Sand and Dust

12

X

Not applicable, no test required

Fungus Resistance

13

X

Not applicable, no test required

Salt Spray

14

X

Not applicable, no test required

Magnetic Effect

15

Z

< 0.3 meter

Power Input

16

A & E

28 volt DC and 115 volt 400 Hz AC

Voltage Spike

17

A

Audio Frequency Conducted Sus-
ceptibility - Power Inputs

18

A & E

Induced Signal Susceptibility

19

C

Z is minimum requirement, C is the goal

Radio Frequency Susceptibility
(Radiated and Conducted)

20

V

U is minimum requirement, V is the goal

Emission of Radio Frequency En-
ergy

21

M

Lightning Induced Transient Sus-
ceptibility

22

A3
C2
E2

Pin injection
Unshielded cables
Shielded cables

Lightning Direct Effects

23

X

Not applicable, no test required

Icing

24

X

Not applicable, no test required

Electrostatic Discharge (ESD)

25

A

Содержание AT7000

Страница 1: ...AT7000 Mode S Transponder Installation Manual December 14 2001 560 0405 00 Rev ...

Страница 2: ...s 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 2345 Turner Rd SE PO Box 13549 Salem OR 97302 Salem OR 97309 USA Phone 503 581 8101 800 525 6726 Fax 503 364 2138 In Canada ...

Страница 3: ... 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 ...

Страница 4: ...Installation Manual AT7000 Mode S Transponder 560 0405 00 Rev December 14 2001 NOTES ...

Страница 5: ...isions For each revision insert the revised pages into your manual and discard the replaced pages On this record page note the revision number and date date pages were inserted into the manual and the initials of the person inserting the pages Revision Number Revision Date Date Inserted By Revision Number Revision Date Date In serted By ...

Страница 6: ...00 Page 23 00 Page 24 00 Page 25 00 Page 26 00 Page 27 00 Page 28 00 Page 29 00 Page 30 00 Page 31 00 Page 32 00 Page 33 00 Page 34 00 Page 35 00 Page 36 00 Section and Page Revision Page 37 00 Sec 4 Post Install Checkout Page 38 00 Page 39 00 Sec 5 Equipment Rem and Rep Page 40 00 Page 41 00 Sec 6 Operation Page 42 00 Page 43 00 Sec 7 Specifications Page 44 00 Page 45 00 Page 46 00 Page 47 00 Sec...

Страница 7: ...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 Pl...

Страница 8: ...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...

Страница 9: ...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 S...

Страница 10: ...AT7000 Mode S Transponder Installation Manual Page vi 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc NOTES ...

Страница 11: ...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 Figure 1 AT7000 System Block Diagram AT7000 System Block Diagram AT700...

Страница 12: ...nsponders 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 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...

Страница 13: ...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 wi...

Страница 14: ...AT7000 Mode S Transponder Introduction Page 4 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc NOTES ...

Страница 15: ...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 eithe...

Страница 16: ...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 MAINTENANCE DISPLAY XPDR PASS XPDR FAIL CTRL PNL ALT TOP ANT BOT ANT TEST DATA LOADER AT7000 Mode S Data Link Transponder barcode of serial number SN 1234567 UPS Aviation Technologies Salem OR USA Model AT7000 PN 430 6091 00 00 SW Mod T...

Страница 17: ...er 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 Minimal Necessary Labels Label Description Minim...

Страница 18: ...missions 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 diagno...

Страница 19: ...nel 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 ...

Страница 20: ...System Description Installation Manual Page 10 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc NOTES ...

Страница 21: ...e 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 Equi...

Страница 22: ...enna 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 Margol...

Страница 23: ...ARINC 429 A B TP 2E TP 2F Reserved 1 Output ARINC 429 A B TP 2G TP 2H Reserved Discrete Input 1 TP 2J 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 Top Bot B A Common TP 3C TP 3D TP 3E TP 3F 3 4 4 SDI Program B A Common TP 3G TP 3H TP 3J 3...

Страница 24: ...puts 2 1 TP 5J TP 5K To Air Ground Relay 3 5 12 NAV Data Flight ID 429 Input Bus A B TP 6A TP 6B From LDPU ADLP Reserved A B TP 6C TP 6D Reserved A B TP 6E TP 6F Reserved TP 6G Reserved A B TP 6H TP 6J 3 4 7 Antenna Program TP 6K 3 5 5 Control Panel Input Bus 1 A B TP 7A TP 7B To Pin 22 of Control Panel Optional To Pin 23 of Control Panel Optional Reserved TP 7C 3 5 5 1 Control Panel Data Port Sel...

Страница 25: ...rse X Y Z Fine X Y Z H C 26VAC Ref Synchro Flag 1 disc ip RSVD IP 2 disc ip Max Airspeed Program A B C com TX COORD A B 429 ip XT COORD A B 429 pp Air Gnd 2 disc ip Air Gnd 1 disc ip Flight ID FMS A B 429 ip ADL Input A B 429 ip ADL Output A B 429 op ADL IP Sel disc ip Reserved A B Antenna Program prgmip Control Panel IP 1 A B 429 ip RSVD IP 3 disc ip Cntl Pnl Select disc ip Control Panel IP 2 A B...

Страница 26: ...Installation Installation Manual Page 16 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc THIS PAGE INTENTIONALLY LEFT BLANK ...

Страница 27: ... 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 Reserved 1 ARINC 429 Input A B MP 3F MP 3G Reserved for mode control panel or other DAPS inputs 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 ...

Страница 28: ... B MP 6A MP 6B Hardware Provisions Maintenance Data 429 Output A B MP 6C MP 6D 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 MP 6K 3 5 3 Synchro Altitude Input 2 X Course Y Course Z Course Ref H Ref C X F...

Страница 29: ...E prgrm ip Maint Data Input A B 429 ip Maint Data Output A B 429 op Synchro Altitude 2 X Y C X Bottom Antenna 1 23 01 RAS MP 11 12 13 14 15 16 17 18 19 21 22 23 24 com Rsrvd 1 IP A B 429 ip Func Test disc ip Alt Cmpar Fail disc op XPDR Fail 1 disc op A2 A4 B1 B2 B4 C1 C2 C4 D2 D4 com Air Data 2 A B 429 ip Reserved A B Alt Cmpar En disc ip DL DLP prgm ip Alt Src Select disc ip Altitude Type Select ...

Страница 30: ...Installation Installation Manual Page 20 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc THIS PAGE INTENTIONALLY LEFT BLANK ...

Страница 31: ...nal Name Pin No Equipment Connection 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 Figure 9 Bottom Plug Interconnect Description ...

Страница 32: ... Connector Layout Bottom Plug 12 Suppression Pulse Input 13 int conx to pin 12 Suppression Pulse Input 11 Chassis Ground Aircraft DC Ground 9 Not Used 1 115 v AC power input Hot 2 Not Used 3 28VDC Power Input Return 7 115 vac Power Input Return 8 Signal Ground Aircraft DC Ground 6 Not Used 5 Not Used 4 Not Used 10 28 VDC Power Input ...

Страница 33: ... 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 nu...

Страница 34: ...p 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 Delay Program Connections Differential Delay nsec Delay B TP 3D Delay A TP 3E Programm...

Страница 35: ...TE 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 altit...

Страница 36: ...e 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 ...

Страница 37: ...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 inpu...

Страница 38: ...ta 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 ou...

Страница 39: ...r 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 ...

Страница 40: ...Provisions Only Spare 3 Spare 4 Chassis Ground 429 Input Bus Shield GND 5 Shield Ground Spare 6 Spare 7 PDL ARINC 615 Output Bus A B 8 9 429 Output Provisions Only 429 Output Provisions Only Spare 10 Spare 11 Spare 12 Spare 13 Spare 14 Spare 15 Chassis Ground 429 Output Bus Shield GND 16 Shield Ground Spare 17 Spare 18 Spare 19 115 Volt AC Power Input HOT 20 Chassis Ground GND 21 115 Volt AC Power...

Страница 41: ...are 35 Spare 36 28 Volt DC Power Input POS 37 28 Volt DC Power Return NEG 38 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 Funct...

Страница 42: ...Installation Installation Manual Page 32 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc VIEW OF MATING CONNECTOR ON AIRCRAFT VIEW OF CONNECTOR ON UNIT Figure 11 Data Loader ...

Страница 43: ...d 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 ...

Страница 44: ...Post Installation Checkout Installation Manual Page 34 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc NOTES ...

Страница 45: ...le 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 transpo...

Страница 46: ...er 14 2001 2001 by UPS Aviation Technologies Inc 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 ...

Страница 47: ...ponder 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 receiv...

Страница 48: ...Specifications Installation Manual Page 38 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc NOTES ...

Страница 49: ...s 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 Con...

Страница 50: ...rature 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 environ ments 7 4 Transponder Performance TSO TSO C112 TSO Class CL 2A7 121 011 Warm up None required Re...

Страница 51: ... 2001 by UPS Aviation Technologies Inc 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 ...

Страница 52: ...Specifications Installation Manual Page 42 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc NOTES ...

Страница 53: ...ations 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 ...

Страница 54: ...Limitations Installation Manual Page 44 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc NOTES ...

Страница 55: ...light 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 ...

Страница 56: ...rcraft 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 Table 8 Status LEDs Summary LED Color Description XPDR PASS Green Transponder pass turned on if B I T E passes and the transponder is able to operate XPD...

Страница 57: ...nterface TCAS Interface Control Panel Transponder Fail Status Control Panel Fail Status Top Antenna Fail Status Bottom Antenna Fail Status Altitude Fail Status x2 x2 x2 x2 UPS Aviation Technologies Power Up DISCRETE INPUTS AT7000 Self Test Running Altitude Select Air Ground OR OR Program Pin Dependent Program Pin Dependent Program Pin Dependent Figure 15 Maintenance Displays 9 2 3 1 Page Descripti...

Страница 58: ...tus page displays the number of currently active fault types 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 atte...

Страница 59: ...nth 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 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...

Страница 60: ...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 sele...

Страница 61: ...ult 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 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 9 2 4 3 Mode S Address This display is for decoding the 24 bit mode S address displayed in octal and hexadeci mal PROGRA...

Страница 62: ... This display is for the max airspeed program input The airspeed displays are 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 ...

Страница 63: ... 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 The possible displayed antenna BITE selections are 0 Disabled 1 Enabled 9 2 4 9 Antenna Program This page displays the antenna program input Antenna Delay Delay 51 to 150 nsec Ant botto...

Страница 64: ...h of the discrete inputs grouped in the following pages Discrete Inputs Page 1 The top line is used to display the control panel selected either A or B The second line is used to display the current mode of the standby input either Standby or Active The third line is used to display the state of the functional test input either Test or Norm Discrete Inputs Page 2 The top line is used to display th...

Страница 65: ... 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 9 2 6 1 ADC Altitude Inputs This page is used to display the altitude and status from the air data computer inputs The data is displaye...

Страница 66: ...tatus 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 The data is displayed for both the 1 and 2 inputs The altitude is displayed in feet with a 1 foot resoluti...

Страница 67: ...rting 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 The third line is used to display the current setting of the input Flight ID if the input is set to ...

Страница 68: ...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 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 ...

Страница 69: ...losed 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...

Страница 70: ...CTRL PNL failure light is il luminated and the Control Panel Fail Status page reads Invalid Rate Failed or No Data Control panel not connected Check wiring Re place faulty control panel TOP ANT failure light is illu minated and Top Antenna page reads BITE Test Fail Top antenna not connected correctly BOT ANT failure light is il luminated and Bottom An tenna page reads BITE Test Fail Bottom antenna...

Страница 71: ...ation Manual Periodic Maintenance 560 0405 00 Rev December 14 2001 Page 61 2001 by UPS Aviation Technologies Inc Section 10 Periodic Maintenance 10 1 Maintenance There are no internal manual adjustments needed ...

Страница 72: ...Periodic Maintenance Installation Manual Page 62 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc NOTES ...

Страница 73: ... shock and crash safety Aircraft type 5 test type R Vibration 8 S T S curves B and M T curves B B1 and R Explosion Proofness 9 X Not applicable no test required Waterproofness 10 X Not applicable no test required Fluids Susceptibility 11 X Not applicable no test required Sand and Dust 12 X Not applicable no test required Fungus Resistance 13 X Not applicable no test required Salt Spray 14 X Not ap...

Страница 74: ...Environmental Qualifications Installation Manual Page 64 560 0405 00 Rev December 14 2001 2001 by UPS Aviation Technologies Inc NOTES ...

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